Abstract
An electronically speed controlled pulsed supersonic turbine engine powering automotive, drone and electric power generation, energised by breathable, clean renewable energy airflow from 2700 psi integral air-tank energising the engine continuously for 3 hours, replacing the toxic fossil gasoline-diesel energised internal combustion engine with carbon emissions that affects climate change. The turbine blades are turning by pulsed impulse of supersonic airflow from sequentially energised eight manifolds of de Laval convergence-divergence-CD with sonic choking nozzle and supersonic divergence airflow impulsing turbine blades turning them within divergence shroud to atmospheric pressure with turbine nose with engine output shaft supported with bearings supported by the air-tank. An electric pulse generator controls engine shaft speed with voltage pulses to solenoid valves commanding spool valves with airflow from the air-tank with output shaft magnetic speed sensing signal sent back to controller in closed loop adjusting to desired set with pulse amplitude and time duration.
Claims
1. An electronically speed controlled pulsed supersonic turbine engine energised by a clean breathable air from an extremely high pressure renewable energy air stored in mobile air-tank with outlet shaft coupled with automotive input power, or coupled with generator input shaft, with outlet shaft speed controlled in closed loop using electronically controlled pulse generator controller set to predetermined engine output shaft speed, sending short time electrical voltage pulses to fast-opening solenoid valve and spool valve assembly in the programmable amplitude, frequency, sequence and time duration, comprising: a. A large cylindrical air-tank with front flange and cylindrical extension in the rear with through centre-hole, thereby storing large amount of extremely high-pressure air, supporting an output shaft bearings and turbine bearings and supporting turbine and the output shaft rotation, comprising, 1. air-tank centre hole thereby supporting engine output shaft beaings and outlet shaft rotation within said centre hole with non-magnetic ring, and 2. an air-tank relief valve thereby preventing air overpressure in said extremely high-pressure air tank, and 3. a air-tank front end flange thereby supporting bolted magnetic sensor and electronic pulse generator and connecting with bolts to said automotive structural chassis, supporting engine to the chassis, and 4. air-tank Inlet port with high pressure shutoff valve, thereby controlling charging of the air-tank with extremely high pressure air from auxilliary high capacity external air-tank, and 5. eight air-tank outlet ports thereby said connecting pipes connected to eight control solenoid valves, controlling the airflow to the engine, and 6. air-tank rear cylindrical extension, thereby supporting turbine bearings, and b. eight De Laval convergent-divergent CD nozzle systems, each connected to a solenoid valve and spool valve assembly, thereby high pressure air from air-tank is provided to each at sequential timing, each comprising: 1. a convergent manifold chamber connecting between the spool valve outlet port and the choking nozzle, whereas the high pressure convergnce manifold chamber airflow is at subsonic speed, and 2. a choked nozzle with precision diameter connecting between the convergence manifold chamber and downstream to the divergence manifold chamber, whereas airflow speed through the choking nozzle is kept at sonic M=1 at speed of sound, and 3. a divergence manifold chamber connecting between the choking nozzle and turbine outer shroud flow adaptor wherein airflow speed is accelerating to supersonic with Mach number larger than 1 when leaving the choking nozzle, while being limited to M=1.2 to avoid shock, and c. a solenoid valve with inlet port connected to said air-tank and with outlet port connected to the spool valve command port, whereas the solenoid actuated by electric voltage pulse is a fast-opening and is connected to the command port of the spool valve, comprising: 1. a fast-opening magnetic solenoid energised by short duration voltage pulses from a pulse generator thereby opening said valve for a very short time, flowing to command port of the spool valve, and 2. a solenoid plunger with a conical poppet sealing surface, thereby the conical poppet provides a tight seal against the sealing seat, and 3. a solenoid valve body with an inlet port connected to said tank air and with an outlet port connected to spool valve command port, and, 4. a solenoid valve helical spring, thereby said helical spring pushes said solenoid plunger to move to closed position, keeping valve in a sealed closed position when solenoid in not energised, and 5. a solenoid valve inlet port connected to said air tank, and 6. a solenoid valve outlet port connected to said spool valve command port thereby when solenoid valve in open position, it provide pressurised air to spool valve command port to move said spool valve cylindrical spool to open position, and e. a spool valve with command port connected to the solenoid valve outlet inlet port connected to air tank and outlet port connected to said convergence chamber manifold, comprising: 1. a spool valve body with a spool valve bore, spool valve command port inlet, spool valve command port outlet, spool valve inlet port and spool valve outlet port, comprising 2. a spool valve cylindrical spool with axial centre through hole, wherein said spool is sliding axially inside said