CN108999726A - A kind of punching engine of the preparatory high speed atomisation of liquid aviation kerosine - Google Patents

A kind of punching engine of the preparatory high speed atomisation of liquid aviation kerosine Download PDF

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Publication number
CN108999726A
CN108999726A CN201810502304.6A CN201810502304A CN108999726A CN 108999726 A CN108999726 A CN 108999726A CN 201810502304 A CN201810502304 A CN 201810502304A CN 108999726 A CN108999726 A CN 108999726A
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China
Prior art keywords
wall surface
spreader
high speed
combustion chamber
intake duct
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CN201810502304.6A
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Chinese (zh)
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CN108999726B (en
Inventor
赵永胜
欧平
张江
吴军飞
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China Academy of Aerospace Aerodynamics CAAA
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China Academy of Aerospace Aerodynamics CAAA
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K7/00Plants 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
    • F02K7/10Plants 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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • F02K1/82Jet pipe walls, e.g. liners
    • 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
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

The invention discloses a kind of punching engines of preparatory high speed atomisation of liquid aviation kerosine, comprising: spreader, air intake duct wall surface, combustion chamber wall surface, jet pipe wall surface, fuel reserve tank and petroleum pipeline;Wherein, the spreader is connected by the petroleum pipeline with the fuel reserve tank;The air intake duct wall surface, the combustion chamber wall surface and the jet pipe wall surface are sequentially connected and connect;The spreader and the fuel reserve tank are set in the cavity that the air intake duct wall surface, the combustion chamber wall surface and the jet pipe wall surface are formed as a part;Air intake duct is formed between the spreader and the air intake duct wall surface, combustion chamber runner is formed between the spreader and the combustion chamber wall surface, jet pipe runner is formed between the spreader and the jet pipe wall surface, the air intake duct, the combustion chamber runner and the jet pipe runner are sequentially connected logical;Air inlet is offered at the top of the spreader.The present invention improves punching engine economy and safety.

