Shaft-less twin rotor turbomachinery and the applications
20220268206 · 2022-08-25
Inventors
Cpc classification
F01D15/08
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F02K9/48
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F01D11/00
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F05D2240/51
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F05D2220/10
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F02C6/02
MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
International classification
Abstract
This invention relates to shaft-less twin rotor turbomachinery and the applications the shaft-less turbomachine has a twin tubing rotator assembly with vortical effect passages forming a high power zone and lower power zone, the twin tubing rotator assembly has two rotors to rotate independently or together with multiple powers universal bearings, high speed seal assemblies, it combines the best features of high flow rate of axial turbomachine and high pressure output of centrifugal turbomachine with the most efficient blade and turbine designs, it represents a new era of this turbomachine, disrupt invention and would power millions of turbomachines like the turbo pumps for rocket engines, jet engine/ramjet, submarines/torpedo and ships with the most advanced propellers as well as compression/pumping stations, turbines for power plants at an unprecedented level of efficiency and reliability with the twin tubing full port rotor assembly.
Claims
1. A turbomachine system has at least one turbomachine, the at least one turbomachine has a body assembly, a twin tubing rotor assembly movably disposed in said body assembly by means of at least two ball bearings disposed between said twin tubing rotor assembly and said body assembly for providing dynamic supports, and by means of at least two seal assemblies disposed between said twin tubing rotor assembly and said body assembly for providing seals, said body assembly has a left body assembly having at least one fixed wheel and a body bore and a right body assembly having at least one fixed wheel and a body bore, said left body assembly has one of plurality of structures including one piece structure and two-piece structure, said right body assembly has one of plurality of structures including one piece structure and two-piece structure, said twin tubing rotor assembly has a left rotor having a tubing housing having at least one internal rotary wheel and at least one external rotary wheel and a tubing bore, a right rotor having a tubing housing having at least one internal rotary wheel and at least one external rotary wheel and a tubing bore, and a union to support said left rotor and said right rotor, said union has one of plurality of supporting methods including (1) two static supports (2) two dynamic supports (3) one static support and one dynamic support (4) at least one hybrid support, said static support is defined by one of plurality of methods including welding, press fitting and gluing, said dynamic support is defined by one of the at least two ball bearings disposed between said union and one of said left rotor and said right rotor, the at least one hybrid support is defined by a magnetic coupling, each of the at least two ball bearings has a left ring and a right ring and multiple balls disposed between said left ring and said right ring, a left, wedge insert ring and a right wedge insert ring respectively disposed between said left ring and said right ring, said left ring has a left conical surface and a left ball groove, said right ring has a right conical surface and a right ball groove, said multiple balls are respectively engaged with said left ball groove and said right ball groove, said left insert ring and said right insert ring are respectively disposed between said left conical surface and said right conical surface, said left ring and said right ring have one of plurality of materials including magnetic materials and nonmagnetic materials the at least two ball bearings has fluids for providing seals, each of the at least two seal ring assemblies disposed between said tubing bore and said body bore with press fits has at least one fixed V shape seal ring having a conical surface and at least one dynamic V seal ring having a mated conical surface engaged with said conical surface of the at least one fixed V shape seal ring in one of plurality methods including an axial method and a radial method for providing dynamic as well as static seals, said each of the at least two seal ring assemblies has a top gap defined by said body bore and the at least one dynamic V shape seal ring, and a low gap defined by said tubing bore and the at least one fixed V shape seal ring, said each of the at least two seal ring assemblies has at least one groove between the at least one fixed V shape seal ring and the at least one dynamic V shape seal ring said turbomachine system has one of plurality of power supplies including (a) internal gas powers (b) internal electrical powers (c) internal gas powers and internal electrical powers (d) external gas powers external electrical powers (f) external gas powers and internal electrical powers (g) external powers (h) internal powers.
2. The turbomachine system of claim 1, wherein said body assembly having a main port defined by an inlet port, an outlet port, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber, and a second left rotor chamber connected with a relief hole, said right assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber, and a second right rotor chamber connected to a relief hole, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades and a relief hole, said right body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades and a relief hole, said left rotor has a first of the at least one internal rotary wheel having multiple blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left set of holes communicating between said main port and said first left rotor chamber, a second of the at least one external rotary wheel having multiple blades and a third of the at least one external rotary wheel having multiple blades disposed in said second left rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades, said right rotor has a first of the at least one internal rotary wheel having multiple blades a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rotary wheel having multiple blades and a third of the at least one external rotary wheel having multiple blades disposed in said second right rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades, said union has an internal rotary wheel having multiple blades and one of plurality of hole forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
3. The turbomachine system of claim 1, wherein said body assembly having a main port defined by an inlet port, an outlet port and an left electrical device having a left electrical stator and a left electrical rotor and a right electrical device having a right electrical stator and a right electrical rotor, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber, said right assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having said left electrical stator in said second left rotor chamber, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left set of holes communicating between said main port and said first left rotor chamber, a second of the at least one external rotary wheel having said left electrical rotor engaged with said left electrical stator in said second right rotor chamber, said right body assembly has a first of the at least one fixed wheel having said right electrical stator in said second tight rotor chamber, said right rotor has a first of the at least one internal rotary wheel having blades and a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said second right rotor chamber, said union has an internal rotary wheel having blades and one of plurality of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
4. The turbomachine system of claim 1, wherein said body assembly having a main port defined by an inlet port, an outlet port and a right electrical device having a right stator and a right electrical rotor and a relief hole said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber connected with said relief hole, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said union has an external wall having one of the at least two seal assemblies between said second left rotor chamber and said second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left set of first set of holes communicating between said main port and said first left rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades disposed in said second left rotor chamber sandwiching said second one of the at least one fixed wheel having multiple blades, said right body assembly has a first of the at least one fixed wheel having said right electrical stator, a first of the at least one internal rotary wheel having blades and a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said second right rotor chamber, said union has an internal rotary wheel having blades and one of plurality of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
5. The turbomachine system of claim 1, wherein said body assembly having a main port defined by an inlet port, an function port defined by one of plurality of functions including inlet functions and outlet functions, a relief hole and a left electrical device having a left electrical stator and a left electrical rotor and a right electrical device having a right electrical stator and a right electrical rotor, said union has one of plurality of structures including no-internal wall and an internal wall having a left set of blades and a right set of blades, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber and a third left rotor camber, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber a second right rotor chamber, and a third right rotor camber, said left body assembly has a first of the at least one fixed wheel having said left electrical stator, a second of the at least one fixed wheel having multiple left through holes, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power, and a first of the at least one external rotary wheel having said left electrical rotor engaged with said left electrical stator in said first left rotor chamber, a second of the at least one external rotary wheel having blades in said second left rotor chamber and at least one left set of holes between said main port and said second left rotor chamber, a third of the at least one external rotary wheel having blades disposed in said third left rotor chamber engaged with said right rotor, said right body assembly has a first of the at least one fixed wheel having said right electrical stator, a second of the at least one fixed wheel having multiple right through holes, said right rotor has a first of the at least one internal rotary wheel having blades dividing said main port into a high power zone and a lower power and a first of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said first left rotor chamber, a second of the at least one external rotary wheel having blades disposed in said second right rotor chamber, and at least one right set of holes communicating between said main port and said second right rotor chamber, a third of the at least one external rotary wheel having multiple blades disposed in said third right rotor chamber engaged with said left rotor.