spool bore to open position under command port pulse pressure from said solenoid valve outlet port, and 3. a spool valve helical return spring between said spool and said bottom cover of said spool bore, thereby said spring applying axial force on said cylindrical spool, pushing it back to closed position, and 4. a spool valve inlet command port connected axially into said spool bore upper side and to the outlet port of said solenoid control valve, thereby applying a fast short duration pressurised air axial force on upper side of the spool valve cylindrical spool for a rapid move to spool valve open position, and, 5. a spool valve inlet port connected to said air tank connecting pipe, thereby connected to the high pressure source air-tank, and, 6. a spool valve outlet port connected to said convergence manifold chamber, whereas the spool valve providing high pressure air flow at open position into convergence manifold chamber at subsonic speed, and f. 16 turbine blades with an helical pattern bolted around the inner shroud and nose assembly with close radial proximity to an turbine outer shroud, whereas said turbine blades are turning under supersonic airflow speed impulse converting airflow speed to turbine rotation at a controlled speed with said nose is coupled with said output shaft to transfer turbine rotary motion to output shaft, and g. a turbine inner shroud and nose assembly with multiple radial inner fins bolted to to engine outlet power shaft and supporting turbine ball bearing outer diameter, whereas the turbine ball bearing inner diameter is mounted to air-tank rear cylindrical extension, and turbine rotation speed is same as output shaft rotation speed, and h. a turbine outer shroud flow adaptor bolted to divergence manifold chamber outer diameter and to turbine divergence shroud, and i. a turbine divergence shroud bolted to the turbine outer shroud flow adaptor, wherein airflow exiting turbine blades at low ambient atmosphere pressure, and j. an electronic pulse generator speed control system of the engine output shaft, whereas the engine output shaft speed is controlled in a closed loop by electronic pulse generator controller and engine out shaft speed sensor with non-magnetic ring with embedded magnets mounting on the engine output shaft, comprising: 1. a non-magnetic ring with embedded magnets bolted radially to the engine outlet shaft, thereby the non-magnet ring with embedded magnets rotates at the same speed of the engine output shaft while in close proximity to the magnetic sensor 2. a magnetic sensor bolted to the air tank front flange, wherein the magnetic sensor includes reed switch that produces electrical signal to the electronic pulse gnerator when a rotating magnet of the non-magnetic ring with embedded magnets is passing in close proximity and 3. an electronic pulse generator controller bolted to the air-tank front flange, wherein said pulse generator controller is programmable to produce an electrical voltage pulses of predetermined amplitude, time duration, frequency and synchronisation between the solenoid valves 4. reed switches sensors that are bolted to said air tank front flange, thereby producing electrical signal for controlling the speed of said output shaft in closed loop.
Description
BRIEF SUMMARY OF THE DRAWINGS
[0022] FIG. 1 presents the top view of a Electronically speed controlled pulsed supersonic turbine engine installed in automotive application
[0023] FIG. 1A presents the side view of a Electronically speed controlled pulsed supersonic turbine engine installed in automotive application
[0024] FIG. 1B presents the top view of a Electronically speed controlled pulsed supersonic turbine engine installed in electrical power generator application
[0025] FIG. 2 presents the top view of a Electronically speed controlled pulsed supersonic turbine engine
[0026] FIG. 2A presents the front view of a Electronically speed controlled pulsed supersonic turbine engine
[0027] FIG. 2B presents the back view of a Electronically speed controlled pulsed supersonic turbine engine
[0028] FIG. 2C presents the top view of a Electronically speed controlled pulsed supersonic turbine engine
[0029] FIG. 3 presents the air-tank of high- pressure air
[0030] FIG. 4 presents the engine output shaft rotating within said centre hole with magnet ring
[0031] FIG. 5 presents the air-tank relief valve of the air tank
[0032] FIG. 6 presents the air-tank front end flange bolted automotive structural chassis
[0033] FIG. 7 presents an air-tank Inlet port with high pressure gas shutoff valve,
[0034] FIG. 8 presents eight air-tank outlet ports connected to eight control solenoid valves
[0035] FIG. 9 presents two turbine ball bearings mounted on the inner shroud
[0036] FIG. 10 presents an air-tank front flange supporting a magnetic speed sensor
[0037] FIG. 11 presents eight supersonic airflow convergent-divergent manifolds each equipped with flow control solenoid valve
[0038] FIG. 12 presents a high pressure gas flow inlet convergent manifold chamber
[0039] FIG. 13 presents a fast-opening pulse energised solenoid valve
[0040] FIG. 14 presents a fast-opening solenoid coil energised by short duration voltage pulses from an electronic pulse generator
[0041] FIG. 15 presents a pressure-balanced solenoid valve plunger
[0042] FIG. 16 presents a solenoid valve body with an solenoid valve air inlet port
[0043] FIG. 17 presents a helical spring pushing the solenoid valve plunger
[0044] FIG. 18 pesents a solenoid valve inlet port with air-tank connecting pipe.
