CN105736178B - Combined cycle engine - Google Patents
Combined cycle engine Download PDFInfo
- Publication number
- CN105736178B CN105736178B CN201610222011.3A CN201610222011A CN105736178B CN 105736178 B CN105736178 B CN 105736178B CN 201610222011 A CN201610222011 A CN 201610222011A CN 105736178 B CN105736178 B CN 105736178B
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- gas
- shell
- engine
- turbojet
- supersonic speed
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Abstract
The present invention provides a kind of combined cycle engine, including：Supersonic speed admission gear has the first gas inlet open vertically connected with outside；Continuous rotation detonation engine is fixedly connected on the downstream of supersonic speed admission gear；And turbojet, it is fixedly connected on the downstream of supersonic speed admission gear.Wherein, continuously rotation detonation engine and turbojet with supersonic speed admission gear it is controlled connect with via first gas inlet it is controlled introducing extraneous gas and work.The present invention combined cycle engine mode conversion can be completed in the range of operating envelope, provide steady propulsion for aircraft, so make aircraft endoatmosphere realize 5.0 Mach or more hypersonic flight and can horizontal take-off land.In addition, based on continuous rotation pinking technology is employed, engine/motor specific impulse is improved, improves the thermal efficiency of burning, and improves the economy and reliability of engine.
Description
Technical field
The present invention relates to aerospace power technology field more particularly to a kind of combined cycle engines.
Background technology
Highest flying speed possesses superior high-altitude at a high speed in the near space hypersonic vehicle of Mach number 5.0 or so
The advantages such as characteristic, flexible mobility, higher penetraton probability have highly important potential military value.In addition, with leading
The progress of defense technique is played, the prominent anti-and survival ability of traditional guided missile is also greatly threatened, is badly in need of filling by propelled at high velocity
It puts to improve mobility.However, the aircraft of this type has the characteristics that operating envelope is wide, flight operating mode is complicated and changeable, it is single
The propulsion device of one type is difficult to complete independently whole job requirement, and therefore, assembly power technology is come into being, and is caused rapidly
The concern of people.It is rocket punching press combined cycle engine and turboram to study two more class combined cycle engines at present
Combined cycle engine, the former is less economical because of oxygen in air is not efficiently used, and is difficult to meet repetition at present and makes
It is required that and for the latter, it is maximum the problem of be mode conversion, the highest work Mach number of turbogenerator is less than punching press
Effective Start mach number of engine, during so as to cause combined engine from turbine mode to punching press mode conversion, thrust can not
It meets the requirements.
The content of the invention
In view of problem present in background technology, it is an object of the present invention to provide a kind of combined cycle engine,
It can smoothly complete mode conversion in the range of operating envelope, provide steady propulsion for aircraft, and then make aircraft in air
Layer in realize 5.0 Mach or more hypersonic flight and can horizontal take-off landing.
It is another object of the present invention to provide a kind of combined cycle engines, and which raises engine/motor specific impulses, solve
The problem of combustion instability, and then the thermal efficiency of burning is improved, and improve the economy and reliability of engine.
To achieve these goals, the present invention provides a kind of combined cycle engine, including：Supersonic speed is into mechanism of qi
Structure has the first gas inlet open vertically connected with outside；Continuous rotation detonation engine, is fixedly connected on Supersonic
The downstream of fast admission gear；And turbojet, it is fixedly connected on the downstream of supersonic speed admission gear.Wherein, continuously
Rotation detonation engine and turbojet with supersonic speed admission gear it is controlled connect with via first gas inlet by
Control introduces extraneous gas and works.
Beneficial effects of the present invention are as follows：
In combined cycle engine according to the present invention, it is continuous rotate detonation engine and turbojet with
The controlled connection of supersonic speed admission gear turns so as to smoothly complete mode in the range of the operating envelope of combined cycle engine
Change, steady propulsion provided for aircraft, so make aircraft endoatmosphere realize 5.0 Mach or more hypersonic flight and
It being capable of horizontal take-off landing.In addition, employing continuous rotation pinking technology based on continuous rotation detonation engine, improve and start
Machine specific impulse solves the problems, such as combustion instability, and then improves the thermal efficiency of burning, and improve engine economy and
Reliability.
