AEROSPACE TURBOFAN ENGINES

Abstract

An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.

Claims

1. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet, comprising: an oxygen-enriched gas injection component; a body structure; an afterburner middle portion; and a first afterburner outer ring; wherein the oxygen-enriched gas injection component comprises: an oxygen-enriched gas three-way pipe; an oxygen-enriched gas introduction pipe; an oxygen-enriched gas collector; and an oxygen-enriched gas injection ring; wherein the body structure comprises: an inlet outer wall; a low-pressure compressor; a high-pressure compressor; a primary combustion chamber; a high-pressure turbine; a low-pressure turbine; a central exhaust nozzle; an outer wall of an outer duct; a thickened inner wall of the outer duct; and an outer wall flange of the outer duct; wherein the afterburner middle portion comprises: a nozzle outer wall; a fuel collector; and a fuel introduction pipe; wherein the first afterburner outer ring comprises: an acoustic cavity; a plurality of screw piles; a plurality of nuts; a coolant outflow collector; a coolant eduction pipe; a spiral groove inner wall; a spiral groove outer wall, a coolant inflow collector; a coolant introduction pipe; and a plurality of baffle plates; wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded; a plurality of radial holes configured to inject oxygen-enriched gas into the inlet are formed on the oxygen-enriched gas injection ring and uniformly distributed along a circumference of the oxygen-enriched gas injection ring; the oxygen-enriched gas is composed of oxygen and water vapor and is produced by catalytic decomposition of hydrogen peroxide with a concentration of 70-79%; a plurality of fuel vertical holes are formed on the nozzle outer wall; a plurality of fuel oblique holes are formed on the fuel collector; the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into an afterburner for afterburning; and a plurality of spiral grooves through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall.

2. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously, comprising: an oxygen-enriched gas injection component; a body structure; an afterburner middle portion; and a second afterburner outer ring; wherein the oxygen-enriched gas injection component comprises: an oxygen-enriched gas three-way pipe; an oxygen-enriched gas introduction pipe; an oxygen-enriched gas collector; and an oxygen-enriched gas injection ring; wherein the body structure comprises: an inlet outer wall; a low-pressure compressor; a high-pressure compressor; a primary combustion chamber; a high-pressure turbine; a low-pressure turbine; a central exhaust nozzle; an outer wall of an outer duct; a thickened inner wall of the outer duct; and an outer wall flange of the outer duct; wherein the afterburner middle portion comprises: a nozzle outer wall; a fuel collector; and a fuel introduction pipe; wherein the second afterburner outer ring comprises: an acoustic cavity; a plurality of screw piles; a plurality of nuts; a dual collector; an annular cover plate; an oxygen-enriched gas intake pipe; an oxygen-enriched gas three-way pipe; an angular cover plate; a coolant eduction pipe; a spiral groove inner wall; a spiral groove outer wall; a coolant inflow collector; a coolant intake pipe; and a plurality of baffle plates wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded; a plurality of radial holes configured to inject oxygen-enriched gas into the inlet are formed on the oxygen-enriched gas injection ring and uniformly distributed along a circumference of the oxygen-enriched gas injection ring; a plurality of oxygen-enriched gas holes are formed on the dual collector and uniformly distributed along a circumference of the dual collector; the oxygen-enriched gas is composed of oxygen and water vapor and is produced by catalytic decomposition of hydrogen peroxide with a concentration of 70-79%; a plurality of fuel vertical holes are formed on the nozzle outer wall; a plurality of fuel oblique holes are formed on the fuel collector; the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into the afterburner for afterburning; and a plurality of spiral grooves through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.

3. The aerospace turbofan engine of claim 1, wherein the nozzle outer wall is fitted with the central exhaust nozzle; the plurality of fuel vertical holes are perpendicular to a wall surface of the nozzle outer wall and are uniformly distributed along a circumference of the nozzle outer wall; the plurality of fuel oblique holes have an angle of 10-60 degrees with an axis and are uniformly distributed along a circumference of the fuel collector.