[0045] FIG. 19 presents an solenoid valve outlet port connected the spool valve
[0046] FIG. 20 presents a pressure-commanded spool valve
[0047] FIG. 21 presents a spool valve body with a spool valve bore
[0048] FIG. 22 presents a spool valve cylindrical spool with a cylindrical spool lateral circular through hole
[0049] FIG. 23 presents a spool valve helical return spring between the spool valve cylindrical spool and spool valve bottom cover
[0050] FIG. 24 presents the spool valve inlet command port connected into the spool valve bore
[0051] FIG. 25 presents the spool valve inlet airflow port connected to the air tank outlet port
[0052] FIG. 26 presents the spool valve outlet port connected to the convergence manifold chamber
[0053] FIG. 27 presents the convergence manifold chamber connected to the spool valve outlet port
[0054] FIG. 28 presents a choked sonic airflow in the choking nozzle
[0055] FIG. 29 presents the divergence manifold chamber
[0056] FIG. 30 presents the turbine blades and inner shroud assembly
[0057] FIG. 31 presents the turbine blades turning under supersonic airflow speed impulse,
[0058] FIG. 32 presents a turbine aerodynamically rounded turbine nose with multiple radial turbine nose radical fins
[0059] FIG. 33 presents the turbine outer shroud flow adaptor bolted to the divergence manifold chamber outlet diameter,
[0060] FIG. 34 presents the turbine divergence shroud bolted to outer shroud
[0061] FIG. 35 presents an electronic pulse generator bolted to air-tank front flange
[0062] FIG. 36 presents a multiple ring magnets mounted radially on a non-magnetic ring
[0063] FIG. 37 presents a reed switch sensor bolted to said air-tank front flange.
[0064] FIG. 38 presents a sample graph presenting pulses provided to manifolds numbered as #1& #5, #2& #6, #3 & #7 and #4 & #8
DETAILED DESCRIPTION OF THE DRAWINGS
[0065] An Electronically speed controlled pulsed supersonic turbine engine 56 energised by a clean breathable air from an extremely high pressure renewable energy air stored in mobile air-tank 12 with engine outlet shaft 11 coupled with automotive input power, or coupled with generator input shaft, with outlet shaft 11 speed controlled in closed loop using electronically controlled pulse generator controller set to predetermined engine output shaft speed, sending short time electrical voltage pulses to fast-opening solenoid valve and spool valve assembly 16 in the programmable amplitude, frequency, sequence and time duration, FIG. 1, FIG. 1A, and FIG. 1B present a top, back and a front views respectively of an electronically speed controlled pulsed supersonic turbine engine 56 for automotive input power 51 energised by a clean renewable energy from an extremely high pressure air stored in mobile air-tank 11 with outlet shaft coupled with automotive input power with outlet shaft speed control
[0066] FIG. 2, FIG. 2A, FIG. 2B and FIG. 2C present a top and a front views respectively of an electronically speed controlled pulsed supersonic turbine engine 56 for electric power for electrical energy generation energised by a clean renewable energy from an extremely high pressure air stored in mobile air-tank 12 with outlet shaft 11 coupled with electrical power generator input shaft 52, with outlet shaft speed control using electronically controlled pulse generator controller 43 creating short time pulses that actuate sequentually fast opening solenoid valves 14 in the predetermined amplitude, sequence and time duration.
[0067] FIG. 3 presents a large internal air-tank 12 storing large amounts of extremely high-pressure air, with through centre-hole 12c, supporting an output shaft 11, and extended to support turbine rotating inner shroud with turbine bearings 48.
[0068] FIG. 4 presents an engine output shaft rotating within said centre hole with magnets embedded in non-magnet ring 45, supported to said air-tank with two ball bearings 13 one at each end, thereby supporting said rotating engine output shaft 11 and sensing its rotating speed.
