CN105736178A - Combined cycle engine - Google Patents
Combined cycle engine Download PDFInfo
- Publication number
- CN105736178A CN105736178A CN201610222011.3A CN201610222011A CN105736178A CN 105736178 A CN105736178 A CN 105736178A CN 201610222011 A CN201610222011 A CN 201610222011A CN 105736178 A CN105736178 A CN 105736178A
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- Prior art keywords
- housing
- combined cycle
- turbojet
- gas
- cycle engine
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- 238000005474 detonation Methods 0.000 claims abstract description 39
- 238000002485 combustion reaction Methods 0.000 claims abstract description 31
- 239000007789 gas Substances 0.000 claims description 61
- 239000000446 fuel Substances 0.000 claims description 17
- 230000033001 locomotion Effects 0.000 claims description 16
- 210000003793 centrosome Anatomy 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 7
- 239000002243 precursor Substances 0.000 claims description 7
- 239000000567 combustion gas Substances 0.000 claims description 4
- 239000002912 waste gas Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract 1
- 230000007704 transition Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 230000009466 transformation Effects 0.000 description 5
- 238000005183 dynamical system Methods 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 239000008246 gaseous mixture Substances 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Classifications
-
- 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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The invention provides a combined cycle engine. The combined cycle engine comprises a supersonic air inlet mechanism, a continuous rotation detonation engine body and a turbojet engine body, wherein the supersonic air inlet mechanism is provided with a first gas inlet which communicates with the outside and is opened in the axial direction, and the continuous rotation detonation engine body and the turbojet engine body are fixedly connected to the lower portion of the supersonic air inlet mechanism. The continuous rotation detonation engine body and the turbojet engine body both communicate with the supersonic air inlet mechanism in a controlled mode in order to work in the mode that external gas is introduced into the continuous rotation detonation engine body and the turbojet engine body through the first gas inlet in the controlled mode. According to the combined cycle engine, mode transition can be completed within an operating envelope range, the stable thrust is provided for an aircraft, and then the aircraft hypersonically flies at 5.0 Mach or above in the atmosphere and can land and take off horizontally; in addition, the specific impulse of the engine is improved on the basis of adopting the continuous rotation detonation technique, the combustion heat efficiency is improved, and the economy and the reliability of the engine are improved.
Description
Technical field
The present invention relates to Aero-Space power technology field, particularly relate to a kind of combined cycle engine.
Background technology
The highest flight speed has superior high-altitude high speed characteristics, the flexibly advantage such as mobility, higher penetraton probability at the near space hypersonic vehicle of Mach number about 5.0, has highly important potential military value.Additionally, along with the progress of missile defense technology, the prominent anti-and survival ability of tradition guided missile is also affected by great threat, is badly in need of improving mobility by propelled at high velocity device.But, the aircraft of this kind of type has the features such as operating envelope width, flight operating mode be complicated and changeable, and the propulsion plant of single type is difficult to the whole job requirement of complete independently, and therefore, assembly power technology is arisen at the historic moment, and causes rapidly the concern of people.Studying two more class combined cycle engines at present is rocket punching press combined cycle engine and turboram combined cycle engine, the former is less economical because effectively not utilizing the oxygen in air, and be difficult at present meet reusable requirement, and for the latter, maximum it has a problem in that MODAL TRANSFORMATION OF A, the most high workload Mach number of turbogenerator is lower than effective Start mach number of punching engine, thus when causing combined engine from turbine mode to punching press MODAL TRANSFORMATION OF A, thrust cannot meet requirement.
Summary of the invention
In view of Problems existing in background technology, it is an object of the present invention to provide a kind of combined cycle engine, it can smoothly complete MODAL TRANSFORMATION OF A within the scope of operating envelope, there is provided steady propulsion for aircraft, and then make hypersonic flight that aircraft realizes more than 5.0 Mach in endoatmosphere and can horizontal take-off land.
A kind of combined cycle engine of offer is provided, which raises engine/motor specific impulse, the problem solving combustion instability, and then improve the thermal efficiency of burning, and improve economy and the reliability of electromotor.
To achieve these goals, the invention provides a kind of combined cycle engine, comprising: supersonic speed admission gear, there is the first gas access opened wide vertically with ft connection；Rotate detonation engine continuously, be 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, rotate continuously that detonation engine is all controlled with supersonic speed admission gear with turbojet to be connected to be operated via the first controlled introducing extraneous gas in gas access.