Description

A kind of punching engine of the preparatory high speed atomisation of liquid aviation kerosine
Technical field
The invention belongs to a kind of punching press of punching engine field more particularly to preparatory high speed atomisation of liquid aviation kerosine hairs Motivation.
Background technique
With the continuous improvement required aircraft speed, traditional turbojet is had been unable to meet to thrust Demand.And punching engine does not have the rotatable parts such as compressor, turbine, it is to utilize high speed incoming flow stagnation in air intake duct, will Kinetic energy is converted into pressure energy, completes compression process.Therefore punching engine is big with its thrust ratio, component is simple and supersonic speed flies The features such as economic performance is good when row becomes the first choice of supersonic and hypersonic aircraft.
Punching engine mostly uses solid fuel at present, and the control of such engine is difficult, and the working time is limited, solid simultaneously Fluid fuel storage is difficult, and cost is high;Using liquid hydrogen as the punching engine of fuel, security performance is very limited again.Aviation Kerosene is that a kind of calorific value is high, storage is simple, security performance is high and the fuel of good economy performance.But the burning of liquid aviation kerosine is anti- It should need just to can be carried out after overspray, broken, atomization and evaporation, while the ignition delay time of liquid aviation kerosine is also opposite It is longer, and air velocity is exceedingly fast in scramjet combustor, therefore the residence time of fuel is extremely short, which limits aviation coals Application of the oil in punching engine, increases design difficulty.
Summary of the invention
Technical problem solved by the present invention is it is preparatory to have overcome the deficiencies of the prior art and provide a kind of liquid aviation kerosine The punching engine of high speed atomisation, the operating mode of preparatory high speed atomisation improve punching engine economy and safety.
The object of the invention is achieved by the following technical programs: a kind of punching press of the preparatory high speed atomisation of liquid aviation kerosine Engine, comprising: spreader, air intake duct wall surface, combustion chamber wall surface, jet pipe wall surface, fuel reserve tank and petroleum pipeline;Wherein, described Spreader is connected by the petroleum pipeline with the fuel reserve tank;The air intake duct wall surface, the combustion chamber wall surface and the tail Jet pipe wall surface, which is sequentially connected, to be connect;The spreader and the fuel reserve tank are set to the air intake duct wall surface, described as a part In the cavity that combustion chamber wall surface and the jet pipe wall surface are formed;Air inlet is formed between the spreader and the air intake duct wall surface Road, forms combustion chamber runner between the spreader and the combustion chamber wall surface, the spreader and the jet pipe wall surface it Between formed jet pipe runner, the air intake duct, the combustion chamber runner and the jet pipe runner are sequentially connected logical;The shunting Air inlet is offered at the top of cone.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, the spreader includes cone wall and fuel spray Change device;Wherein, the tip of the cone wall offers several air inlets;The inside of the cone wall forms air collecting chamber;The cone wall Be internally provided with fuel atomizer, the cone wall offers direct-injection type spray orifice corresponding with fuel atomizer, the fuel oil Atomizer is connected by direct-injection type spray orifice with combustion chamber runner;The fuel atomizer passes through the petroleum pipeline and the oil storage Case is connected.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, the fuel atomizer includes several drawings Wa Er jet pipe;Wherein, the quantity of the direct-injection type spray orifice is consistent with the quantity of the Laval nozzle;Each Laval nozzle A circular radius is constituted, one end of each Laval nozzle is located at center location;Each Laval nozzle with it is corresponding Direct-injection type spray orifice is connected.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, the Fighter Inlet Mach 2 ship 2~ 5, the fuel oil of direct-injection type spray orifice injection and the ratio of momentum of the air in the runner of combustion chamber are 10~100.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, the diameter of phi a and jet pipe wall of air intake duct The ratio between face outer diameter Φ b is 0.5~0.8;The ratio between length Lb of air intake duct length La and combustion chamber runner is 0.65~0.95.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, the ratio between air inlet and direct-injection type injection diameter It is 5~10.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, spreader angle, θ is 15 °~30 °.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, air intake duct throat area Sa and jet pipe stream The ratio between road throat area Sb is 0.45~0.85.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, Laval nozzle inlet diameter Φ c and drawing The ratio between Wa Er jet pipe throat diameter of phi d is 1.5~2;The ratio between Laval nozzle length Lc and Laval nozzle inlet diameter Φ c is 3.5~4.5.
In the punching engine of the above-mentioned preparatory high speed atomisation of liquid aviation kerosine, petroleum pipeline diameter of phi e and Laval nozzle The ratio between throat diameter of phi d is 1~1.2.
Compared with prior art, the present invention has the following advantages:
(1) present invention forms high pressure origin using air collecting chamber come sluggish air, and configuration is simple, can make full use of and Flow high-speed air.