Description of the drawings
Fig. 1 is the operating diagram of an operation mode of combined cycle engine according to the present invention, wherein second gas
Entrance and third gas entrance partially open, and window is closed, arrow instruction airflow direction；
Fig. 2 is the circumferential position schematic diagram of the fuel nozzle ports of the continuous rotation detonation engine in Fig. 1；
Fig. 3 is the circumferential position schematic diagram of the igniter of the continuous rotation detonation engine in Fig. 1；
Fig. 4 is the operating diagram of another operation mode of combined cycle engine according to the present invention, wherein the second gas
Body entrance is closed, third gas entrance is opened and window is in inside bleed state, arrow instruction airflow direction；
Fig. 5 is the operating diagram of the another operation mode of combined cycle engine according to the present invention, wherein the second gas
Body entrance is opened, third gas entrance is closed and window is closed, arrow instruction airflow direction；
Fig. 6 is the operating diagram of the combined cycle engine under operation mode identical with Fig. 1, wherein second gas inlet
It is partially opened with third gas entrance, and window is in outside exhaust condition, arrow instruction airflow direction.
Wherein, the reference numerals are as follows：
1 supersonic speed admission gear, 25 igniter
11 first gas inlet, 26 fuel nozzle ports
12 first shell, 3 turbojet
The 3rd housing of 13 centerbody 31
131 precursor, 311 head
312 afterbody of body after 132
1321 increase 32 third gas entrance of diameter and arc surface portion
1322 tube reducing cambered surface portion, 33 third gas outlet
1323 tube reducing truncated cones, 4 first adjusting mechanisms of face
14 air inlet runner, 41 valve
15 window, 42 cylinder
2 continuous rotation 421 cylinder bodies of detonation engine
21 second shell, 422 piston rod
22 toroidal combustion chamber, 5 second adjusting mechanism
23 second gas inlet, 51 blade
24 second gas export
Specific embodiment
It is described in detail combined cycle engine according to the present invention with reference to the accompanying drawings.
Referring to figs. 1 to Fig. 6, combined cycle engine according to the present invention includes：Supersonic speed admission gear 1, have with it is outer
The first gas inlet 11 open vertically of portion's connection；Continuous rotation detonation engine 2, is fixedly connected on supersonic speed into mechanism of qi
The downstream of structure 1；And turbojet 3, it is fixedly connected on the downstream of supersonic speed admission gear 1.Wherein, continuously rotate quick-fried
Shake engine 2 and turbojet 3 with supersonic speed admission gear 1 is controlled connects with controlled via first gas inlet 11
It introduces extraneous gas and works.
It is continuous to rotate detonation engine 2 and turbojet 3 in combined cycle engine according to the present invention
With supersonic speed admission gear 1 is controlled connects, so as to smoothly complete mode in the range of the operating envelope of combined cycle engine
Conversion, steady propulsion is provided for aircraft, and then aircraft is made to realize 5.0 Mach or more of hypersonic flight in endoatmosphere
It and being capable of horizontal take-off landing.In addition, employing continuous rotation pinking technology based on continuous rotation detonation engine 2, improve
Engine/motor specific impulse solves the problems, such as combustion instability, and then improves the thermal efficiency of burning, and improves the economy of engine
Property and reliability.