Beneficial effects of the present invention is as follows:
According in the combined cycle engine of the present invention, rotate continuously that detonation engine is all controlled with supersonic speed admission gear with turbojet to be connected, thus MODAL TRANSFORMATION OF A can be smoothly completed within the scope of the operating envelope of combined cycle engine, there is provided steady propulsion for aircraft, and then make hypersonic flight that aircraft realizes more than 5.0 Mach in endoatmosphere and can horizontal take-off land.Additionally, have employed, based on rotating detonation engine continuously, the pinking technology that rotates continuously, improve engine/motor specific impulse, the problem solving combustion instability, and then improve the thermal efficiency of burning, and improve economy and the reliability of electromotor.
Accompanying drawing explanation
Fig. 1 is the operating diagram of an operation mode of the combined cycle engine according to the present invention, and wherein the second gas access and the 3rd gas access all partially open, and window is closed, arrow instruction airflow direction；
Fig. 2 is the circumferential position schematic diagram of the fuel nozzle ports rotating detonation engine continuously in Fig. 1；
Fig. 3 is the circumferential position schematic diagram of the lighter rotating detonation engine continuously in Fig. 1；
Fig. 4 is the operating diagram of another operation mode of the combined cycle engine according to the present invention, and wherein the second gas access is closed, the 3rd gas access 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 the combined cycle engine according to the present invention, and wherein the second gas access is opened, the 3rd gas access closes 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, and wherein the second gas access and the 3rd gas access all partially open, and window is in outside exhaust condition, arrow instruction airflow direction.
Wherein, description of reference numerals is as follows:
1 supersonic speed admission gear 25 lighter
11 first gas access 26 fuel nozzle ports
12 first housing 3 turbojets
13 centrosome 31 the 3rd housings
131 precursor 311 heads
Body 312 afterbody after 132
1321 increase gas access, diameter and arc surface portion 32 the 3rd
1322 gas outlets of tube reducing cambered surface portion 33 the 3rd
1323 tube reducing truncated cone face 4 first governor motions
14 air inlet runner 41 valve
15 window 42 cylinders
2 rotate detonation engine 421 cylinder body continuously
21 second housing 422 piston rods
22 toroidal combustion chamber 5 second governor motions
23 second gas access 51 blades
24 second gas outlets
Detailed description of the invention
Describe the combined cycle engine according to the present invention with reference to the accompanying drawings in detail.
Referring to figs. 1 through Fig. 6, include according to the combined cycle engine of the present invention: supersonic speed admission gear 1, there is the first gas access 11 opened wide vertically with ft connection；Rotate detonation engine 2 continuously, be fixedly connected on the downstream of supersonic speed admission gear 1；And turbojet 3, it is fixedly connected on the downstream of supersonic speed admission gear 1.Wherein, rotate continuously that detonation engine 2 is all controlled with supersonic speed admission gear 1 with turbojet 3 to be connected to be operated via the first controlled introducing extraneous gas in gas access 11.
According in the combined cycle engine of the present invention, rotate continuously that detonation engine 2 is all controlled with supersonic speed admission gear 1 with turbojet 3 to be connected, thus MODAL TRANSFORMATION OF A can be smoothly completed within the scope of the operating envelope of combined cycle engine, there is provided steady propulsion for aircraft, and then make hypersonic flight that aircraft realizes more than 5.0 Mach in endoatmosphere and can horizontal take-off land.Additionally, have employed, based on rotating detonation engine 2 continuously, the pinking technology that rotates continuously, improve engine/motor specific impulse, the problem solving combustion instability, and then improve the thermal efficiency of burning, and improve economy and the reliability of electromotor.
Combined cycle engine according to the present invention, in one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, supersonic speed admission gear 1 comprises the steps that the first housing 12 and centrosome 13.Centrosome 13 comprises the steps that precursor 131, stretches out in the first housing 12；And after body 132, it is contained in the first housing 12, the position, boundary of rear body 132 and precursor 131 forms the first gas access 11 with the first housing 12, and is formed with, between the outside wall surface and the first housing 12 of rear body 132, the air inlet runner 14 connected with the first gas access 11.What here remark additionally is, owing to the first gas access 11 is narrower relative to air inlet runner 14, the air inlet runner 14 formed between outside wall surface and first housing 12 of cause hereafter body 132 is pressure channel, especially, when supersonic flight, incoming air can form shock train with deceleration supercharging in air inlet runner 14.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, precursor 131 is taper.Rear body 132 can have: increases diameter and arc surface portion 1321, is gradually increased to axial downstream orient diameter from the axial downstream end of precursor 131；Tube reducing cambered surface portion 1322, is gradually reduced from the axial downstream end increasing footpath curved portions to axial downstream orient diameter；And tube reducing truncated cone face 1323, it is progressively smaller until turbojet 3 from the axial downstream end of tube reducing curved portions to axial downstream orient diameter.