4. The aerospace turbofan engine of claim 2, wherein the nozzle outer wall is fitted with the central exhaust nozzle; the plurality of fuel vertical holes are perpendicular to a wall surface of the nozzle outer wall and are uniformly distributed along a circumference of the nozzle outer wall; the plurality of fuel oblique holes have an angle of 10-60 degrees with an axis and are uniformly distributed along a circumference of the fuel collector; and the plurality of fuel oblique holes and the plurality of oxygen-enriched gas holes together form a gas-liquid injection unit at an included angle of 60-100 degrees.

5. The aerospace turbofan engine of claim 1, wherein a plurality of fanned straight flutes having the same width and arc length as one another are formed on the acoustic cavity and uniformly distributed along the circumference of the acoustic cavity; a plurality of acoustic cavity ribs are arranged between the plurality of fanned straight flutes without regenerative cooling; the plurality of fanned straight flutes include a plurality of deep acoustic cavities and a plurality of shallow acoustic cavities which are in a alternate arrangement with an alternating ratio of 2:1, 1:1 or 1:2; and a plurality of screw pile holes are formed in metal solid portions of the plurality of shallow acoustic cavities.

6. The aerospace turbofan engine of claim 2, wherein a plurality of fanned straight flutes having the same width and arc length as one another are formed on the acoustic cavity and uniformly distributed along the circumference of the acoustic cavity; a plurality of acoustic cavity ribs are arranged between the plurality of fanned straight flutes without regenerative cooling; the plurality of fanned straight flutes include a plurality of deep acoustic cavities and a plurality of shallow acoustic cavities which are in a alternate arrangement with an alternating ratio of 2:1, 1:1 or 1:2; and a plurality of screw pile holes are formed in metal solid portions of the plurality of shallow acoustic cavities.

7. The aerospace turbofan engine of claim 1, wherein the plurality of baffle plates are of high-temperature resistance; and six or more baffle plates are uniformly distributed along the circumference of the first afterburner outer ring and are fixedly welded on inner side surfaces of the acoustic cavity along a direction that the plurality of acoustic cavity ribs extend radially.

8. The aerospace turbofan engine of claim 2, wherein the plurality of baffle plates are of high-temperature resistance; and six or more baffle plates are uniformly distributed along the circumference of the second afterburner outer ring and are fixedly welded on inner side surfaces of the acoustic cavity along a direction that the plurality of acoustic cavity ribs extend radially.

9. The aerospace turbofan engine of claim 1, wherein the spiral groove outer wall upon entire processing is sectioned longitudinally into two symmetrical halves; and the two symmetrical halves are welded into a whole when the two symmetrical halves are fitted in the spiral groove inner wall.

10. The aerospace turbofan engine of claim 2, wherein the spiral groove outer wall upon entire processing is sectioned longitudinally into two symmetrical halves; and the two symmetrical halves are welded into a whole when the two symmetrical halves are fitted in the spiral groove inner wall.

11. The aerospace turbofan engine of claim 1, wherein one way in the oxygen-enriched gas three-way pipe is configured to deliver the oxygen-enriched gas to an air source system of an aircraft.

12. The aerospace turbofan engine of claim 2, wherein one way in the oxygen-enriched gas three-way pipe is configured to deliver the oxygen-enriched gas to an air source system of an aircraft.

13. The aerospace turbofan engine of claim 1, wherein the thickened inner wall of the outer duct of the body structure is welded to the afterburner middle portion; and the outer wall flange of the outer duct of the body structure is threaded with the acoustic cavity.

14. The aerospace turbofan engine of claim 2, wherein the thickened inner wall of the outer duct of the body structure is welded to the afterburner middle portion; and the outer wall flange of the outer duct of the body structure is threaded with the acoustic cavity.