Combined cycle engine according to the present invention, in one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, supersonic speed into
Mechanism of qi structure 1 may include：First shell 12 and centerbody 13.Centerbody 13 may include：Precursor 131 stretches out in first shell 12；
And rear body 132, it is contained in first shell 12, the boundary position of rear body 132 and precursor 131 forms first with first shell 12
Gas access 11, and be formed between the outside wall surface of rear body 132 and first shell 12 connected with first gas inlet 11 into
Flow channel 14.It remarks additionally herein, since first gas inlet 11 is relatively narrow compared with air inlet runner 14, because of hereafter body
The air inlet runner 14 formed between 132 outside wall surface and first shell 12 is pressure channel, especially under the conditions of supersonic flight,
Incoming air can form shock train with supercharging of slowing down in air inlet runner 14.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, precursor 131 is taper.Body 132 can have afterwards：Increase diameter and arc surface portion
1321, it is gradually increased from the axial downstream end of precursor 131 to axial downstream orient diameter；Tube reducing cambered surface portion 1322, from increasing footpath
The axial downstream end of curved portion is gradually reduced to axial downstream orient diameter；And tube reducing truncated cone face 1323, from tube reducing arc
The axial downstream end in shape portion is progressively smaller until turbojet 3 to axial downstream orient diameter.
In one embodiment, referring to figs. 1 to Fig. 6, the continuous detonation engine 2 that rotates may include：Second shell 21, it is fixed to connect
It is connected to the axial downstream end of first shell 12.
In one embodiment, referring to figs. 1 to Fig. 6, turbojet 3 may include：3rd housing 31, is fixedly connected on
The axial downstream end of the rear body 132 of the centerbody 13 of supersonic speed admission gear 1.Wherein, the head 311 of the 3rd housing 31 is stretched into
It is continuous to be formed between the outside wall surface on the head 311 of the 3rd housing 31 and the internal face of second shell 21 in second shell 21
Rotate the toroidal combustion chamber 22 of detonation engine 2.Rotation detonating combustion based on the fuel in toroidal combustion chamber 22 for etc. appearances combustion
It burns, so as to significantly improve the thermal efficiency, thus reduces the oil consumption rate of continuous rotation detonation engine 2, improve fuel-economy
Property.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, the continuous detonation engine 2 that rotates can have：Second gas enters
Mouth 23；And second gas outlet 24, it connects to discharge the exhaust gas in toroidal combustion chamber 22 after burning with toroidal combustion chamber 22.Whirlpool
Wheel jet engine 3 can have：Third gas entrance 32；And third gas outlet 33, it is arranged at turbojet 3
The afterbody 312 of 3rd housing 31, and connect to discharge inside turbojet 3 with the inside of turbojet 3
Gas.Combined cycle engine may also include：First adjusting mechanism 4, control second gas inlet 23 open or close so that
The toroidal combustion chamber 22 of continuous rotation detonation engine 2 is connected or disconnected with the air inlet runner 14 of supersonic speed admission gear 1；And
Second adjusting mechanism 5, control third gas entrance 32 open or close so that 3 inside of turbojet and supersonic speed into
The connection or disconnection of the air inlet runner 14 of mechanism of qi structure 1.
It remarks additionally herein, when speed of incoming flow is less than 1.5 Mach, incoming air is via first gas inlet 11
It is compressed into air inlet runner 14, temperature, the pressure of compressed air are not very high, are unfavorable for the shape of detonation wave at this time
Into, it can not be worked by the way that the first adjusting mechanism 4 is controlled to close second gas inlet 23 so as to continuously rotate detonation engine 2,
Only turbojet 3 works, as shown in Figure 4.It at this point, can be by the way that the second adjusting mechanism 5 be controlled to enter to tune up third gas
The aperture of mouth 32, so that incoming air is fully entered in turbojet 3.
When speed of incoming flow reaches 1.5 Mach, the continuous detonation engine 2 that rotates starts to start work, passes through control first
Adjusting mechanism 4 gradually expands the aperture of second gas inlet 23；At the same time the performance of turbojet 3 has decayed
It is larger, it can be by the way that the second adjusting mechanism 5 be controlled to be gradually reduced the aperture of third gas entrance 32, as shown in Figure 1.In this incoming
Under speed state, two kinds of simultaneous firings.
When speed of incoming flow is equal to 2.5 Mach, third gas entrance 32 is thoroughly closed, and turbojet 3 thoroughly stops
Only work.And second gas inlet 23 is opened to maximum, as shown in figure 5, incoming air all enters via second gas inlet 23
In the toroidal combustion chamber 22 of continuous rotation detonation engine 2, and gaseous mixture is formed with fuel, through 25 points of igniter described below
Detonation wave is formed after fire in toroidal combustion chamber 22, subsequent tail gas is via 24 discharge of second gas outlet, so as to generate thrust.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, the first adjusting mechanism 4 may include：Valve 41 and cylinder 42.