In one embodiment, referring to figs. 1 through Fig. 6, rotate detonation engine 2 continuously and comprise the steps that the second housing 21, be fixedly connected on the axial downstream end of the first housing 12.
In one embodiment, referring to figs. 1 through Fig. 6, turbojet 3 comprises the steps that the 3rd housing 31, is fixedly connected on the axial downstream end of the rear body 132 of the centrosome 13 of supersonic speed admission gear 1.Wherein, the head 311 of the 3rd housing 31 stretches in the second housing 21, to form the toroidal combustion chamber 22 rotating detonation engine 2 continuously between the internal face of the outside wall surface of the head 311 at the 3rd housing 31 and the second housing 21.Rotation detonating combustion based on the fuel in toroidal combustion chamber 22 is isochoric combustion, thus significantly improving the thermal efficiency, thus reducing the oil consumption rate rotating detonation engine 2 continuously, improve fuel economy.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, rotating detonation engine 2 continuously can have: the second gas access 23；And second gas outlet 24, connect to discharge the waste gas after burning in toroidal combustion chamber 22 with toroidal combustion chamber 22.Turbojet 3 can have: the 3rd gas access 32；And the 3rd gas outlet 33, it is arranged at the afterbody 312 of the 3rd housing 31 of turbojet 3, and connects to discharge the gas within turbojet 3 with the inside of turbojet 3.Combined cycle engine may also include that the first governor motion 4, controls opening or closing so that the toroidal combustion chamber 22 rotating detonation engine 2 continuously connects with the air inlet runner 14 of supersonic speed admission gear 1 or disconnects of the second gas access 23；And second governor motion 5, what control the 3rd gas access 32 opens or closes so that the connection of the internal air inlet runner 14 with supersonic speed admission gear 1 of turbojet 3 or disconnection.
What here remark additionally is, when speed of incoming flow is less than 1.5 Mach, incoming air enters in air inlet runner 14 via the first gas access 11 and is compressed, the temperature of the air after compression, pressure are not as high, now being unfavorable for the formation of detonation wave, the second gas access 23 can be closed by controlling the first governor motion 4, not working so that rotating detonation engine 2 continuously, only turbojet 3 works, as shown in Figure 4.Now, the aperture of the 3rd gas access 32 can be tuned up by controlling the second governor motion 5, so that incoming air fully enters in turbojet 3.
When speed of incoming flow reaches 1.5 Mach, rotate detonation engine 2 continuously and start to start work, expand the aperture of the second gas access 23 by controlling the first governor motion 4 gradually；Meanwhile the performance of turbojet 3 has decayed relatively big, can be gradually reduced the aperture of the 3rd gas access 32 by controlling the second governor motion 5, as shown in Figure 1.Under this speed of incoming flow state, two kinds of simultaneous firings.
When speed of incoming flow is equal to 2.5 Mach, the 3rd gas access 32 is thoroughly closed, and turbojet 3 thoroughly quits work.And the second gas access 23 is opened to maximum, as shown in Figure 5, incoming air all enters via the second gas access 23 in the toroidal combustion chamber 22 rotating detonation engine 2 continuously, and form gaseous mixture with fuel, in toroidal combustion chamber 22, detonation wave is formed after lighter 25 hereinafter described is lighted a fire, tail gas is discharged via the second gas outlet 24 subsequently, thus producing thrust.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, the first governor motion 4 comprises the steps that valve 41 and cylinder 42.Valve 41 is arranged in the second housing 21 rotating continuously detonation engine 2, and be slidably mounted on turbojet 3 the 3rd housing 31 front portion on the position near the first housing 12.Cylinder 42 includes: cylinder body 421, and one end is pivotally connected to the part of the axial rearward direction at valve 41 of the second housing 21；And piston rod 422, cylinder body 421 is stretched in one end, and the other end stretches out cylinder body 421 and is pivotally connected to valve 41.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, the second governor motion 5 comprises the steps that multiple blade 51, and the rear body 132 near centrosome 13 is radially installed in the front portion of the 3rd housing 31.Wherein, each blade 51 all can rotate around respective installation axle (not shown).When each blade 51 rotates around respective installation axle and is separated from each other between adjacent blades 51, the 3rd gas access 32 is opened；When each blade 51 is closely joined together mutually around the rotation of respective installation axle and adjacent blades 51, the 3rd gas access 32 is closed.