15. An aerospace turbofan engine that introduces no oxygen-enriched gas, comprising: a body structure; an afterburner middle portion; and a first afterburner outer ring; wherein the first afterburner outer ring uses kerosene or liquid hydrogen fuel as a coolant; wherein the body structure comprises: an inlet outer wall; a low-pressure compressor; a high-pressure compressor; a primary combustion chamber; a high-pressure turbine; a low-pressure turbine; a central exhaust nozzle; an outer wall of an outer duct; a thickened inner wall of the outer duct; and an outer wall flange of the outer duct; wherein the afterburner middle portion comprises: a nozzle outer wall; a fuel collector; and a fuel introduction pipe; wherein the first afterburner outer ring comprises: an acoustic cavity; a plurality of screw piles; a plurality of nuts; a coolant outflow collector; a coolant eduction pipe; a spiral groove inner wall; a spiral groove outer wall, a coolant inflow collector; a coolant introduction pipe; and a plurality of baffle plates; wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded; a plurality of fuel vertical holes are formed on the nozzle outer wall; a plurality of fuel oblique holes are formed on the fuel collector; the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into an afterburner for afterburning; and a plurality of spiral grooves through which the kerosene or liquid hydrogen fuel flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.

16. An aerospace turbofan engine that introduces oxygen-enriched gas from an afterburner, comprising: a body structure; an afterburner middle portion; and a second afterburner outer ring; wherein the body structure comprises: an inlet outer wall; a low-pressure compressor; a high-pressure compressor; a primary combustion chamber; a high-pressure turbine; a low-pressure turbine; a central exhaust nozzle; an outer wall of an outer duct; a thickened inner wall of the outer duct; and an outer wall flange of the outer duct; wherein the afterburner middle portion comprises: a nozzle outer wall; a fuel collector; and a fuel introduction pipe; wherein the second afterburner outer ring comprises: an acoustic cavity; a plurality of screw piles; a plurality of nuts; a dual collector; an annular cover plate; an oxygen-enriched gas intake pipe; an oxygen-enriched gas three-way pipe; an angular cover plate; a coolant eduction pipe; a spiral groove inner wall; a spiral groove outer wall; a coolant inflow collector; a coolant intake pipe; and a plurality of baffle plates wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded; a plurality of oxygen-enriched gas holes are formed on the dual collector and uniformly distributed along a circumference of the dual collector; the oxygen-enriched gas is composed of oxygen and water vapor and is produced by catalytic decomposition of hydrogen peroxide with a concentration of 70-79%; a plurality of fuel vertical holes are formed on the nozzle outer wall; a plurality of fuel oblique holes are formed on the fuel collector; the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into the afterburner for afterburning; and a plurality of spiral grooves through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0027] FIG. 1 is a schematic diagram of an aerospace turbofan engine according to a first embodiment.

[0028] FIG. 2 is a schematic diagram of an aerospace turbofan engine according to a second embodiment.

[0029] FIG. 3 is a schematic diagram of an oxygen-enriched gas jet component.

[0030] FIG. 4 is a schematic diagram of a body structure.

[0031] FIG. 5 is a schematic diagram of a first regenerative cooling-type afterburner with acoustic cavity and baffle plates.

[0032] FIG. 6 is a schematic diagram of a second regenerative cooling-type afterburner with acoustic cavity and baffle plates.

[0033] FIG. 7A is a bottom view of an acoustic cavity.

[0034] FIG. 7B is a sectional view taken along A-A line of FIG. 7A.

[0035] FIG. 7C is a sectional view taken along B-B line of FIG. 7A.

DETAILED DESCRIPTION OF EMBODIMENTS

[0036] FIGS. 1-6 and 7A-7C show embodiments of basic aerospace turbofan engines of the first and second embodiments of the present disclosure. Structures of variants of aerospace turbofan engines can also be seen from the figures.