6. The turbomachine system of claim 3, said union has one of plurality of structures connected to said external power supplies including (a) gear train power supplies (b) belt/wheel powers supplies.
7. The turbomachine system of claim 1, said body assembly has a main port defined by a left inlet port and a right inlet port, at least one outlet port and a left electrical device having a left electrical stator and a left electrical rotor and a right electrical device having a right electrical stator and a right electrical rotor, said left body assembly has a left rotor bore receiving said left rotor to form an external left rotor chamber, an internal left rotor chamber having multiple relief holes extending to the at least one outlet port and a first left rotor chamber, said right assembly has a right rotor bore receiving said right rotor to form an external right rotor chamber and an internal right rotor chamber having multiple relief holes extending to the at least one outlet port and a first right rotor chamber, said left, body assembly has a first the at least one fixed wheel having said left electrical stator, a second of the at least one fixed wheel having external gas injectors extending to said left inlet port, a third of the at least one fixed wheel having external multiple blades, a first the at least one fixed wheel having internal gas injectors extending to said left, inlet port, a second of the at least one fixed wheel having internal multiple blades, said left rotor has a first of the at least one internal rotary wheel having blades and a second of the at least one internal rotary wheel having blades sandwiching said second of the at least one fixed wheel having internal multiple blades in said internal left rotor chamber, a first of the at least one external rotary wheel having said left electrical rotor engaged with said electrical stator in said first left rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades sandwiching said second of the at least one fixed wheel having external multiple blades in said external left rotor chamber, said right body assembly has a first the at least one fixed wheel having said right electrical stator, a second of the at least one fixed wheel having external gas injectors extending to said right inlet port, a third of the at least one fixed wheel having external multiple blades, a first the at least one fixed wheel having internal gas injectors extending to said right inlet port, a second of the at least one fixed wheel having internal multiple blades, said right rotor has a first of the at least one internal rotary wheel having blades and a second of the at least one internal rotary wheel having blades sandwiching said second of the at least one fixed wheel having internal multiple blades in said internal right rotor chamber a first of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said first right rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades sandwiching said second of the at least one fixed wheel having external multiple blades in said external right rotor chamber.
8. The turbomachine system of claim 1, wherein said body assembly has a main port defined by an inlet port, an outlet port, a left relief ring and a right relief ring, at least one joint control shaft having multiple through holes, said left body assembly has a left extension, a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber, said right body assembly has a right extension, a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades and a relief hole in said second left rotor chamber said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left set holes communicating between said main port and said first left rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades disposed in said second left rotor chamber sandwiching said second one of the at least one fixed wheel having multiple blades, said left extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said left body assembly also has multiple holes between said first left rotor chamber and said left extension, said right body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades and a relief hole in said second right rotor chamber, said right rotor has a first of the at least one internal rotary wheel having blades a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades disposed in said second right rotor chamber sandwiching said second of the at least one fixed wheel multiple blades, said right extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said right body assembly also has multiple holes between said first right rotor chamber and said right extension, said union has an internal rotary wheel having blades and one of plurality of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
9. The turbomachine system of claim 1, wherein said body assembly has a main port defined by an inlet port, an outlet port, two relief rings and at least one joint control shaft having multiple through holes, and a left electrical device having a left stator and a left electrical rotor and a right electrical device having a right stator and a right electrical rotor, said left body assembly has a left extension, a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber, said right assembly has a right extension, a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having said left electrical stator in said second left rotor chamber said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left set of holes communicating between said main port and said first left rotor chamber, and a second of the at least one external rotary wheel having said left electrical rotor engaged with said left electrical stator in said second left rotor chamber, said right body assembly has a first of the at least one fixed wheel having said right electrical stator, said right rotor has a first of the at least one internal rotary wheel having blades and a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rota wheel having said right electrical rotor engaged with said right electrical stator said second right rotor chamber, said left extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said left body assembly also has multiple holes between said first left rotor chamber and said left extension, said right extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said right body assembly also has multiple holes between said first right rotor chamber and said right extension, said union has an internal rotary wheel having blades and one of plurality of multiple of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
10. The turbomachine system of claim 2, wherein said body assembly has a main port defined by an inlet port, an outlet port, at least one control shaft having multiple through holes and a right electrical device having a right electrical stator and a right electrical rotor said union has an external wall said left body assembly has a left extension, a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber, said right body assembly has a right extension, a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel multiple blades and a relief hole in said second left rotor chamber, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, and a first of the at least one external rotary wheel having blades disposed in said first left rotor chamber and at least one left, set of holes communicating between said main port and said first left rotor chamber, a second of the at least one external rotary wheel having blades and a third of the at least one external rotary wheel having blades disposed in said second left rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades, said left extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said left body assembly also has multiple holes between said first left rotor chamber and said left extension, said right body assembly has a first of the at least one fixed wheel having said right electrical stator, said right rotor has a first of the at least one internal rotary wheel having blades and a first of the at least one external rotary wheel having blades disposed in said first right rotor chamber and at least one right set of holes communicating between said main port and said first right rotor chamber, a second of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said second right rotor chamber, said right extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said right body assembly also has multiple holes between said first right rotor chamber and said right extension, said union has an internal rotary wheel having blades and one of plurality of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
