CN109340818B - A kind of engine chamber with guidance combustion chamber - Google Patents

A kind of engine chamber with guidance combustion chamber Download PDF

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Publication number
CN109340818B
CN109340818B CN201811149358.5A CN201811149358A CN109340818B CN 109340818 B CN109340818 B CN 109340818B CN 201811149358 A CN201811149358 A CN 201811149358A CN 109340818 B CN109340818 B CN 109340818B
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China
Prior art keywords
cone
combustion chamber
chamber
guidance
combustion
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CN201811149358.5A
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CN109340818A (en
Inventor
王卫星
张仁涛
朱婷
谭慧俊
李宥晨
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

The present invention provides a kind of engine chamber with guidance combustion chamber, which includes the inner cavity surrounded by lip cover, the compression cone at lumen inlet, the stifled cone at chamber exit;In High Mach number flight, incoming flow total temperature is higher, and guidance combustion chamber forms the recirculating zone of high temperature and pressure low speed in centerbody rear end downstream, in recirculating zone fuel spontaneous combustion due to high temperature and pressure, and then entire sub- combustion guidance combustion chamber of igniting;Cone is blocked up at chamber exit can be enhanced the diffusivity of guidance combustion chamber high temperature combustion gas, accelerates the diffusion velocity of supersonic speed combustion chamber flame, is a kind of high pressure ratio, the Combustion chamber design scheme spread by force;Meanwhile entire combustion chamber uses central burner, can effectively mitigate the thermic load of combustion chamber wall surface.