Valve 41 is arranged in the second shell 21 of continuous rotation detonation engine 2, and is slidably mounted on the of turbojet 3
The position of close first shell 12 on the forepart of three housings 31.Cylinder 42 includes：Cylinder body 421, one end is pivotally connected to second
The part of the axial rearward direction in valve 41 of housing 21；And cylinder body 421 is stretched into piston rod 422, one end, the other end stretches out cylinder body
421 and it is pivotally connected to valve 41.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, the second adjusting mechanism 5 may include：Multiple blades 51, it is close
132 radially installed of rear body of centerbody 13 is in the forepart of the 3rd housing 31.Wherein, each blade 51 can be around respective installation
Axis (not shown) rotates.When each blade 51 is rotated around respective installation axle and is separated from each other between adjacent blades 51, the 3rd gas
Body entrance 32 is opened；When each blade 51 is rotated around respective installation axle and adjacent blades 51 are mutually closely joined together, the
Three gas accesses 32 are closed.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, supersonic speed admission gear 1 may also include：Window 15, perforation
It is arranged in first shell 12, and air inlet runner 14 is controlled connects, with to the extraneous gas of the input supplement of air inlet runner 14 or will
Gas in air inlet runner 14 discharges.It remarks additionally herein, when speed of incoming flow is less than 0.6 Mach, due to the
One gas access 11 is relatively narrow and incoming is subsonic speed, and incoming air is insufficient for engine work requirements, at this time supersonic speed into
Window 15 on mechanism of qi structure 1 can be adjusted to bleed state, and by outside air, thus window 15 introduces air inlet runner 14, for supplementing
Air mass flow, as shown in Figure 4.And when inlet distortion occurs, window 15 can be adjusted to deflation status, will be in air inlet runner 14
Air draws the external world, so as to expand the stable operation range of engine, as shown in Figure 6.
In one embodiment, window 15 is a few conduits 151 circumferentially outputed at 12 rear portion of first shell.Conduit 151
The one side being connected with air is provided with adjustment sheet (not shown), and adjustment sheet can be rotated along respective installation axle, so as to fulfill air-flow
Flow and direction control, the angle of adjustment sheet can control by air inlet runner 14 and ambient atmosphere pressure difference.
In one embodiment, with reference to Fig. 1 and Fig. 3 to Fig. 6, the continuous detonation engine 2 that rotates may also include：Igniter
25, it is arranged in the toroidal combustion chamber 22 of continuous rotation detonation engine 2, for entering the combustion gas in toroidal combustion chamber 22
(i.e. the gaseous mixture of fuel and air) lights a fire, and then combustion gas detonating combustion.
In one embodiment, with reference to Fig. 1, Fig. 2 and Fig. 3 to Fig. 6, the continuous detonation engine 2 that rotates can also have：It is multiple
Fuel nozzle ports 26, radially penetrate through second shell 21 with 22 corresponding part of toroidal combustion chamber, and along the week of second shell 21
To distribution, each fuel nozzle ports 26 connect 3 inside of turbojet and toroidal combustion chamber 22, so that fuel is sprayed via each fuel
Mouth 26 enters toroidal combustion chamber 22.Remark additionally herein, multiple fuel nozzle ports 26 along the circumferentially distributed of second shell 21,
Fuel can be made to enter the direction of toroidal combustion chamber 22 and the stream of the air (as oxidant) entered via second gas inlet 23
Dynamic direction contributes to fuel fully to be blended with air in 90 °.
In one embodiment, combined cycle engine may also include：Control system (not shown), communication connection first are adjusted
The cylinder 42 of mechanism 4, the second adjusting mechanism 5 and window 15.
In one embodiment, combined cycle engine can as near space hypersonic vehicle dynamical system, two
Grade is entered the orbit the dynamical system of the delivery system first order or the dynamical system of hypersonic speed civil aircraft and sky and space plane.
