CN109630314A - A kind of airbreathing motor cold starting system and cold start-up method - Google Patents
A kind of airbreathing motor cold starting system and cold start-up method Download PDFInfo
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- CN109630314A CN109630314A CN201811527829.1A CN201811527829A CN109630314A CN 109630314 A CN109630314 A CN 109630314A CN 201811527829 A CN201811527829 A CN 201811527829A CN 109630314 A CN109630314 A CN 109630314A
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- combustion chamber
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- 238000000034 method Methods 0.000 title claims description 8
- 239000000446 fuel Substances 0.000 claims abstract description 52
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 239000004449 solid propellant Substances 0.000 claims abstract description 12
- 238000001816 cooling Methods 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 37
- 239000002737 fuel gas Substances 0.000 claims description 29
- 239000003380 propellant Substances 0.000 claims description 18
- 239000007921 spray Substances 0.000 claims description 18
- 239000004215 Carbon black (E152) Substances 0.000 claims description 9
- 229930195733 hydrocarbon Natural products 0.000 claims description 9
- 150000002430 hydrocarbons Chemical class 0.000 claims description 8
- 239000003350 kerosene Substances 0.000 claims description 8
- 238000000354 decomposition reaction Methods 0.000 claims description 3
- 229910052784 alkaline earth metal Inorganic materials 0.000 claims description 2
- 150000001342 alkaline earth metals Chemical class 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims description 2
- 239000000126 substance Substances 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 5
- 239000002360 explosive Substances 0.000 description 3
- 108091053398 TRIM/RBCC family Proteins 0.000 description 2
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000011049 filling Methods 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- VGGSQFUCUMXWEO-UHFFFAOYSA-N Ethene Chemical compound C=C VGGSQFUCUMXWEO-UHFFFAOYSA-N 0.000 description 1
- 239000005977 Ethylene Substances 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- BLRPTPMANUNPDV-UHFFFAOYSA-N Silane Chemical compound [SiH4] BLRPTPMANUNPDV-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 229910000077 silane Inorganic materials 0.000 description 1
- -1 small molecule hydrocarbon Chemical class 0.000 description 1
- 238000002910 structure generation Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 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
- F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
本发明涉及一种吸气式发动机冷启动系统，为了消除现有发动机所采用的易燃物质引导燃料点火燃烧预热的冷启动结构及气态燃料燃烧预热的冷启动结构所存在的使用安全隐患，本发明的冷启动系统包括燃气发生器、燃气分配阀及开口于燃烧室内壁且位于燃烧室前端的至少一个第一燃料喷注器；燃气发生器包括依次连接的气体发生装置、冷却装置及过滤器；气体发生装置包括燃料腔及发生器点火器，燃料腔装有固体燃料，发生器点火器用于固体燃料的点燃；燃气分配阀的入口与过滤器的出口连接，燃气分配阀设置有与第一燃料喷注器一一对应的至少一个出口，燃气分配阀的出口与第一燃料喷注器分别连接。
The invention relates to a cold start system for an air-breathing engine, in order to eliminate the potential safety hazard existing in the cold start structure in which flammable substances guide the ignition, combustion and preheating of fuel and the cold start structure in which gaseous fuel is burned and preheated. , the cold start system of the present invention comprises a gas generator, a gas distribution valve and at least one first fuel injector opened on the inner wall of the combustion chamber and located at the front end of the combustion chamber; the gas generator comprises a gas generating device, a cooling device and a filter; the gas generating device includes a fuel cavity and a generator igniter, the fuel cavity is filled with solid fuel, and the generator igniter is used for igniting the solid fuel; the inlet of the gas distribution valve is connected with the outlet of the filter, and the gas distribution valve is provided with a At least one outlet of the first fuel injector is in one-to-one correspondence, and the outlet of the gas distribution valve is respectively connected with the first fuel injector.
Description
Technical field
The invention belongs to rocket punching press combined engine field, it is related to a kind of airbreathing motor cold starting system and cold opens
Dynamic method.
Background technique
Ma7 scramjet engine below and RBCC engine are usually using kerosene or Endothermic Hydrocarbon Fuel as combustion
Material.Before engine cold-start, fuel is in normal temperature state, and the igniting and burning tissues difficulty under the conditions of Supersonic Stream are larger.
Currently, engine cold-start generallys use the side that combustible material guidance fuel ignition burning or preheated with other gaseous fuel combustions
Case.Wherein, the cold start-up scheme of combustible material guidance fuel ignition burning is usually using gaseous states flammable and explosive substances such as silane,
With very big security risk, it is mainly used in ground experiment and flying demonstration test, does not have engineer application precedent still；Use other
The cold start-up scheme of gaseous fuel combustion preheating, can be improved fuel temperature, is obviously improved the blending of fuel and combustion characteristics,
But used fuel gas is usually the explosion hazard gases of ethylene etc, and is stored in high pressure gas cylinder, closes on to be hypersonic
The storage and use of spacecraft bring security risk.
Therefore, one kind is developed to store for a long time, is very necessary using safe high-speed suction formula engine cold-start system.
Summary of the invention
To eliminate the cold start-up structure and gas that combustible material used by available engine guides fuel ignition burning preheating
The cold start-up structure of state fuel combustion preheating is existing to use security risk, improves maintainability, the reliability of engine, the present invention
It provides using a kind of high-speed suction formula engine cold-start system and cold start-up side for generating fuel gas using gas generator
Method.