[0037] As shown in FIGS. 1, 3-5 and 7A-7C, in a first embodiment, a basic aerospace turbofan engine (referred to as the first aerospace turbofan engine) that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component 1, a body structure 2, an afterburner middle portion 3 and a first afterburner outer ring 4. The oxygen-enriched gas injection component 1 includes an oxygen-enriched gas three-way pipe 10, an oxygen-enriched gas introduction pipe 11, an oxygen-enriched gas collector 12 and an oxygen-enriched gas injection ring 13. The body structure 2 includes an inlet outer wall 20, a low-pressure compressor 21, a high-pressure compressor 22, a primary combustion chamber 23, a high-pressure turbine 24, a low-pressure turbine 25, a central exhaust nozzle 26, an outer wall 27 of an outer duct, a thickened inner wall 28 of the outer duct, and an outer wall flange 29 of the outer duct. The afterburner middle portion 3 includes a nozzle outer wall 30, a fuel collector 31 and a fuel introduction pipe 32. The first afterburner outer ring 4 includes an acoustic cavity 40, a plurality of screw piles 41, a plurality of nuts 42, a coolant outflow collector 43, a coolant eduction pipe 44, a spiral groove inner wall 45, a spiral groove outer wall 46, a coolant inflow collector 47, a coolant introduction pipe 48, and a plurality of baffle plates 49. All parts except the body structure 2, the plurality of screw piles 41 and the plurality of nuts 42 are fixedly welded. The oxygen-enriched gas injection ring 13 is provided with a plurality of radial holes 14 configured to inject oxygen-enriched gas into an inlet 15 and uniformly distributed along a circumference of the oxygen-enriched gas injection ring 13. The oxygen-enriched gas composed of oxygen and water vapor is a gas produced by catalytic decomposition of hydrogen peroxide with a medium concentration of 70-79%. The nozzle outer wall 30 and the fuel collector 31 are provided with a plurality of fuel vertical holes 33 and a plurality of fuel oblique holes 34 which are configured to inject kerosene or liquid hydrogen fuel into the afterburner 50. A plurality of spiral grooves 51 through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on the outer surface of the spiral groove inner wall 45. The spiral groove inner wall 45 is brazed together with the spiral groove outer wall 46 into a whole.

[0038] As shown in FIGS. 2-4, 6 and 7A-7C, in a second embodiment, a basic aerospace turbofan engine (referred to as the second aerospace turbofan engine) that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously. The second aerospace turbofan engine includes an oxygen-enriched gas injection component 1, a body structure 2, an afterburner middle portion 3 and a second afterburner outer ring 5. The oxygen-enriched gas injection component 1 includes an oxygen-enriched gas three-way pipe 10, an oxygen-enriched gas introduction pipe 11, an oxygen-enriched gas collector 12 and an oxygen-enriched gas injection ring 13. The body structure 2 includes an inlet outer wall 20, a low-pressure compressor 21, a high-pressure compressor 22, a primary combustion chamber 23, a high-pressure turbine 24, a low-pressure turbine 25, a central exhaust nozzle 26, an outer wall 27 of an outer duct, a thickened inner wall 28 of the outer duct and an outer wall flange 29 of the outer duct. The afterburner middle portion 3 includes a nozzle outer wall 30, a fuel collector 31 and a fuel introduction pipe 32. The second afterburner outer ring 5 includes an acoustic cavity 40, a plurality of screw piles 41, a plurality of nuts 42, a dual collector 52, an annular cover plate 53, an oxygen-enriched gas introduction pipe 11, an oxygen-enriched gas three-way pipe 10, an angular cover plate 54, a coolant eduction pipe 44, a spiral groove inner wall 45, a spiral groove outer wall 46, a coolant inflow collector 47, a coolant introduction pipe 48, and a plurality of baffle plates 49. All parts except the body structure 2, the a plurality of screw piles 41 and the a plurality of nuts 42 are fixedly welded. The oxygen-enriched gas injection ring 13 is provided with a plurality of radial holes 14 configured to inject oxygen-enriched gas into the inlet 15 and uniformly distributed along the circumference of the oxygen-enriched gas injection ring 13. The dual collector 52 is provided with a plurality of oxygen-enriched gas holes 55 configured to inject the oxygen-enriched gas into the afterburner 50 and uniformly distributed along a circumference of the dual collector 52. The oxygen-enriched gas composed of oxygen and water vapor is a gas produced by catalytic decomposition of hydrogen peroxide with a medium concentration of 70-79%. The nozzle outer wall 30 and the fuel collector 31 are provided with the plurality of fuel vertical holes 33 and the plurality of fuel oblique holes 34 which are configured to inject kerosene or liquid hydrogen fuel into the afterburner 50. The plurality of spiral grooves 51 through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on the outer surface of the spiral groove inner wall 45. The spiral groove inner wall 45 is brazed together with the spiral groove outer wall 46 into a whole.