In one embodiment, with reference to Fig. 1 and Fig. 4 to Fig. 6, supersonic speed admission gear 1 may also include that window 15, through is arranged on the first housing 12, controlled with air inlet runner 14 connect, with the extraneous gas supplemented to air inlet runner 14 input or the gas in air inlet runner 14 is discharged.What here remark additionally is, when speed of incoming flow is less than 0.6 Mach, owing to the first gas access 11 is narrower and incoming flow is supersonic speed, incoming air is insufficient for electromotor work requirements, now the window 15 in supersonic speed admission gear 1 can be adjusted to bleed state, so that outside air thus window 15 is introduced into flow channel 14, it is used for supplementing air mass flow, as shown in Figure 4.And when there is inlet distortion, window 15 can be adjusted to deflation status, so that the air in air inlet runner 14 is drawn the external world, thus expanding the stable operation range of electromotor, as shown in Figure 6.
In one embodiment, window 15 is a few conduits 151 circumferentially outputed at the first housing 12 rear portion.The side that conduit 151 is connected with air is provided with adjustment sheet (not shown), and adjustment sheet can rotate along respective installation axle, thus realizing the flow of air-flow and the control in direction, the angle of adjustment sheet can be controlled with ambient atmosphere pressure reduction by air inlet runner 14.
In one embodiment, with reference to Fig. 1 and Fig. 3 to Fig. 6, rotate detonation engine 2 continuously and may also include that lighter 25, it is arranged in the toroidal combustion chamber 22 rotating detonation engine 2 continuously, light a fire for the combustion gas (i.e. the gaseous mixture of fuel and air) entered in toroidal combustion chamber 22, and then combustion gas detonating combustion.
In one embodiment, with reference to Fig. 1, Fig. 2 and Fig. 3 to Fig. 6, rotate detonation engine 2 continuously also can have: multiple fuel nozzle ports 26, the part corresponding with toroidal combustion chamber 22 of radially through second housing 21, and circumferentially distributed along the second housing 21, each fuel nozzle ports 26 connects turbojet 3 inside and toroidal combustion chamber 22, so that fuel enters toroidal combustion chamber 22 via each fuel nozzle ports 26.What here remark additionally is, multiple fuel nozzle ports 26 are circumferentially distributed along the second housing 21, it is 90 ° that fuel can be made to enter the direction of toroidal combustion chamber 22 with the flow direction of the air (as oxidant) entered via the second gas access 23, contributes to fuel and fully blends with air.
In one embodiment, combined cycle engine may also include that control system (not shown), communicates to connect cylinder the 42, second governor motion 5 and the window 15 of the first governor motion 4.
In one embodiment, combined cycle engine can be 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 as the dynamical system of near space hypersonic vehicle, two-stage.
Claims (10)
1. a combined cycle engine, it is characterised in that including:
Supersonic speed admission gear (1), has the first gas access (11) opened wide vertically with ft connection；
Rotate detonation engine (2) continuously, be 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, rotate that detonation engine (2) is all controlled with supersonic speed admission gear (1) with turbojet (3) to be connected to be operated via the first gas access (11) controlled introducing extraneous gas continuously.
2. combined cycle engine according to claim 1, it is characterised in that supersonic speed admission gear (1) including:
First housing (12)；And
Centrosome (13), including:
Precursor (131), stretches out in the first housing (12)；
Rear body (132), it is contained in the first housing (12), the position, boundary of rear body (132) and precursor (131) and the first housing (12) form the first gas access (11), and are formed with, between the outside wall surface and the first housing (12) of rear body (132), the air inlet runner (14) connected with the first gas access (11).
3. combined cycle engine according to claim 2, it is characterised in that rotate detonation engine (2) continuously and including:
Second housing (21), is fixedly connected on the axial downstream end of the first housing (12).
4. combined cycle engine according to claim 3, it is characterised in that turbojet (3) including:
3rd housing (31), is fixedly connected on the axial downstream end of the rear body (132) of the centrosome (13) of supersonic speed admission gear (1)；
Wherein, the head (311) of the 3rd housing (31) stretches in the second housing (21), to form the toroidal combustion chamber (22) rotating detonation engine (2) continuously between the outside wall surface of the head (311) of the 3rd housing (31) and the internal face of the second housing (21).