[0069] FIG. 5 presents an air-tank relief valve 12d to prevent air overpressure in said extremely high-pressure air tank 12.
[0070] FIG. 6 presents an air-tank front end flange 12a bolted to said automotive structural chassis 53 or said electric power generator chassis 54, thereby supporting the engine to the chassis.
[0071] FIG. 7 presents an air-tank Inlet port 12e with high pressure gas shutoff valve, thereby controlling charging of the air-tank with extremely high pressure air from auxilliary high capacity external air-tank 55.
[0072] FIG. 8 presents eight air-tank outlet relief valve 12d and air-tank connecting pipe 12e connected to eight control solenoid valves 14 operated by electrical voltage pulse of controlled time duration, voltage and sequence
[0073] FIG. 9 presents two turbine ball bearings 48 mounted on the inner shroud 34 with outer diameter supported by said air-tank centre hole 12c.
[0074] FIG. 10 presents an air-tank front flange 12a supporting a magnetic speed sensor 46 thereby sensing magnet signal from the magnet ring attached to said output shaft 11.
[0075] FIG. 11 presents eight supersonic airflow convergent-divergent manifolds 30 each equipped with flow control solenoid valve 14 and spool valve inlet port 18 connected to said high pressure tank air connecting pipe 12e.
[0076] FIG. 12 presents a high pressure gas flow inlet convergent manifold chamber 31 of high-pressure with subsonic airflow speed funnelled into with a choked flow nozzle 32 with sonic flow and then divergent manifold chamber 33 with supersonic airflow.
[0077] FIG. 13 presents a fast-opening pulse energised solenoid valve 14 with solenoid valve inlet port 28 connected to said air-tank outlet port 12e, controlling extremely high-pressure gas flow into the spool valve command inlet port 21.
[0078] FIG. 14 presents a fast-opening solenoid coil 23 energised by short duration voltage pulses from an electronic pulse generator 43 thereby opening said valve for a very short time flow to spool valve inlet port 18.
[0079] FIG. 15 presents a pressure-balanced solenoid valve plunger 25 with a conical poppet sealing surface, thereby providing tight seal against solenoid valve seal seat 27 at balanced forces condition.
[0080] FIG. 16 presents a solenoid valve body 24 with an solenoid valve air inlet port 28 connected to said tank air connecting pipe 12d, outlet port connected to pilot valve inlet port, a solenoid support flange, a radial seal seat 27 and an solenoid valve electrical connector 23a said solenoid valve plunger 16 with a centre-hole and with radial seal rings, whereas said plunger poppet 25a creates a tight seal when engages said ring seal, and is pushed by solenoid armature 25b under electrical pulse, moving away from engagement with said seal seat 27, allowing full-airflow to the spool valve command inlet port 21.
[0081] FIG. 17 presents a helical spring 26 pushing said pressure-balanced plunger 25 to move to solenoid valve no-airflow sealed position, thereby keeping the valve at the no-airflow sealed position when solenoid is not energised.
[0082] FIG. 18 pesents a solenoid valve inlet port 28 with air-tank connecting pipe 12e and air-tank shutoff valve 41 and air-tank relief valve 12d connected to air tank 12.
[0083] FIG. 19 presents an solenoid valve outlet port 29 connected to said spool valve command inlet port 21 thereby actuating said spool valve cylindrical spool 16 by pushing the spool to full-airflow position.
[0084] FIG. 20 presents a pressure-commanded spool valve 15 connecting extremely high-pressure gas from said air-tank connecting pipe 12d into said convergence manifold chamber 31.
[0085] FIG. 21 presents a spool valve body 24 with a spool valve bore 17a, with a spool valve spring cover 15b and with a spool valve command port cover 15a, whereas the bottom cover supporting a spool valve return spring 22 pushing the spool to sealed no flow position and said spool valve bore 17a is pressurised under spool valve top cover 15a pushing spool valve cylindrical spool 16 to full airflow position.
[0086] FIG. 22 presents a spool valve cylindrical spool 16 with a cylindrical spool lateral circular through hole 16a in its centre, wherein the spool valve cylindrical spool is sliding axially inside the spool valve spool bore 17a to open full airflow position under command of a pulsed pressurised air from the solenoid valve outlet port 19 into the spool valve bore 17a under the spool valve top cover 15a.