[0039] As shown in FIG. 4, for the basic aerospace turbofan engines, the body structure 2 has been modified slightly as compared to the body of the existing aero turbofan engine, and further provided with the thickened inner wall 28 of the outer duct and the outer wall flange 29 of the outer duct. The thickened inner wall 28 of the outer duct is integrally welded with the afterburner middle portion 3. The outer wall flange 29 of the outer duct is integrally threaded to the acoustic cavity 40.

[0040] As shown in FIGS. 5-6, for the basic aerospace turbofan engines, the nozzle outer wall 30 is fitted with the central exhaust nozzle 26, and is provided with the plurality of fuel vertical holes 33 which are perpendicular to the nozzle outer wall 30 and have different diameters. The fuel collector 31 is provided with the plurality of fuel oblique holes 34 which have an angle of 10-60 degrees with an axis. The plurality of fuel vertical holes 33 are uniformly distributed along a circumference of the nozzle outer wall 30. The plurality of fuel oblique holes 34 are uniformly distributed along a circumference of the fuel collector 31. The plurality of fuel oblique holes 34 and the plurality of oxygen-enriched gas holes 55 form a gas-liquid injection unit at an angle of 60-100 degrees.

[0041] As shown in FIGS. 5-7, for the basic aerospace turbofan engines, the acoustic cavity 40 are provided with a plurality of fanned straight flutes which are uniformly distributed along a circumference of the first afterburner outer ring 4 and the second afterburner outer ring 5. The plurality of fanned straight flutes have the same width and arc length as one another. A plurality of acoustic cavity ribs 56 which do not conduct regenerative cooling are arranged between the plurality of fanned straight flutes. The fanned straight flutes include a plurality of deep acoustic cavities 57 and a plurality of shallow acoustic cavities 58 which are in an alternate arrangement at an alternating ratio of 2:1, 1:1 or 1:2. A plurality of screw pile holes 59 are formed in metal solid portions of the shallow acoustic cavities 58.

[0042] As shown in FIGS. 5-7, for the basic aerospace turbofan engines, the plurality of baffle plates 49 is of high-temperature resistance. Six or more baffle plates 49 are uniformly distributed along the circumference of the first afterburner outer ring 4 and the second afterburner outer ring 5 and are fixedly welded on the inner side surface of the acoustic cavity 40 along a direction that acoustic cavity ribs 56 extend radially.

[0043] As shown in FIGS. 5-6, for the basic aerospace turbofan engines, the spiral groove outer wall 46 upon entire processing is sectioned longitudinally into two symmetrical halves. The two symmetrical halves are welded into a whole when fitted in the spiral groove inner wall 45.

[0044] As shown in FIGS. 1-3 and 6, for the basic aerospace turbofan engines, one way in the oxygen-enriched gas three-way pipe 10 is configured to deliver the oxygen-enriched gas into an air source system of the aircraft.

[0045] As shown in FIGS. 1, 4, 5 and 7A-7C, a variant of the first aerospace turbofan engine (referred to as the third aerospace turbofan engine) is designed and obtained by removing the oxygen-enriched gas jet component from the first aerospace turbofan engine. The third aerospace turbofan engine includes a body structure 2, an afterburner middle portion 3 and a first afterburner outer ring 4. Such aerospace turbofan engine introduces no oxygen-enriched gas. The first afterburner outer ring 4 uses the kerosene or liquid hydrogen fuel as coolant.

[0046] As shown in FIGS. 2, 4, 6 and 7A-7C, a variant of the second aerospace turbofan engine (referred to as the fourth aerospace turbofan engine) is designed and obtained by removing the oxygen-enriched gas jet component from the second aerospace turbofan engine. The fourth aerospace turbofan engine includes a body structure 2, an afterburner middle portion 3 and a second afterburner outer ring 5. Such aerospace turbofan engine, also called a tandem turbine-rocket combined engine, introduces oxygen-enriched gas from the afterburner.