11. The turbomachine system of claim 2, wherein said body assembly has a main port defined by an inlet port, an outlet port, at least one control shaft having multiple through holes and a left electrical device having a left stator and a left electrical rotor and a right electrical device having a right stator and a right electrical rotor, said left body assembly has a left extension, a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber and a third left rotor chamber, said right body assembly has a right extension a right rotor bore receiving said right rotor to form a first tight rotor chamber and a second right rotor chamber and a third right rotor chamber, said left body assembly has a first of the at least one fixed wheel having said left electrical stator, a second of the at least one fixed wheel multiple through holes, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a lower power between said inlet port and said outlet port, a first of the at least one external rotary wheel having said left electrical rotor engaged with said left electrical stator in said first left rotor chamber, and a second of the at least one external rotary wheel having blades disposed in said second left rotor chamber and at least left one set of holes communicating between said main port and said second left rotor chamber, a third of the at least one external rotary wheel having blades disposed in said third left rotor chamber engaged with said right rotor, said left extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said left body assembly also has multiple holes between said first second rotor chamber and said left extension, said right body assembly has a first of the at least one fixed wheel having said right electrical stator and a second of the at least one fixed wheel multiple through holes, said right rotor has a first of the at least one internal rotary wheel having blades and a first of the at least one external rotary wheel having said right electrical rotor engaged with said right electrical stator in said first right rotor chamber a second of the at least one external rotary wheel having blades disposed in said second right rotor chamber and at least one right set of holes communicating between said main port and said second right rotor chamber, a third of the at least one external rotary wheel having blades disposed in said third right rotor chamber engaged with said left rotor, said right extension has an external surface and an internal surface and multiple cross holes between said external surface and said internal surface, said right body assembly also has multiple holes between said second right rotor chamber and said right extension, said union has an internal rotary wheel having blades and one of plurality of holes forms including multiple axial non-through holes and multiple axial through holes between said left rotor and said right rotor.
12. The turbomachine system of claim 9, where said turbomachine system has one of plurality of installing methods in marine vehicles defined by a front head and a back tail and a left side and right side including (1) the at least one turbomachine installed in said back tail of said marine vehicles (2) the at least one installed in said left side of said marine vehicles and the at least one installed in said right side of said marine vehicles (3) the at least one installed in said left side of said marine vehicles and the at least one installed in said right side of said marine vehicles and the at least one turbomachine installed in said back tail of said marine vehicles.
13. The turbomachine system of claim 1, wherein said body assembly has a left main port defined by a left inlet port and a left outlet port and a right main port defined by a right inlet port and a right outlet port, said union has one of plurality of structures including an (1) internal wall having a fight set of blades and a left set of blades (2) no internal wall, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber having a relief hole, said right assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber having a relief hole, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades, a left volute groove between the left outlet port and said first rotor chambers connected with said left inlet port said left rotor has a first of the at least one internal rotary wheel having blades defined by a combination of backward centrifugal blades and axial blades having an inside diameter dividing said main left main port into a high power zone and a low power zone, a second of the at least one internal rotary wheel having centrifugal blades engaged with said left volute groove and an opening, and an internal groove between said first of the at least one internal rotary wheel, and multiple through holes between said opening and said internal groove, said left rotor also has a first of the at least one external rotary wheel having blades and a second of the at least one external rotary wheel having blades disposed in said second left rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades, said right body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades, a right volute groove between said right outlet port and said first right rotor chamber connected with said right inlet port, said right rotor has a first of the at least one internal rotary wheel having blades defined by a combination of backward centrifugal blades and axial blades having an inside diameter dividing said right main port into a high power zone and a low power zone, a second of the at least one internal rotary wheel having centrifugal blades engaged with said right volute groove and an opening and an internal groove between said first of the at least one internal rotary wheel and multiple through holes between said opening and said internal groove said right rotor also has a first of the at least one external rotary wheel having axial blades and a second of the at least one external rotary wheel having blades disposed in said second right rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades.
14. The turbomachine system of claim 1, wherein said body assembly has a left main port defined by a left inlet port and a left outlet port and a right main port defined by a right inlet port and a right outlet port and a fight electrical device having a right electrical stator and a right electrical rotor, said union has one of plurality of structures including (1) an internal wall having a left set of blades and a right set of blades an external wall and (2) an external wall, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber expanding to a relief hole said right assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and second right rotor chamber, said left body assembly has a first of the at least one fixed wheel having gas injectors extending to an inlet hole, a second of the at least one fixed wheel having multiple blades, a left volute groove between the left outlet port and said first left rotor chamber connected with said left inlet port, said left rotor has a first of the at least one internal rotary wheel having blades defined by a combination of backward centrifugal blades and axial blades having an inside diameter dividing said main left main port into a high power zone and a low power zone, a second of the at least one internal rotary wheel having centrifugal blades engaged with said left volute groove and an opening and an internal groove between said first of the at least one internal rotary wheel and said internal wall and multiple through holes between said opening and said internal groove, said left rotor also has a first of the at least one external rotary wheel having axial blades and a second of the at least one external rotary wheel having blades disposed in said second right rotor chamber sandwiching said second of the at least one fixed wheel having multiple blades, said right body assembly has a first of the at least one fixed wheel having said right electrical stator, a right volute groove between said right outlet port and said first right rotor chamber, said right rotor has a first of the at least one internal rotary wheel having blades defined by a combination of backward centrifugal blades and axial blades having an inside diameter dividing said main right main port into a high power zone and a low power zone, a second of the at least one internal rotary wheel having centrifugal blades engaged with said right volute groove, and an opening and an internal groove between said first of the at least one internal rotary wheel and said internal wall, and multiple through holes between said opening and said internal groove, said right rotor also has a first of the at least one internal rotary wheel having said right electrical rotor engaged with said right electrical stator in said second right rotor chamber.
15. The turbomachine system of claim 1, said union has an internal rotary wheel having blades with an inside diameter to form a high power zone and a low power zone, a front support having at least two link bars and a shaft adapter connected to said external powers.