[0087] FIG. 23 presents a spool valve helical return spring 22 between the spool valve cylindrical spool 16 and spool valve bottom cover 15b, thereby said spring applying axial force on the cylindrical spool, pushing it back to sealed-no airflow position.
[0088] FIG. 24 presents the spool valve inlet command port 20 connected into the spool valve bore 17a top side connected to the solenoid valve outlet port 29, thereby applying a fast short duration pressurised air pulse axially on the top side of said spool valve cylindrical spool 16 causing a rapid movement to full-airflow position.
[0089] FIG. 25 presents the spool valve inlet airflow port 18 connected to the air tank outlet port 12f at spool valve 15 full-airflow through the spool valve circular spool lateral through hole 16a to convergence manifold chamber 31.
[0090] FIG. 26 presents the spool valve outlet port 19 connected to the convergence manifold chamber 31. When the spool valve is in full-airflow position, the high pressure airflow at subsonic speed flows into convergence manifold chamber 31.
[0091] FIG. 27 presents the convergence manifold chamber 31 connected to the spool valve outlet port 19. The Subsonic airflow in the convergence manifold chamber is funnelled into a choking nozzle 32 sonic airflow.
[0092] FIG. 28 presents a choked sonic airflow in the choking nozzle 32 through a controlled precision tapered diameter where airflow speed is kept at speed of sound. The airflow is then accelerated into a larger diameter divergence manifold chamber 33.
[0093] FIG. 29 presents the divergence manifold chamber 33 where airflow speed increases to supersonic with Mach number larger than 1, while being limited to M=1.2 to avoid the creation of a lateral shock wave.
[0094] FIG. 30 presents the turbine blades and inner shroud assembly 35 including 16 turbine blades 37 with aerodynamic cross section and with helical pattern that is bolted to the inner shroud. The turbine inner shroud 34 is bolted to the nose 36 creating inner shroud and nose assembly 38 which rotates with close radial proximity to turbine outer shroud 34a that is bolted to the divergence manifold flow adaptor 34c.
[0095] FIG. 31 presents the turbine blades 37 turning under supersonic airflow speed impulse, converting airflow speed kinetic energy into turbine blades and inner shroud 35 fast rotation over turbine ball bearings 45 mounted to air-tank rear turbine support 12b.
[0096] FIG. 32 presents a turbine aerodynamically rounded nose 36 with multiple radial turbine nose radical fins 36a. bolted to inner shroud 34 and bolted to the end of engine outlet shaft 11, making turbine rotation speed same as engine output shaft rotation speed with inner shroud and nose assembly 37 turning around the turbine bearings 45 supported by air-tank rear turbine support 12b.
[0097] FIG. 33 presents the turbine outer shroud flow adaptor 33a bolted to the divergence manifold chamber outlet diameter, funnelling the supersonic airflow into the turbine outer shroud 34a. ,
[0098] FIG. 34 presents the turbine divergence shroud 39 bolted to outer shroud 34a, wherein airflow exiting turbine blades at subsonic speed, low temperature and low pressure into the ambient atmosphere.
[0099] FIG. 35 presents an electronic pulse generator 43 bolted to air-tank front flange 12a, controlling the. speed of engine output shaft 11 in a closed loop by providing .controlled rectangular short duration pulses varying in voltage, time duration and sequence to two opposing manifolds of the total eight number of manifolds numbered as #1& #5, #2& #6, #3 & #7 and #4 & #8 at a time.
[0100] FIG. 36 presents a multiple magnets 47 mounted radially on a non-magnetic ring 49 bolted concentrically to said outlet shaft 11, thereby the non-magnet ring rotates at shaft speed in close proximity to said magnetic reed switches sensors that are bolted to said air tank front flange, thereby producing electrical signal for controlling the speed of said output shaft in closed loop
[0101] FIG. 37 presents a reed switch sensor 46 bolted to said air-tank front flange 12a. The reed switch produces electrical output signal proportional to output shaft speed to the electronic pulse generator 43 when a rotating magnet embedded non-magnetic ring 47 is passing in their proximity to the non-magnetic ring reed switch.
[0102] FIG. 38 presents a sample graph presenting pulses provided to manifolds numbered as #1& #5, #2& #6, #3 & #7 and #4 & #8 by electronic pulse generator 43. The engine output speed is controlled by providing controlled rectangular short duration pulses varying in voltage, time duration and sequence to two opposing manifolds of the total eight at a time.