Description

A kind of engine chamber with guidance combustion chamber
Technical field
The invention belongs to aircraft air intake duct technical fields.
Background technique
For the aero-engine under supersonic speed state that works, air-flow generally still falls within ultrasound when reaching combustion chamber State, and consider for integration, the length of combustion chamber cannot be too long, it means that remaining time of the high-speed flow in combustion chamber Only millisecond magnitude.Processes such as burning broken, atomization, blending, igniting and flame propagation and most are realized in a relatively short period of time Stable, efficient burning is completed eventually, faces larger challenge.Supersonic speed combustion chamber, burning tissues are keys, at present supersonic combustion room master It will be using combustion methods such as cavity, center supporting plate, throttlings.
Traditional Cavity Flame Holder carries out burning tissues by the way that cavity is arranged on wall surface to establish recirculating zone, has Steady flame ability is strong, resistance is small, advantages of simple structure and simple.But Cavity Flame Holder is low with the mass exchange rate of mainstream, flame to The deficiencies of mainstream diffusion is difficult, and efficiency of combustion is relatively low, and wall surface thermal force is big.
Center supporting plate flameholder can be formed with the recirculating zone conducive to igniting and flame stabilization in supporting plate tail rafter, and lead to The interaction crossed between different supporting plates can form the lower low mach region of speed in flow field, be conducive to tissue and burn.But Conventional supporting plate scheme is easily jammed to runner generation, increases flow losses and resistance, and steady flame ability deviation;Supporting plate scheme Sufficiently complex, circumferential direction can not be arranged continuously, therefore flame propagation still is difficult to carry out.
Air throttle is to generate shock train by throttling so that the Mach number in flow field reduces, and then raising static temperature with it is quiet Pressure is more advantageous to igniting and stablizes and burns, and the whirlpool of generation also contributes to the mixing and igniting of fuel.However the choosing of Restriction Parameters Taking has a strong influence for restriction effect, and inappropriate Restriction Parameters igniting to engine and can stablize burning and play phase Anti- effect, or even influence the starting performance of engine.
Summary of the invention
Goal of the invention: the present invention discloses a kind of engine chamber of aero-engine, solves point in engine combustion room The problem of fire and combustion instability, while solving the problems, such as how to accelerate engine combustion interior flame diffusion velocity.
Technical solution: in order to achieve the above objectives, following technical solution can be used in the present invention:
A kind of engine chamber with guidance combustion chamber, the guidance combustion chamber are located at the inside of engine chamber And close to the entrance of engine chamber;The guidance combustion chamber includes the inner cavity surrounded by lip cover, at lumen inlet Compression cone, the stifled cone at chamber exit;The compression cone includes former and later two parts, and front is divided into cone, rear part For round estrade, and part with round estrade front divides the cross section of connecting place maximum for area in entire compression cone after cone Cross section;The front end of the cone extends anteriorly out at lumen inlet;The front end of the stifled cone is similarly cone, and this is stifled The cone front end of cone extends forwardly to chamber exit and forms gap between chamber exit.
The utility model has the advantages that being provided with guidance combustion chamber in engine combustion room of the invention.In High Mach number flight, incoming flow Total temperature is higher, and guidance combustion chamber forms the recirculating zone of high temperature and pressure low speed in centerbody rear end downstream, in the recirculating zone fuel The spontaneous combustion due to high temperature and pressure, and then entire sub- combustion guidance combustion chamber of igniting.The present invention not only can effectively guide combustion Burn the igniting and burning of room, it is important to the diffusivity of guidance combustion chamber high temperature combustion gas can be enhanced, accelerate supersonic speed combustion chamber The diffusion velocity of flame is a kind of high pressure ratio, the Combustion chamber design scheme spread by force;Meanwhile entire combustion chamber is fired using center It burns, can effectively mitigate the thermic load of combustion chamber wall surface.
Further, the guidance combustion chamber is designed for axial symmetry, and guides the center line and engine combustion of combustion chamber The center line of room is overlapped.
Further, the lip cover is located at the formation inclined-plane of the inside at chamber exit, and the inclined-plane is outer with stifled cone cone Surface is parallel.
Further, sub- combustion air intake duct uses external pressure one stage of compression, and external compression angle is 220;Lip cover one stage of compression, and lip Cover compression angle is 11 °.
Further, blocking up cone cone angle is 60 °.
Detailed description of the invention
Fig. 1 is the engine combustion chamber structure schematic diagram that the present invention has guidance combustion chamber.
Fig. 2 is the structural schematic diagram for guiding combustion chamber.
Fig. 3 is to block up cone position details figure in present invention guidance combustion chamber.Wherein, Lt is two venturi width, and θ is the stifled vertex of a cone Angle, α are the angle of flare of outlet.
Fig. 4 is the chemical reaction face of Combustion Flow Field.
Specific embodiment