16. The turbomachine system of claim 1, wherein said body assembly has a main port defined by an inlet port and an outlet port, a heat exchanger, said union has an internal rotary wheel having multiple blades, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a front extension having a fan bore, a first of the at least one fixed wheel having multiple blades with a first segment ring, a second of the at least one fixed wheel having blades with a second segment ring, a third of the at least one fixed wheel having a top pressure storage and a low pressure storage, said first left rotor chamber is defined by a top pressure chamber connected with said top pressure storage and a low pressure chamber connected with said low pressure storage, said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a low power zone, and a first of the at least one external rotary wheel having blades disposed in said fan bore, and at least one set of holes communicating between said main port and said low pressure chamber, said left rotor also has a second of the at least one external rotary wheel having blades with a second edge ring and a second segment ring, a third of the at least one external rotary wheel having blades with an third edge ring and a third segment ring, a fourth of the at least one external rotary wheel having blades with a fourth edge ring and a fourth segment ring, said edge rings have one of plurality structures including one piece structure and multiple pieces structure, said right body assembly has a top burner extending to said top pressure storage and a low burner extending to said low pressure storage and a first of the at least one fixed wheel having at least one set of blades, said right rotor has a first of the at least one internal rotary wheel having blades, a first of the at least one external rotary wheel having at least one set of blades and second of the at least one external rotary wheel having at least one set of blades disposed in said second right rotor chamber respectively sandwiching said first of the at least one fixed wheel having the at least one set of blades, said right body assembly has a back burner having a umbrella cover with multiple through holes and multiple internal fuel injectors and internal multiple igniters as well as multiple external fuel injectors and external multiple igniters in said first right rotor chamber, said umbrella cover is constructed with one of plurality of methods including with said right rotor and with said right body assembly, said heat exchanger is connected to said low burner.
17. The turbomachine system of claim 1, wherein said body assembly has a main port defined by an inlet port and an outlet port, a heat exchanger and an electrical device having an electrical stator and an electrical rotor, said union has an internal rotary wheel having multiple blades and an external wall, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber with said external wall, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber and a second right rotor chamber, said left body assembly has a front extension having a fan bore a first of the at least one fixed wheel having multiple blades with a first segment ring, a second of the at least one fixed wheel having blades with a second segment ring, a third of the at least one fixed wheel having a top pressure storage and a low pressure storage, said first left rotor chamber is defined by a top pressure chamber connected with said top pressure storage and a low pressure chamber connected with said low pressure storage, said right body assembly has a top burner extending to said top pressure storage and a low burner extending to said low pressure storage and a first of the at least one fixed wheel having at least one set of blades said left rotor has a first of the at least one internal rotary wheel having blades with an inside diameter dividing said main port into a high power zone and a low power zone, and a first of the at least one external rotary wheel having blades disposed in said fan bore, and at least one set of holes communicating between said main port and said low pressure chamber said left, rotor also has a second of the at least one external rotary wheel having blades with a second edge ring and a second segment ring, a third of the at least one external rotary wheel having blades with an third edge ring and a third segment ring, a fourth of the at least one external rotary wheel having blades with a fourth edge ring and a fourth segment ring, a fifth of the at least one external rotary wheel having said electrical rotor engaged with said electrical stator in said second left rotor chamber, said right rotor has a first of the at least one internal rotary wheel having blades, a first of the at least one external rotary wheel having at least one set of blades disposed in said second right rotor chamber respectively engaged with said first of the at least one fixed wheel having the at least one set of blades, said right body assembly has a back burner having a umbrella cover with multiple through holes and multiple internal fuel injectors and internal multiple igniters as well as multiple external fuel injectors and external multiple igniters in said first right rotor chamber said umbrella cover is constructed with one of plurality of methods including with said right rotor and with said right body assembly, said heat exchanger is connected to said low burner.
18. The turbomachine system of claim 1, wherein said body assembly has a left electrical device having a left stator and a left electrical rotor and a right electrical device having a right stator and a right electrical rotor, at least two heat exchangers, said union has one of plurality structures including with an internal wall having a left set of blades and a right set of blades and without an internal wall, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber and a third left rotor chamber extending to said left outlet port, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber, a second right rotor chamber and a third right rotor chamber extending to said right outlet port, said left body assembly has a left front extension having a left stator bore, a left outlet port, a left inlet defined by said first left rotor chamber and a left main port, and a left first of the at least one fixed wheel having said left electrical stator disposed in said left stator bore, a left second of the at least one fixed wheel having blades with a second segment ring, a left third of the at least one fixed wheel having blades with a third segment ring, a left fourth of the at least one fixed wheel having a left top pressure storage and a left low pressure storage, a left fifth of the at least one fixed wheel having at least one set of blades disposed in said third left rotor chamber, said first left rotor chamber is defined by a left top pressure chamber extending to said left top pressure storage and a left low pressure chamber extending to said left low pressure storage, said left body assembly also has a left top burner extending to said left top pressure storage and a left low burner extending to said left low pressure storage in said second left rotor chamber, said left rotor has a left first of the at least one internal rotary wheel having blades with an inside diameter dividing said left main port into a high power zone and a low power zone, at least one left set of holes communicating between said left main port and said left low pressure chamber, said left rotor also has a left first of the at least one external rotary wheel having blades, a first edge ring having a set of fan blades and said left electrical rotor engaged with said left electrical stator in said left stator bore, and a first segment ring, a left second of the at least one external rotary wheel having blades, a second edge ring and a second segment ring, a left third of the at least one external rotary wheel having blades, a third edge ring and a third segment ring, a left fourth of the at least one external rotary wheel having at least one set of blades and a left fifth of the at least one external rotary wheel having at least one set of blades sandwiching said left fourth of the at least one fixed wheel having the at least one of set of blades in said third left rotor chamber, said right body assembly has a right front extension having a right stator bore, a right outlet port, and a right inlet defined by said first right rotor chamber and a right main port, a right first of the at least one fixed wheel having said right electrical stator disposed in said right stator bore, a right second of the at least one fixed wheel having a second segment ring a right third of the at least one fixed wheel having blades, a third segment ring, a right fourth of the at least one fixed wheel having a right top pressure storage and a right low pressure storage a right fifth of the at least one fixed wheel having at least one set of blades disposed in said third right rotor chamber, said first right rotor chamber is defined by a right top pressure chamber extending to said right top pressure storage and a right low pressure chamber extending to said right low pressure storage, said right body assembly has a right top burner extending to said right top pressure storage and a right low burner extending to said right low pressure storage in said second right rotor chamber, said right rotor has a right first of the at least one internal rotary wheel having blades with an inside diameter dividing said left main port into a high power zone and a low power zone, at least one right set of holes communicating between said right main port and said right low pressure chamber, said right rotor also has a right first of the at least one external rotary wheel having blades, a first edge ring having a set of fan blades and said right electrical rotor engaged with said right electrical stator in said right stator bore, and a first segment ring, a right second of the at least one external rotary wheel having blades, a second edge ring and a second segment ring, a right third of the at least one external rotary wheel having blades, a third edge ring and a third segment ring, a right fourth of the at least one external rotary wheel having at least one set of blades and a right fifth of the at least one external rotary wheel having at least one set of blades sandwiching said tight fourth of the at least one fixed wheel having the at least one of set of blades in said third right rotor chamber.