Claims (7)
1. a kind of combined cycle engine, which is characterized in that including：
Supersonic speed admission gear (1) has the first gas inlet (11) open vertically connected with outside；
Continuous rotation detonation engine (2) is fixedly connected on the downstream of supersonic speed admission gear (1)；And
Turbojet (3) is fixedly connected on the downstream of supersonic speed admission gear (1)；
Wherein, continuously rotate detonation engine (2) and turbojet (3) with supersonic speed admission gear (1) controlled company
It passes to and works via the controlled introducing extraneous gas of first gas inlet (11)；
Supersonic speed admission gear (1) includes：
First shell (12)；And
Centerbody (13), including：
Precursor (131) stretches out in first shell (12)；
Body (132) afterwards are contained in first shell (12), boundary position and first shell of the rear body (132) with precursor (131)
(12) first gas inlet (11) is formed,
And it is formed with the air inlet connected with first gas inlet (11) between the outside wall surface of rear body (132) and first shell (12)
Runner (14)；
Supersonic speed admission gear (1) further includes：Window (15), perforation is arranged in first shell (12), with air inlet runner (14)
Controlled connection, to be discharged to the extraneous gas of air inlet runner (14) input supplement or by the gas in air inlet runner (14)；
Window (15) is a few conduits (151) circumferentially outputed at first shell (12) rear portion, conduit (151) and big gas phase
One side even is provided with adjustment sheet, and adjustment sheet rotate along respective installation axle, the angle of adjustment sheet by air inlet runner (14) with outside
Boundary's atm difference control.
2. combined cycle engine according to claim 1, which is characterized in that continuously rotating detonation engine (2) includes：
Second shell (21) is fixedly connected on the axial downstream end of first shell (12).
3. combined cycle engine according to claim 2, which is characterized in that turbojet (3) includes：
3rd housing (31) is fixedly connected on the axial downstream of the rear body (132) of the centerbody (13) of supersonic speed admission gear (1)
End；
Wherein, the head (311) of the 3rd housing (31) is stretched into second shell (21), on the head of the 3rd housing (31)
(311) toroidal combustion chamber of continuous rotation detonation engine (2) is formed between outside wall surface and the internal face of second shell (21)
(22)。
4. combined cycle engine according to claim 3, which is characterized in that
Continuous rotation detonation engine (2) has：
Second gas inlet (23)；And
Second gas exports (24), connects to discharge the exhaust gas in toroidal combustion chamber (22) after burning with toroidal combustion chamber (22)；
Turbojet (3) has：
Third gas entrance (32)；And
Third gas exports (33), is arranged at the afterbody (312) of the 3rd housing (31) of turbojet (3), and and whirlpool
The inside of wheel jet engine (3) connects to discharge the internal gas of turbojet (3)；
Combined cycle engine further includes：
First adjusting mechanism (4), control second gas inlet (23) are opened or closed so as to continuously rotate detonation engine (2)
Toroidal combustion chamber (22) connect or disconnect with the air inlet runner (14) of supersonic speed admission gear (1)；And
Second adjusting mechanism (5), control third gas entrance (32) are opened or closed so that turbojet (3) is internal
With the connection or disconnection of the air inlet runner (14) of supersonic speed admission gear (1).
5. combined cycle engine according to claim 4, which is characterized in that the first adjusting mechanism (4), including：
Valve (41) is arranged in the second shell (21) of continuous rotation detonation engine (2), and is slidably mounted on turbojet
The position of close first shell (12) on the forepart of 3rd housing (31) of engine (3)；And
Cylinder (42), including：
Cylinder body (421), one end are pivotally connected to the part of the axial rearward direction in valve (41) of second shell (21)；And
Cylinder body (421) is stretched into piston rod (422), one end, and the other end stretches out cylinder body (421) and is pivotally connected to valve (41).