(2) present invention makes liquid fuel high speed atomisation using Laval nozzle, greatly shortens the igniting of fuel oil Delay time and residence time in combustion chamber.
(3) the liquid aviation kerosine being atomized in advance injection combustion chamber is just participated in burning instead using direct-injection type spray orifice by the present invention It answers, improves efficiency of combustion and combustion stability.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the structural representation of the punching engine of the preparatory high speed atomisation of liquid aviation kerosine provided in an embodiment of the present invention Figure;
Fig. 2 is the structural schematic diagram of fuel atomizer provided in an embodiment of the present invention;
Fig. 3 is the cross-sectional view of Laval nozzle and petroleum pipeline provided in an embodiment of the present invention relative position.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure It is fully disclosed to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the structural representation of the punching engine of the preparatory high speed atomisation of liquid aviation kerosine provided in an embodiment of the present invention Figure.As shown in Figure 1, the punching engine of the preparatory high speed atomisation of liquid aviation kerosine include: spreader 1, air intake duct wall surface 3, Combustion chamber wall surface 4, jet pipe wall surface 5, fuel reserve tank 6 and petroleum pipeline 14;Wherein,
Spreader 1 is connected by petroleum pipeline 14 with fuel reserve tank 6;Air intake duct wall surface 3, combustion chamber wall surface 4 and jet pipe wall Face 5, which is sequentially connected, to be connect;Spreader 1 and fuel reserve tank 6 are used as a part to be set to air intake duct wall surface 3, the combustion chamber wall surface 4 and tail In the cavity that jet pipe wall surface 5 is formed;Air intake duct 10, spreader 1 and chamber wall are formed between spreader 1 and air intake duct wall surface 3 Combustion chamber runner 8 is formed between face 4, and jet pipe runner 7, air intake duct 10, burning are formed between spreader 1 and jet pipe wall surface 5 Room runner 8 and jet pipe runner 7 are sequentially connected logical;The top of spreader 1 offers air inlet 2.
Spreader 1 includes cone wall 12 and fuel atomizer 15;Wherein, the tip for boring wall 12 offers several air inlets 2; The inside for boring wall 12 forms air collecting chamber 11;Cone wall 12 is internally provided with fuel atomizer 15, and cone wall 12 offers and fuel spray Change the corresponding direct-injection type spray orifice 9 of device 15, fuel atomizer 15 is connected by direct-injection type spray orifice 9 with combustion chamber runner 8;Fuel oil Atomizer 15 is connected by petroleum pipeline 14 with fuel reserve tank 6.
Fig. 2 is the structural schematic diagram of fuel atomizer provided in an embodiment of the present invention.As shown in Fig. 2, the fuel atomizer 15 include several Laval nozzles 13;Wherein, the quantity of direct-injection type spray orifice 9 is consistent with the quantity of Laval nozzle 13;Often A Laval nozzle 13 constitutes a circular radius, and one end of each Laval nozzle 13 is located at center location;Each Bearing score You are connected jet pipe 13 with corresponding direct-injection type spray orifice 9.
Incoming air shunts after the rectification of spreader 1, respectively enters air inlet 2 and air intake duct 10;Into air inlet 2 Air-flow slows down in air collecting chamber 11 after pressurization, and into fuel atomizer 15, air-flow is again speeded up, the fuel oil in fuel reserve tank 6, warp It crosses petroleum pipeline 14 and enters fuel atomizer 15, by the air-flow quick break after the acceleration of Laval nozzle 13, then from direct-injection type Spray orifice 9 injects combustion chamber runner 8;Fuel oil after atomization is blended with by the pressurized air-flow of air intake duct 10, and is being burnt Combustion reaction occurs in room runner 8, the combustion gas of the high temperature and pressure of generation sprays by jet pipe runner 7, realizes fuel oil and firing It burns residence time in room greatly to shorten, improves efficiency of combustion and combustion stability.
Wherein 10 inflow Mach number of air intake duct is 2~5, the sky in fuel oil and combustion chamber runner 8 that direct-injection type spray orifice 9 injects The ratio of momentum of gas is 10~100;The ratio between air intake duct diameter of phi a and jet pipe casing outer diameter Φ b are 0.5~0.8;Air intake duct length The ratio between La and chamber length Lb are 0.65~0.95;Air inlet 2 and 9 diameter ratio of direct-injection type spray orifice are 5~10;Shunt cone angle Spending θ is 15 °~30 °;The ratio between air intake duct throat area Sa and jet pipe throat area Sb are 0.45~0.85.
As shown in Fig. 2, fuel atomizer 15 is made of 6 Laval nozzles 13.
As shown in figure 3, the ratio between Laval nozzle inlet diameter Φ c and Laval nozzle throat diameter of phi d are 1.5~2;It draws The ratio between Wa Er jet pipe length Lc and Laval nozzle inlet diameter Φ c are 3.5~4.5;Petroleum pipeline diameter of phi e and Laval nozzle The ratio between throat diameter of phi d is 1~1.2, to guarantee that liquid aviation kerosine can be by high speed atomisation.
The present embodiment, come sluggish air, forms high pressure origin, configuration is simple, can make full use of incoming flow using air collecting chamber High-speed air;The present embodiment makes liquid fuel high speed atomisation using Laval nozzle, greatly shortens the igniting of fuel oil Delay time and residence time in combustion chamber;The present embodiment is infused the liquid aviation kerosine being atomized in advance using direct-injection type spray orifice Enter combustion chamber and just participate in combustion reaction, improves efficiency of combustion and combustion stability.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.