19. The turbomachine system of claim 1, wherein said body assembly has a left electrical device having a left stator and a left electrical rotor and a right electrical device having a right stator and a right electrical rotor, and at least two heat exchangers said union has one of plurality structures including having an internal wall having a left set of blades and a right set of blades and having no an internal wall, said left body assembly has a left rotor bore receiving said left rotor to form a first left rotor chamber and a second left rotor chamber extending to said left outlet port, said right body assembly has a right rotor bore receiving said right rotor to form a first right rotor chamber, a second right rotor chamber extending to said right outlet port, said left body assembly has a left front extension having a left stator bore and a left outlet port, a left inlet defined by said first left rotor chamber and a left main port and, a left first of the at least one fixed wheel having said left electrical stator disposed in said left stator bore, a left second of the at least one fixed wheel having blades, a second segment ring, a left third of the at least one fixed wheel having blades, a third segment ring, a left fourth of the at least one fixed wheel having a left top pressure storage and a left low pressure storage respectively extending to said left second rotor chamber said first left rotor chamber is defined by a left top pressure chamber extending to said left top pressure storage and a left low pressure chamber extending to said left low pressure storage, said left rotor has a left first of the at least one internal rotary wheel having blades with an inside diameter dividing said left main port into a high power zone and a low power zone, at least one left set of holes communicating between said left main port and said left low pressure chamfer, said left rotor also has a left first of the at least one external rotary wheel having blades, a first edge ring having a set of fan blades and said left electrical rotor engaged with said left electrical stator in said left stator bore, and a first segment ring, a left second of the at least one external rotary wheel having blades, a second edge ring and a second segment ring, a left third of the at least one external rotary wheel having blades, a third edge ring and a third segment ring, a left fourth of the at least one external rotary wheel having at least one set of blades engaged with said right rotor, said right body assembly has a right front extension having a right stator bore and a right outlet port, a right inlet defined by said first right rotor chamber and a right main port, a right first of the at least one fixed wheel having said right electrical stator disposed in said right stator bore, a right second of the at least one fixed wheel having blades, a second segment ring, a right third of the at least one fixed wheel having blades, a third segment ring, a right fourth of the at least one fixed wheel having a right top pressure storage and a right low pressure storage respectively extending to said right second rotor chamber said first right rotor chamber is defined by a right top pressure chamber extending to said right top pressure storage and a right low pressure chamber extending to said right low pressure storage, said right rotor has a right first of the at least one internal rotary wheel having blades with an inside diameter dividing said left main port into a high power zone and a low power zone, at least one right set of holes communicating between said right main port and said right low pressure chamber, said right rotor also has a right first of the at least one external rotary wheel having blades, a first edge ring having a set of fan blades and said right electrical rotor engaged with said right electrical stator in said right stator bore, and a first segment ring, a right second of the at least one external rotary wheel having blades, a second edge ring and a second segment ring, a right third of the at least one external rotary wheel having blades, a third edge ring and a third segment ring, a right fourth of the at least one external rotary wheel having at least one set of blades engaged with said left rotor in said right second rotor chamber.
20. The turbomachine system of claim 1, said internal gas powers have at least one burner having a front plate having at least one front torus tube extending at least one prep-conditioning torus tube with multiple holes connected to the at least one front torus tube and multiple combustion tubes with at least one layer defined by a large diameter end connected to a post conditioning container and a smaller diameter end connected to the at least one prep-conditioning torus tube said post -conditioning container has multiple injecting holes each of said multiple combustion tubes has a fuel injector and an igniter, said internal gas powers have one of plurality of arrangement of the at least one burner including (1) in-series ways (2) parallel ways (3) a combination of in-series ways and parallel ways.
Description
DRAWINGS
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DESCRIPTION
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[0068] Referring
[0069] Each of the rotors 103,103′ is respectively disposed in the left body assembly 108 and the right body assembly 108′, the union 152 with a set of internal blades 168 supports both the rotors 103,103′ statically to impel incoming flows or dynamically to mix incoming flows, the union 152 is a key for product modulation, each rotors 103,103 housings can be made as standard products, then based on applications, the union 152 can be increased or decreased by the length or inside diameter or outside diameter and constructed as an integral part by welding, press fit gluing or with one or two ball bearings 190 for independent control of the rotors 103,103′ or with a magnetic coupling in a hybrid manner, the union 152 can be made out of different materials form that of the rotors 103,103′, because the thermal difference between the hot gas and cryogenic fluids can cause thermal shock and damage the rotors 103,103′, so the union152 is designed to provide a thermal shelf to prevent the rotors 103,103′ from thermal shock, the left rotor 103 has multiple radial holes 171 and a rotary wheel with blades 167 defined by features of centrifugal blades and axial blades dividing incoming flows in the main port 105 into two flow zones, a high power zone and a lower power zone, the zones are defined by the inside diameter of blade 167.
[0070] Tests for this invention were conducted with a conventional rotor having range of 1 to 12 blades, there are two extreme cases, (1) as the rotor speeds up with the 12 blades, the blades soon become a wall, so there is almost no flow to pass (2) while the rotor speeds up with 0 to 1 blade, there is almost no flow to pass due to lack of converting power from the rotor, why did the rotor cause the two results? because the conventional rotor is designed to add blade angularly so when the rotor speed up, eventually the number of blades would block the flow path, the same problems happen in the wind turbine blades as well as marine propeller blades, moreover if the rotor convert all 100% given power to the flow, then the rotor would stop, so the conventional rotor never reach high efficiency more than 50% to 55%.