6. combined cycle engine according to claim 4, which is characterized in that the second adjusting mechanism (5) includes：
Multiple blades (51), rear body (132) radially installed close to centerbody (13) is in the forepart of the 3rd housing (31)；
Wherein, each blade (51) can rotate around respective installation axle, when each blade (51) around respective installation axle rotate and
When being separated from each other between adjacent blades (51), third gas entrance (32) is opened；When each blade (51) turns around respective installation axle
When dynamic and adjacent blades (51) are closely joined together, third gas entrance (32) is closed.
7. combined cycle engine according to claim 1, which is characterized in that continuously rotate detonation engine (2) and also wrap
It includes：
Igniter (25) is arranged in the toroidal combustion chamber (22) of continuous rotation detonation engine (2), for entering annular
Combustion gas in combustion chamber (22) is lighted a fire, and then combustion gas detonating combustion；And
Multiple fuel nozzle ports (26) radially penetrate through the part corresponding with toroidal combustion chamber (22) of second shell (21), and edge
Circumferentially distributed, each fuel nozzle ports (26) connection turbojet (3) inside and the toroidal combustion chamber of second shell (21)
(22), so that fuel enters toroidal combustion chamber (22) via each fuel nozzle ports (26).
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| CN201610222011.3A CN105736178B (en) | 2016-04-11 | 2016-04-11 | Combined cycle engine |
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| CN201610222011.3A CN105736178B (en) | 2016-04-11 | 2016-04-11 | Combined cycle engine |
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| CN105736178A CN105736178A (en) | 2016-07-06 |
| CN105736178B true CN105736178B (en) | 2018-05-29 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106288980B (en) * | 2016-08-09 | 2018-04-27 | 西北工业大学 | A kind of application method of the Control System for Reusable Launch Vehicle based on RBCC power |
| US10969107B2 (en) | 2017-09-15 | 2021-04-06 | General Electric Company | Turbine engine assembly including a rotating detonation combustor |
| FR3074855A1 (en) * | 2017-12-11 | 2019-06-14 | Airbus Operations | GRID FOR FORMATION OF AN INVERSION FLOW OF AN AIRCRAFT TURBOJET ENGINE |
| US11486579B2 (en) | 2018-02-26 | 2022-11-01 | General Electric Company | Engine with rotating detonation combustion system |
| US11359578B2 (en) | 2018-08-06 | 2022-06-14 | General Electric Company | Ramjet engine with rotating detonation combustion system and method for operation |
| CN109340818B (en) * | 2018-09-29 | 2019-08-23 | 南京航空航天大学 | A kind of engine chamber with guidance combustion chamber |
| CN109538377B (en) * | 2018-11-15 | 2020-03-27 | 厦门大学 | Design method of three-power combined engine sharing sub-combustion chamber |
| CN109441663A (en) * | 2018-12-12 | 2019-03-08 | 清华大学 | Combined cycle engine |
| US11105511B2 (en) | 2018-12-14 | 2021-08-31 | General Electric Company | Rotating detonation propulsion system |
| CN111520766A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Radial grading detonation afterburner |
| CN117552891B (en) * | 2024-01-12 | 2024-03-22 | 清华大学 | Rotary knocking engine based on wall surface multiple concave cavities and pits and control method |
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| CN101514656B (en) * | 2009-04-01 | 2011-03-02 | 西北工业大学 | Turbine combined pulse detonation engine |
| US8429893B2 (en) * | 2009-08-11 | 2013-04-30 | Northrop Grumman Corporation | Airflow modulation for dual mode combined cycle propulsion systems |
| RU2472956C2 (en) * | 2011-04-29 | 2013-01-20 | Открытое акционерное общество "ОКБ Сухого" | Supersonic controlled air intake |
| CN102155331A (en) * | 2011-05-05 | 2011-08-17 | 西北工业大学 | Turboramjet combined engine based on knocking combustion |
| CN105221295B (en) * | 2015-11-06 | 2017-02-01 | 西南科技大学 | Stamping-turbine air injection composite aero-engine |
| CN205592035U (en) * | 2016-04-11 | 2016-09-21 | 清华大学 | Combined cycle engine |
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