Fig. 1, Fig. 2 and Fig. 3 are please referred to, discloses a kind of engine chamber 20 with guidance combustion chamber for the present invention.It is sub- Combustion punching press guidance combustion chamber 10 is installed on 20 inner port of supersonic speed combustion chamber, 30 downstream (close to the import 30 of engine chamber Place).Asia combustion punching press guidance combustion chamber is designed for axial symmetry, and the center line and supersonic combustion of sub- combustion punching press guidance combustion chamber Room center line is overlapped.The guidance combustion chamber includes the inner cavity 21 surrounded by lip cover 2, and compression cone 1 at lumen inlet is located at The stifled cone 5 in 21 exit of inner cavity.The compression cone 1 includes former and later two parts, and front is divided into cone 11, rear portion is divided into rotary table Body 12, and partially divide the cross section of connecting place maximum for area in entire compression cone with 12 front of round estrade after cone 11 Cross section.The front end of the cone 11 extends anteriorly out 21 inlet of inner cavity.Space between the lip cover 2 and round estrade 12 Expansion segment 3 is formed, and forms sub- combustion room 4 between compression cone 1 and stifled cone 5.
The front end of the stifled cone 5 is similarly cone 51, and 51 front end of cone of the stifled cone extends forwardly to inner cavity 21 It exports and forms gap between the outlet of inner cavity 21.
In the present embodiment, it flows into guidance combustion chamber flow and accounts for the 9% of total flow;It fires air intake duct and uses external pressure one in the Asia Grade compression, and external compression angle is 220;Lip cover one stage of compression, and lip cover compression angle is 110, the total shrinkage ratio of air intake duct is 2.0, interior Shrinkage ratio is 1.15, and expansion segment area expansion is than 1.63.Under the design point of free stream Mach number 3.1;The present invention is in design point (Ma3.1) air intake duct realizes shock wave sealing, venturi Mach 2 ship 1.5, self-starting Mach 2 ship 2.5.
For the configuration in order to easy to process, air intake duct benchmark molded line is all made of linear design in addition to inessential extra curvature.Asia combustion When combustion chamber being guided to work normally, pressure and temperature is all very high in air intake duct, one of pressure perturbation occurs in venturi downstream, surpasses Subsonic airflow is reduced to subsonic speed after the pressure perturbation wave, which further slows down to be pressurized in expansion segment rises Temperature participates in subsonic combustion in combustion chamber.
The truncation design of 1 tail portion of centerbody is second key point of the invention.In its tail portion, backward step downstream forms height The recirculating zone 23 of warm high pressure low speed, the revolution arrow mark of 23 part of recirculating zone indicates the reflux effect of fuel in this section in Fig. 2 Fruit, incendiary source of the fuel in this region spontaneous combustion as entire guidance combustion chamber are advantageous to guide the burning tissues of combustion chamber to create Condition.
In the guidance combustion chamber 10, stifled cone 5 plays the role of biggish.Since single sub- combustion guidance flame combustion chamber expands The ability of dissipating is low, so installing stifled cone additional in sub- combustion combustor tail to improve guidance combustion high temperature combustion gas in the expansion of supersonic speed combustion chamber Dissipate squeezing effect.As shown in figure 3, the taper angle theta of stifled cone 5 affects the performance of combustion chamber.As stifled cone cone angle increases, combustion chamber goes out Mouth total pressure recovery coefficient decline, diffusion of the guidance combustion chamber air-flow in bimodal combustion chamber increase.Comprehensively consider, selection is stifled Boring cone angle is 60 °.Guidance combustion chamber nozzle-divergence angle α affects the expansion ratio of jet pipe, and optimized selection α=0 ° conducts a research. The i.e. described lip cover 2 is located at the inside at chamber exit and forms inclined-plane 22, and the inclined-plane 22 is parallel with the stifled cone outer surface of cone, Shrinkage expansion runner is formd therebetween.Asia combustion room high temperature subsonic speed combustion gas flows through shrinkage expansion (Laval nozzle) runner acceleration To supersonic speed and at a certain angle to supersonic speed combustion chamber injection (black region among two white streamlines in Fig. 4).High-temperature fuel gas The wave system structure of a series of complex is produced with outside ultrasound stream mutual extrusion, can effectively enhance guidance combustion chamber air-flow Diffusion ratio, be conducive to the broken of fuel and blending.
Referring to Fig.2, devising axial symmetry Asia combustion punching press guidance combustion chamber using the above method tiltedly sprays scheme, it is imitative using three-dimensional True method has carried out analysis of flow characteristics to the present invention and former scheme and has carried out burning assessment.Simulation result shows energy of the present invention Anti-reflective pressure energy power, the effectively diffusion ratio of enhancing guidance combustion-gas flow are enough improved, is enhanced to peripheral main chamber supersonic flow It squeezes, and is successfully realized bimodal mixed firinor fuel burning.Correlation performance parameters are as shown in table 1, it can be seen that use in design point The combustion chamber maximum anti-reflective pressure energy power of the present invention program improves 33%, Diffusion of gas stream ratio A2/A1, A2/A041% is respectively increased, 24.3%.A0Area, A are captured for air intake duct1To guide combustor exit area of section, A2Most for guidance combustion chamber high temperature combustion gas Big expansion diffusion area.
The technical solution and prior art performance parameter of 1 the present embodiment of table compare
The present invention implement the technical solution method and approach it is very much, the above is only preferred implementation of the invention Mode.It should be pointed out that for those skilled in the art, without departing from the principle of the present invention, also Several improvement can be made, these improvement also should be regarded as protection scope of the present invention.Each composition portion being not known in the present embodiment The available prior art is divided to be realized.