[0071] The two zones are radially designed and solve the conventional rotor inherent problem, the high power zone is designed to pass high power flow from a large part of diameter of the blades 167 and more number of blade, which generate more power, some of the incoming flows is impelled up into the first rotor chamber 160 through the radial holes 171, some of the incoming flows is impelled forward in the main port 105 in the low power zone, while the left rotor 103 also has multiple radial holes 171′ and a left rotary wheel with axial blades 153 on an external surface 164 to further impeller the upcoming flow in the first rotor chamber 160, then push back into the main port 105 through the radial holes 171′, then the high velocity flow get back into the low power zone, so a perfect vortical flow is formed between the inlet 104 and the radial holes 171′ as the rotor 103 speeds up with 80% to 90 of input gases power, the pressure gradient is formed between the low power zone and high power zone according to Bernoulli equation, as a result the rotor 103 would suck more flows than the diameter of main port 105, so an inlet adapter from Lox or fuel tank can be much larger, it is also very useful feature in the wind turbine or marine propeller applications, so incoming flows pass the union 152 either with or without a mixer 168 and reach at the right rotor 103′, the whole process repeats again like in the left rotor 103, the incoming flows reach at the first right chamber 160′ through radial holes 171″ as well as the axial holes 152 and are impelled through blades 153′ as well as pass blades 167′, and become a high pressurized and high flow rate outgoing flows, due to the flow streams from radial holes 171′″ at the outlet 104′, so there is no need diffuser unlike centrifugal turbo pump, more powerful feature is that the blades wheel 167 and the blades wheel 167′ can be constructed respectively with left or right or one left and one right, so if the rotor 103 rotor rotates clockwise with the left blades wheel 167, while the rotor 103′ rotates anticlockwise with the right blade wheel 167′, the incoming flows would pass from the inlet 104 to the outlet 104′, if the arrangement is the other way around, then the incoming flows would pass from the outlet 104′ to the inlet 104, why it is so important feature, because it would great reduce noise, vibration and cavitation as well as wake rotation in the downstream, all those inherent problems are related to the conventional turbomachine, specially the wake rotation in downstream is an inherent problem for even the most advanced low noise submarines.
[0072] A seal test for this invention was conducted with a tester having a cylinder bore engaged with a shaft by a radial gap, the tester has an inlet end with a pressurized fluid and a an outlet end (pressure=force/area=force×distance/area×distance=work/volume of the gap=a fluid work density), so we know the leak of flow because the flow does the work, so if the flow does not work, there is no leak!, now we know there are two conditions which cause leak together, a gap and a pressure difference, the test was conducted with the tester having a conical bore engaged with a conical shaft by a radial gap, the shaft is driven by a motor, as the motor speed up or the conical angle increase or the gap reduces, the pressurized fluid would move slower and slower from the inlet to the out let and eventually stop.
[0073] The left rotor 103 has a left wall 159 with a bore 170 between the first left chamber 160 and the second left chamber 162, the right rotor 103′ has a right wall 159′ with a bore 170′ between the first right chamber 160′ and the second right chamber 162′, one of the seal assemblies 180 is disposed between the bore 170′ and a body bore 112′ of the right body assembly 108′, the seal ring assembly 180 has at least one fixed V seal ring 182 with a conical surface 185 and at least one dynamic V seal ring 183 with a mated conical surface 186 engaged with the surface 185 in axial directions for dynamic seals, the fixed V seal ring 182 installed with the seal ring bore 112 of the body assembly 108 with a press fit has a low gap 188 with the step bore 170′ of the right wall 159′, the dynamic V seal ring 183 installed with the right wall 159′ with a press fit has a top gap 187 with the bore 112, the seal ring assembly 180 has at least one groove 184 between the fixed seal ring 182 and the dynamitic seal ring 183 to collect fluid or sealant, in addition, a second of the V seal rings 183,182 can be added to provide spring functions or heat exchange, so as the rotor 103′ rotates, the fixed seal ring 182 stays with the body assembly 108′,while the dynamic seal ring 183 stays with the rotator 103′, there are three factors; centrifugal force, tangential speed, rotational speed with the dynamic V seal ring 183, a speed of OD of seal rings 182,183 is more higher than that of ID of seal ring 182,183, the rotors 103, 103 is defined by X and Y directions, X is an axle of the rotors 103 and 103, the centrifugal force is defined by Y direction, the interface between V wedge rings 182, 183 is defined by an angle from X, as the seal test indicates as the angle change away from Y direction, the leakage gradually stops, so the dynamic V seal ring 183 would not carry fluid without any blade when rotating, while the Fixed V seal rings 182 is stationary, there is no stable gap to be established, moreover the boundary layers of fluid on seal rings 182,183 would remain, as Bernoulli's equation states that higher speed, lower the pressure, so the fluid in the top gap 187 would not go to the low gap 188 due to a negative pressure gradient, while the fluid at the low gap 188 can go to the top gap 187, but it must get through the interfaces between surfaces 185 and 186, there is a little mass of the fluid to be effected by the centrifugal force or fluid pressure, or the fluid can do a little work, as we know the formula (pressure=force/area=force×distance/area×distance=work/volume of the gap), it would not move up, moreover the groove 184 is a fluid equalizer, so even the fluid passing through the low gap 188 would stay at the groove 184 due to fluid surface tension, if the fluid is a gas, then sealant between surfaces 185 and 186 would provide liquid seal as well, sealant can be used for high temperature or cryogenic conditions, so no fluid can leak from top gap 187 to low gap 188 or vice versa, the seal assembly 180 is a positive seal to sustain loads and can be used as a static seal in high vibration applications, while most of spring energized seal ring or shroud seal ring cannot sustain the severe loading even for static seals in high speed or high vibration machines, because they just cannot keep constantly seal contract around 360 degree or pulse dynamic leakage.