Claims (10)

1. a kind of punching engine of the preparatory high speed atomisation of liquid aviation kerosine, characterized by comprising: spreader (1), air inlet Road wall surface (3), combustion chamber wall surface (4), jet pipe wall surface (5), fuel reserve tank (6) and petroleum pipeline (14);Wherein,
The spreader (1) is connected by the petroleum pipeline (14) with the fuel reserve tank (6);
The air intake duct wall surface (3), the combustion chamber wall surface (4) and the jet pipe wall surface (5) are sequentially connected and connect;
The spreader (1) and the fuel reserve tank (6) are used as a part to be set to the air intake duct wall surface (3), the combustion chamber In the cavity that wall surface (4) and the jet pipe wall surface (5) are formed;
Air intake duct (10) are formed between the spreader (1) and the air intake duct wall surface (3), the spreader (1) and the combustion It burns and forms combustion chamber runner (8) between locular wall face (4), form tail spray between the spreader (1) and the jet pipe wall surface (5) Pipe runner (7), the air intake duct (10), the combustion chamber runner (8) and the jet pipe runner (7) are sequentially connected logical;
Air inlet (2) are offered at the top of the spreader (1).
2. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 1, it is characterised in that: described Spreader (1) includes cone wall (12) and fuel atomizer (15);Wherein,
The tip of cone wall (12) offers several air inlets (2);The inside of cone wall (12) forms air collecting chamber (11);
Cone wall (12) is internally provided with fuel atomizer (15), and the cone wall (12) offers and fuel atomizer (15) Corresponding direct-injection type spray orifice (9), the fuel atomizer (15) are connected by direct-injection type spray orifice (9) with combustion chamber runner (8) It is logical;
The fuel atomizer (15) is connected by the petroleum pipeline (14) with the fuel reserve tank (6).
3. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: described Fuel atomizer (15) includes several Laval nozzles (13);Wherein,
The quantity of the direct-injection type spray orifice (9) is consistent with the quantity of the Laval nozzle (13);
Each Laval nozzle (13) constitutes a circular radius, and one end of each Laval nozzle (13) is located at center of circle position It sets;
Each Laval nozzle (13) is connected with corresponding direct-injection type spray orifice (9).
4. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: described Air intake duct (10) inflow Mach number is 2~5, the fuel oil of direct-injection type spray orifice (9) injection and moving for the air in combustion chamber runner (8) Amount is than being 10~100.
5. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: air inlet The ratio between diameter of phi a and jet pipe wall surface outer diameter the Φ b in road is 0.5~0.8;The length Lb of air intake duct length La and combustion chamber runner The ratio between be 0.65~0.95.
6. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: air inlet Hole (2) and direct-injection type spray orifice (9) diameter ratio are 5~10.
7. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: shunt Coning angle θ is 15 °~30 °.
8. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 2, it is characterised in that: air inlet The ratio between road throat area Sa and jet pipe runner throat area Sb are 0.45~0.85.
9. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 3, it is characterised in that: Bearing score Your the ratio between nozzle inlet diameter of phi c and Laval nozzle throat diameter of phi d are 1.5~2;Laval nozzle length Lc and Lavalle The ratio between nozzle inlet diameter of phi c is 3.5~4.5.
10. the punching engine of the preparatory high speed atomisation of liquid aviation kerosine according to claim 3, it is characterised in that: defeated The ratio between tubing diameter Φ e and Laval nozzle throat diameter of phi d are 1~1.2.
CN201810502304.6A 2018-05-23 2018-05-23 Ramjet engine with liquid aviation kerosene atomized at high speed in advance Active CN108999726B (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109595078A (en) * 2018-12-27 2019-04-09 中国人民解放军总参谋部第六十研究所 A kind of water injection structure for turbojet engine
CN113967806A (en) * 2021-10-28 2022-01-25 湖北三江航天江北机械工程有限公司 Welding deformation control method for large-size shunt cone

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CN101576025A (en) * 2009-06-11 2009-11-11 北京航空航天大学 Multi-mode spraying pipe with adjustable throat for ramjet engine
CN103557716A (en) * 2013-09-27 2014-02-05 中国科学院力学研究所 Device for recycling high temperature kerosene of scramjet engine
CN104234867A (en) * 2013-06-13 2014-12-24 陶财德 Scramjet engine
CN104819484A (en) * 2015-04-20 2015-08-05 北京航空航天大学 Evaporation type flame stabilizer of radial ignition
CN205076051U (en) * 2015-05-26 2016-03-09 吴畏 Hypersonic vehicle
CN205449923U (en) * 2016-03-10 2016-08-10 北京理工大学 A combustion system for simulating punching press engine
CN106050471A (en) * 2016-06-13 2016-10-26 南京理工大学 Pre-atomization ignition device used for liquid fuel ramjet engine
US20160377028A1 (en) * 2013-05-07 2016-12-29 Reaction Systems, Llc Catalytic n2o pilot ignition system for upper stage scramjets

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101576025A (en) * 2009-06-11 2009-11-11 北京航空航天大学 Multi-mode spraying pipe with adjustable throat for ramjet engine
US20160377028A1 (en) * 2013-05-07 2016-12-29 Reaction Systems, Llc Catalytic n2o pilot ignition system for upper stage scramjets
CN104234867A (en) * 2013-06-13 2014-12-24 陶财德 Scramjet engine
CN103557716A (en) * 2013-09-27 2014-02-05 中国科学院力学研究所 Device for recycling high temperature kerosene of scramjet engine
CN104819484A (en) * 2015-04-20 2015-08-05 北京航空航天大学 Evaporation type flame stabilizer of radial ignition
CN205076051U (en) * 2015-05-26 2016-03-09 吴畏 Hypersonic vehicle
CN205449923U (en) * 2016-03-10 2016-08-10 北京理工大学 A combustion system for simulating punching press engine
CN106050471A (en) * 2016-06-13 2016-10-26 南京理工大学 Pre-atomization ignition device used for liquid fuel ramjet engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109595078A (en) * 2018-12-27 2019-04-09 中国人民解放军总参谋部第六十研究所 A kind of water injection structure for turbojet engine
CN113967806A (en) * 2021-10-28 2022-01-25 湖北三江航天江北机械工程有限公司 Welding deformation control method for large-size shunt cone

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