Claims (5)

1. a kind of engine chamber with guidance combustion chamber, which is characterized in that the guidance combustion chamber is located at engine combustion Burn the inside of room and the entrance close to engine chamber;
The guidance combustion chamber includes the inner cavity surrounded by lip cover, compression cone at lumen inlet, at chamber exit Stifled cone;The compression cone includes former and later two parts, and front is divided into cone, rear portion is divided into round estrade, and part after cone The cross section of connecting place is divided to be the maximum cross section of area in entire compression cone with round estrade front;The front end of the cone It extends anteriorly out at lumen inlet;The front end of the stifled cone is similarly cone, and the cone front end of the stifled cone extends forward Enter chamber exit and forms gap between chamber exit.
2. the engine chamber with guidance combustion chamber according to claim 1, it is characterised in that: the guidance burning Room is designed for axial symmetry, and the center line of combustion chamber is guided to be overlapped with the center line of engine chamber.
3. the engine chamber with guidance combustion chamber according to claim 1 or 2, it is characterised in that: the lip cover Inside at chamber exit forms inclined-plane, and the inclined-plane is parallel with the stifled cone outer surface of cone.
4. the engine chamber with guidance combustion chamber according to claim 1, it is characterised in that: Asia combustion air intake duct is adopted With external pressure one stage of compression, and external compression angle is 220;Lip cover one stage of compression, and lip cover compression angle is 11 °.
5. the engine chamber with guidance combustion chamber according to claim 3, it is characterised in that: blocking up cone cone angle is 60°。
CN201811149358.5A 2018-09-29 2018-09-29 A kind of engine chamber with guidance combustion chamber Active CN109340818B (en)

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Publication number Priority date Publication date Assignee Title
CN110793062A (en) * 2019-10-30 2020-02-14 北京空天技术研究所 Scramjet engine and runner structure adopting central combustion
CN113432150B (en) * 2021-06-29 2022-04-22 中国人民解放军国防科技大学 Controllable flame stabilizer, engine and aircraft

Citations (5)

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Publication number Priority date Publication date Assignee Title
DE19813949A1 (en) * 1998-03-28 2000-02-10 Geb Hering Heise Aircraft jet engine uses an additional injection of water under high pressure into the combustion zone with the fuel/air mixture for increased thrust and with laser spark plugs for continuous combustion
CN1611761A (en) * 2003-10-31 2005-05-04 王德强 Super combustion pressed engine
CN104359125A (en) * 2014-10-30 2015-02-18 南京航空航天大学 Central igniting mechanism of combustor of scramjet engine
CN105736178A (en) * 2016-04-11 2016-07-06 清华大学 Combined cycle engine
CN207920737U (en) * 2017-12-29 2018-09-28 厦门大学 A kind of three power combination engines with super burn Yu the double combustion chambers Ya Ran

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JP3042304B2 (en) * 1994-06-21 2000-05-15 日産自動車株式会社 Propulsion device
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Publication number Priority date Publication date Assignee Title
DE19813949A1 (en) * 1998-03-28 2000-02-10 Geb Hering Heise Aircraft jet engine uses an additional injection of water under high pressure into the combustion zone with the fuel/air mixture for increased thrust and with laser spark plugs for continuous combustion
CN1611761A (en) * 2003-10-31 2005-05-04 王德强 Super combustion pressed engine
CN104359125A (en) * 2014-10-30 2015-02-18 南京航空航天大学 Central igniting mechanism of combustor of scramjet engine
CN105736178A (en) * 2016-04-11 2016-07-06 清华大学 Combined cycle engine
CN207920737U (en) * 2017-12-29 2018-09-28 厦门大学 A kind of three power combination engines with super burn Yu the double combustion chambers Ya Ran

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