[0074] The left body assembly 108 has a bearing bore 110, the left rotor 103 has a step bore 161, the right body assembly 108′ has a bearing bore 110′, the right rotor 103′ has a step bore 161′, the two ball bearings 190 are respectively disposed between the bearing bore 110 and the step bore 161 and between the bearing bore 110′ and the step bore 161′, the ball bearing 190 has a left ring 191 and a right ring 191′ and multiple balls 196, a left wedge insert ring 195 and right wedge insert ring 195′, the left ring 191 has a conical surface 192 and a ball groove 193, the right ring 191′ has a conical surface 192′ and a ball groove 193′, the multiple balls 196 are disposed between ball grooves 193′,193, the left insert ring 195 and the right insert ring 195′ respectively disposed between wedge surfaces 192,192′ have at least one set of round slots to position the balls 196, the insert rings 195,195′ are made out of soft materials including bronze, aluminum, engineering plastics with sealant or grease or the fluid like lox or fuel are placed between left ring and right rings 191,191′, as the twin tubing rotor assembly 150 rotates, insert ring 195,195′ are disposed between the rings 191,191′ to prevent sealant or grease 199 or other fluids from coming out, the seal theory is the similar to seal ring assembly 190, so the ball bearing 190 not only can support radial and axial loads, but also provide seals, additionally because diameter of the step bore 161 is much larger than any shaft diameter, so there are more balls, more contact surfaces to support loads than the conventional ball bearing, the overheat and vibration are eliminated or reduced greatly.
[0075] Referring to
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[0081] Referring
[0082] According to research reports about Shortfin mako shark, Shortfin mako shark can reach speeds as high as 60 mph (96.5 kph), the secret is that two muscles near the two right and left fins generate most of striking forces during attacking, so if a submarine is defined on X,Y Z axis, a front to back of the submarine is located on Y axis, left to right of the submarine is located on X axis, top to bottom of the submarine is located on Z axis, the submarine or marine vehicle can mimic Shortfin mako shark structure, two left and right propellers 100f can be installed near a middle body of a marine vehicle on X axis (a center of gravity with range between 180 to 120 degree apart) which mimic the left and right fins of the shark, they should be installed in front of ballast tanks access ports, two back propellers 100f with top and bottom shaft on Z axis is installed at the back to mimic the tail of the shark, and two back propellers 100f can be wiggled through the control shafts, so this submarine or torpedo would have six freedoms in sea, because two left and right propellers 100f can rotate around X axis about 180 degree, so the submarine can rotate around round X axis about 180 degree clockwise and anticlockwise or more, if the left and right propellers 100f in an opposite directions rotates 180 degree at the same time, then the submarine can rotate around Y axis, if one of two left and right propellers 100f stops, then the submarine can rotate around Z axis, or the back propeller 100f can rotate around Z axis, rest of translations would be much easy, there is no such submarine ever created!!, which would outsmart and out pass Shortfin mako shark!! Finally the propeller wake is a big enemy for submarine stealth function, what is the inherent problem for all propelled submarines or ships, what the propeller 100f does is to cancel out the wakes with a pair of a clockwise wake and anticlockwise wake, and multiple even number of a pair of propellers 100f with left and right blades can be installed at back of submarine in a concentric manner, so they would cancel out the wakes, or with a more brave try, if a submarine has 6 of propellers 100f, each of propellers 100f has 5 speeds selection with the left rotor 103f, 5 speeds selection with the right rotor 103f′, so the combination would be 5*5*6=150 with Fourier transform and AI, the submarine can mimic a moving behavior of any large sea creature and become a part of nature to hide from enemy instead of fighting against nature.
[0083] Referring
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[0086] Referring
[0087] Although the description above contains many specifications, these should not be construed as limiting the scope of the invention but as merely providing illustration of some of the presently preferred embodiments of this invention. Thus, the scope of the invention should be determined by the appended claims and their legal equivalents, rather than by the examples given.
Conclusion and Impact
[0088] First, the shaft less twin rotor turbomachine has the highest power density and efficiency over the conventional turbomachines, if we use the same length and the diameter to design both the conventional turbomachine and this turbomachine, this turbomachine is a clear winner, because the conventional turbomachine is an area base machine, this turbomachine is a volume base machine, so it produces more power, it pass the Betz limit as a power producer, while as a power receiver, it can use up 75 to 95% input power without negative effect, this turbomachine can use up 85% of the converting power, because there is no flow blockage issue at the center lower zone regardless the speed of rotor or number of blades, the peak performance would be obtained in a much easy way with a pair of clockwise rotary gas stream and an anticlockwise rotary gas stream and with the high pressure in the high power zone and high flow rate at the low power zone, this turbomachine fully uses up the total volume from the center thrust bore at low power and high power zone (out power/total turbomachine volume=power density) Second this turbomachine has revolved the fundamental problems the conventional turbomachine faced with and even surpass in all, as the following; [0089] (a) Shaft less design, it profoundly change the history of turbomachinery, from drivetrain to blade designs. First the shaft less design open up the center passage to the top limit and replace the shaft with tubing rotor, second according to the Machinery's Handbook 27th Edition at page 307 Example: A 4-inch shaft, with a 2-inch hole through it, has a weight 25 percent less than a solid 4-inch shaft, but its strength is decreased only 6.25 percent. [0090] (b) Thermal efficiency, for jet engine as an application of the turbomachine, it would be thermodynamically optimized mechanism divides the conventional one cycle into the multiple thermal cycles, includes the high thermal cycle with rotary and thrust output, a middle thermal cycle with rotary and thrust output, and low thermal cycle with thrust output only along with the water cooling device, an energy equalizer, the maximum combination number would be 3×2×1=6, just like a car transmission or conventional multiple spool compressor, the difference is that the thermal engine uses thermal mechanism to generate more power, the rest of the jet engines multiple mechanisms to reduce power, the thermal mechanism is more reliable and efficient, because the heat is transferrable between two thermal systems, while heat in the transmission or the multiple spool compressor cannot be transferred back to the engine, the combination of multiple thermal cycles is so powerful that it can maneuver an aircraft to surpass all current military aircraft capability and make gas turbine or compressor so quiet you never see before!!!, for example as the data shows that the most noise of jet engine comes from the compressor, the burner and the turbine in an order, so in clandestine operations, only the central thrust cycle can operate to minimize the noise without compressor and turbine operation, while for flight jet or air turbulent, high pressure air from high pressure chamber can be redirected to the central thrust bore, since there is no rotary movement, the thrust is much greater with less fuel or in case of low fuel. In addition, the fuel selection is another variable to maneuver the movement, and includes the kerosene, alcohol and hot water to change speed movement by changing the temperature or the intensity of chemical reaction, for the burner on the rocket engine, the modulation of combustion is used