5. combined cycle engine according to claim 4, it is characterised in that
Rotate detonation engine (2) continuously to have:
Second gas access (23)；And
Second gas outlet (24), connects with toroidal combustion chamber (22) to discharge the waste gas after burning in toroidal combustion chamber (22)；
Turbojet (3) has:
3rd gas access (32)；And
3rd gas outlet (33), it is arranged at the afterbody (312) of the 3rd housing (31) of turbojet (3), and connects the gas internal to discharge turbojet (3) with the inside of turbojet (3)；
Combined cycle engine also includes:
First governor motion (4), controls opening or closing so that the air inlet runner (14) of the toroidal combustion chamber (22) and supersonic speed admission gear (1) that rotate detonation engine (2) continuously connects or disconnects of the second gas access (23)；And
Second governor motion (5), what control the 3rd gas access (32) opens or closes so that the connection of the internal air inlet runner (14) with supersonic speed admission gear (1) of turbojet (3) or disconnection.
6. combined cycle engine according to claim 5, it is characterised in that the first governor motion (4), including:
Valve (41), be arranged in the second housing (21) rotating detonation engine (2) continuously, and be slidably mounted on turbojet (3) the 3rd housing (31) front portion near the position of the first housing (12)；And
Cylinder (42), including:
Cylinder body (421), one end is pivotally connected to the part of the axial rearward direction at valve (41) of the second housing (21)；And
Piston rod (422), cylinder body (421) is stretched in one end, and the other end stretches out cylinder body (421) and is pivotally connected to valve (41).
7. combined cycle engine according to claim 5, it is characterised in that the second governor motion (5) including:
Multiple blades (51), the rear body (132) near centrosome (13) is radially installed in the front portion of the 3rd housing (31)；
Wherein, each blade (51) all can rotate around respective installation axle, and when each blade (51) rotates around respective installation axle and is separated from each other between adjacent blades (51), the 3rd gas access (32) is opened；When each blade (51) is closely joined together around the rotation of respective installation axle and adjacent blades (51), the 3rd gas access (32) is closed.
8. combined cycle engine according to claim 2, it is characterised in that supersonic speed admission gear (1) also includes:
Window (15), through it is arranged on the first housing (12), controlled with air inlet runner (14) connect, with the extraneous gas supplemented to air inlet runner (14) input or the gas in air inlet runner (14) is discharged.
9. combined cycle engine according to claim 8, it is characterised in that window (15) is a few conduits (151) circumferentially outputed at the first housing 12 rear portion.
10. combined cycle engine according to claim 1, it is characterised in that rotate detonation engine (2) continuously and also include:
Lighter (25), is arranged in the toroidal combustion chamber (22) rotating detonation engine (2) continuously, lights a fire for the combustion gas entered in toroidal combustion chamber (22), and then combustion gas detonating combustion；And
Multiple fuel nozzle ports (26), the part corresponding with toroidal combustion chamber (22) of radially through second housing (21), and circumferentially distributed along the second housing (21), each fuel nozzle ports (26) connection turbojet (3) inside and toroidal combustion chamber (22), so that fuel enters toroidal combustion chamber (22) via each fuel nozzle ports (26).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222011.3A CN105736178B (en) | 2016-04-11 | 2016-04-11 | Combined cycle engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222011.3A CN105736178B (en) | 2016-04-11 | 2016-04-11 | Combined cycle engine |
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| CN105736178A true CN105736178A (en) | 2016-07-06 |
| CN105736178B CN105736178B (en) | 2018-05-29 |
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| CN201610222011.3A Active CN105736178B (en) | 2016-04-11 | 2016-04-11 | Combined cycle engine |
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| CN109340818A (en) * | 2018-09-29 | 2019-02-15 | 南京航空航天大学 | A kind of engine chamber with guidance combustion chamber |
| CN109441663A (en) * | 2018-12-12 | 2019-03-08 | 清华大学 | Combined cycle engine |
| CN109538377A (en) * | 2018-11-15 | 2019-03-29 | 厦门大学 | Share three power combination engine design methods of sub- combustion combustion chamber |
| CN109896023A (en) * | 2017-12-11 | 2019-06-18 | 空中客车运营简化股份公司 | Grid and turbofan and aircraft |
| CN111322637A (en) * | 2018-12-14 | 2020-06-23 | 通用电气公司 | Rotary detonation propulsion system |
| CN111520766A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Radial grading detonation afterburner |
| US10969107B2 (en) | 2017-09-15 | 2021-04-06 | General Electric Company | Turbine engine assembly including a rotating detonation combustor |
| US11359578B2 (en) | 2018-08-06 | 2022-06-14 | General Electric Company | Ramjet engine with rotating detonation combustion system and method for operation |
| US11486579B2 (en) | 2018-02-26 | 2022-11-01 | General Electric Company | Engine with rotating detonation combustion system |
| CN117552891A (en) * | 2024-01-12 | 2024-02-13 | 清华大学 | Rotary knocking engine based on wall surface multiple concave cavities and pits and control method |
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