for the first time with high thermal efficiency, for the jet engine the entry torus tube receives the compressed hot air then enters the pre conditioning torus tube mixed with fuel and expands, because the entry torus tube is interconnected with pre conditioning torus tube, so the compressed hot air has heat exchange with the pre conditioning torus tube, then goes to the combustion tube with a tap sharp and one layer, expand again, the fuel would never stay on one location rather evenly distribute to each combustion tube, so the hot gas would never go back, then enters the post conditioning container, and expands again and equalize all hot gas to inject into the blades, for rocket engine, the entry torus tube receives Lox and expands, then enters pre conditioning torus for gasification, then enters the combustion tube with a tap sharp with multiple layers, combust with TEA-TEB or fuel, there is heat exchange but one fluid exchange, the hot gas would never go back, because the hot gas expand to the least resistant volume not through multiple layers to the pre conditioning tube, then enter to the post-conditioning container, so multiple concentric burners or cover can be added for high thermal efficiency and safety, which is much lighter, more efficient and safer than the gas generator, the shaft less twin rotor gas turbines and the shaft less twin rotor compressor are other examples with the highest mechanical and thermal efficiency over all existing peer products, the shaft less twin rotor compressor can produce two different compression gases, low pressure gas and high pressure gas, also the chamber front of the high pressure chamber can be connected to the low pressure storage, so the twin rotor compressor become 6 or 8 stage compressor to produce even higher pressures in a very small volume. [0091] (c) Sealability, the seal ring assembly is another achievement, with no existing solution performing not even closed, the robust seal ring assembly is based on the centrifugal mechanism, surface tension, and fluid dynamics, it provides both static seals as well as dynamic seals, for the static seals, when the two V seal rings are fully engaged, there is no fluid to pass through between the V seal rings. For the dynamic seals, as the rotation speed up, there are three factors, centrifugal force, tangential speed, rotational speed with the V seal surface, since there is a little mass of fluid in the engagement surface to move the fluid up, while the tangential speed of the dynamical V seal ring can only carry the fluid around along the conical surface of V seal ring, but since there is no axial force or pressure difference along the V ring seal surfaces, there is no leak, finally in order to move the fluid forward, the solid gap must be established at high speed, because of the surface tension, even little fluid may pass between the V seal rings, the fluid in the pressure equalized slot would hold the little fugitive fluid, it would play a key role in rocket engine turbo-pump. [0092] (d) The reliability is a paramount requirement for all turbomachine, the reliability improvement for the turbomachine include two levels, the system level as well as the component level, at the system level, like the jet engine, the thermal cycles greatly increase reliability with three redundancies, if one fails the other two can still work, especially the central thrust which works without compressor and turbine, other is the single moving like the rotor assembly which greatly increase reliability far more than other measure, at the component level, the rotor blades are no longer the weakest link, the universal bearing are greatly improved in term of load, stress and heat dissipation, like the twin centrifugal turbo pump has the highest reliability. [0093] (e) The universal bearing provides a long sought solution, it not only support radial as well as axial loads but also it is tolerable with clearance due to wedge insert ring, it can seal off and be self-lubricated, more importantly it resolves the inherent problem with small bearing to support large rotor, now because the shaft is replaced by the tubing rotor, so the large bearing has more contact areas, more balls to support the load, so it can sustain high speed under cryogenic or high temperature and be easily installed and replaced under a designed period, the left ring and right can be made out of magnetic material and the assembly become much easier. [0094] (f) The new blade design is a paradigm shift, it changes the blade design order from root-tip to tip-root, as we can see the rotor external blades is no longer the weakest link and rather become more reliable and stronger in the jet engine application or wind turbines, sine the highest torque point is at the largest diameter at the tip, the tip is logically reinforced with the edge rings, as the change with the tubing rotor, the diameter of the blade increase accordingly, since they are wheel based design, as the diameter of the turbomachine increases, the more wheel base modules would be added without redesign of the blade, the most important change is the blade design based on the rotation and torsion not on airplane wind drag and lift, the foundational question for pump designs is based on rpm with centrifugal pump, or on hybrid design with torsion, the centrifugal pump has low efficiency, because the rotary speed of flow is less than the rotary speed of rotor, in most cases, the weight of a fluid in volute is less than that of the rotor of the centrifugal pump, so more than 50% rotary energy is a waste on the rotor not on the flow, so if the centrifugal pump takes 60% of input power like a gas turbine or electrical motor, as a result, only 30% of total input power is used to power the fluid, while the hybrid pump in this invention can take 80 to 95% input power, the rotors here is based on an optimized combination of the rotary speed and torsion of the blades to maximize output flow power with the two power zone with up to 85%, just think about the rocket turbo pump, if the capacity stays the same, the propellant would reduce at 20 to 30% on the pre burners or gas generators. [0095] (g) Cost reduction, because of single moving part design, it greatly reduces the cost of production and assembly, the big cost reduction is contributed to the new blade design, furthermore, the joint method is with two spring pin or coiled pins to secure the edge ring between each modular to replace the complicated root joint design, moreover, other cost reduction is that the three thermal cycle system replace a single thermal cycle system with the multiple spool compressor, finally the burner become simpler and more efficient, these improvements greatly reduce the purchasing cost as well as operation cost, for purchasing cost of the conventional jet engine, most of cost related to the complicated multiple spool compressor, rotor blades joint and burner, shaft, as well as overkilled materials, they are eliminated, so material weights and production time are reduced as well, as far as the operation cost is concerned, if overweigh of engine adding to aircraft. [0096] (h) Maneuverability is a good start of a next generation of turbomachine, it not only increase maneuverability like hybrid gas power and electrical power, independent operation for left rotor and right rotor, three marine propellers for submarine [0097] (i) Scalability with the component modulation like fixed wheels and rotary wheels, combination of the left rotor, right rotor and the union, the Scalability greatly increase, as a result, it not only reduce the cost, but also increase the reliability and the production capability to meet various customers in a short delivery time. [0098] (j) Beyond the limit, this invention bring a disrupt invocation in many grounds from universal ball bearing, high speed seal ring assembly, as well as the simple burner, jet engine, turbo pump, marine propeller, the new ramjet engine, efficiency and reliability on and on, because human has insatiable desire to break their limit, as the history shows us the invention of car to break our leg limit, the invention of telescope to break our eye limit, to invent the fountain. of youth is to break our life span limit, what is the next thing to break our limits or what is next thing to break the limits for wind turbine, wave turbine or tidal turbine? Stay tuned.