The technical solution of the invention is as follows:
A kind of airbreathing motor cold starting system is characterized in that including gas generator 2, fuel gas distributing valve 5
And it is opened on 16 inner wall of combustion chamber and is located at least one first propellant spray device 18 of 16 front end of combustion chamber；
The gas generator 2 includes sequentially connected gas generating unit, cooling device 3 and filter 4；
The gas generating unit includes fuel cavity and generator igniter 1, and the fuel cavity is equipped with solid fuel, described
Generator igniter 1 is lighted for solid fuel；
The entrance of the fuel gas distributing valve 5 is connect with the outlet of filter 4, and the fuel gas distributing valve 5 is provided with and first
At least one the one-to-one outlet of propellant spray device 18, the outlet of the fuel gas distributing valve 5 divides with the first propellant spray device 18
It does not connect.
Further, solid fuel is the solid mixt fuel comprising alkaline-earth metal.
Further, the generator igniter 1 is thunder cartridge.
Meanwhile the present invention also provides a kind of starting method of airbreathing motor cold starting system, special character exists
In, comprising the following steps:
1) it fills
Before the engine is started up, engine fuel is fills up in the heat exchanger channels 14 of engine wall surface；
2) it preheats
2.1) so that the solid fuel in gas generating unit is decomposed, decomposition product is cooled down and filtered, is obtained
Fuel gas simultaneously passes through Pipeline transport to the first propellant spray device 18；
2.2) fuel gas is fed combustion chamber 16 by the first propellant spray device 18；
2.3) engine ignition lights fuel gas, using burn caused by heat persistently to engine wall surface into
Row heating, until kerosene or Endothermic Hydrocarbon Fuel meet engine combustion tissue needs in engine wall surface heat exchanger channels 14；
3) start
The supply of fuel gas is cut off, while feeding the kerosene or Endothermic Hydrocarbon Fuel after preheating, hair to combustion chamber 16
Motivation igniter completes fuel combustion, engine cold-start.
Advantage is the present invention compared with prior art:
1, airbreathing motor cold starting system of the present invention generates the structure generation of high-temperature gas fuel using gas generator
For the existing flammable explosive gas structure directlyed adopt, eliminates and directly adopt flammable explosive gas as present in preheating gas
Security risk, have working service easy, securely and reliably, the advantages of capable of storing for a long time.
2, airbreathing motor cold starting system of the present invention, it is cold especially suitable for scramjet engine and RBCC engine
Activation system also can be used as the cold starting system of other dynamical systems for needing fuel preheating.
Detailed description of the invention
Fig. 1 is the airbreathing motor schematic illustration using airbreathing motor cold starting system of the present invention.
Fig. 2 is the enlarged drawing in Fig. 1 at heat exchanger channels.
Wherein appended drawing reference are as follows: 1- generator igniter, 2- gas generator 2,3- cooling device 3,4- filter 4,5-
Fuel gas distributing valve 5,6- shut-off valve, 7- control unit, 8- pump, 9- fuel-dispensing valve, 10- fuel tank, 11- pressure reducer, 12- gas
Bottle, 13- jet pipe, 14- heat exchanger channels, the second propellant spray of 15- device, 17- third propellant spray device, 18- the first propellant spray device,
The combustion chamber 16-, 19- gas handling system.
Specific embodiment
Below in conjunction with attached drawing, the present invention is described in detail.
Fig. 1 shows the air flow channel of airbreathing motor and engine controls and supply system, engine control therein
System and supply system include fuel system, cold starting system and control unit 7, and air flow channel therein includes setting gradually
Gas handling system 19, combustion chamber 16 and jet pipe 13, be provided with heat exchanger channels 14 (as shown in Figure 2) in engine wall surface.Air inlet system
What system 19 entered is air.Cold starting system includes gas generator 2, fuel gas distributing valve 5 and fuel gas pipeline, combustion gas hair therein
Raw device 2 includes gas generating unit, cooling device 3 and filter 4, and gas generating unit includes fuel cavity and generator igniter
1, fuel cavity is equipped with solid fuel, and generator igniter 1 is lighted for solid fuel；The entrance and fuel cavity of cooling device 3
Gas outlet connection, the outlet of cooling device 3 connect with the entrance of filter 4, and the outlet of filter 4 passes through fuel gas pipeline company
It is connected to the first propellant spray device 18；First propellant spray device 18 is located in combustion chamber 16, for fuel gas to be fed combustion chamber
16.Fuel system therein includes sequentially connected gas cylinder 12, pressure reducer 11, fuel tank 10 and pump 8, is come out from pump 8
Fuel send through shut-off valve 6 to heat exchanger channels 14 and preheated, the fuel for preheating out is divided into multichannel through fuel-dispensing valve 9 again,
It burns respectively through being sent into combustion chamber 16 through the second propellant spray device 15 and third propellant spray device 17 again per fuel all the way.This hair
Bright middle gas generator 2, fuel gas distributing valve 5 and fuel-dispensing valve 9 are controlled by control unit 7.
Engine uses kerosene or Endothermic Hydrocarbon Fuel for fuel, before the engine is started up, fuel filling to engine
In the heat exchanger channels 14 of wall surface；Engine cold-start uses the scheme of gaseous fuel combustion preheating, and cold starting system includes combustion gas
Generator 2, fuel gas distributing valve 5, the first propellant spray device 18 composition；Gas generator 2 is according to default regime decomposition, by life
At object cooling and filtering, about 600 DEG C of temperature of fuel gas is generated, gaseous state ejector filler is assigned to by fuel gas distributing valve 5 and is fed
Combustion chamber 16；High-temperature gas fuel is mainly made of hydrogen and small molecule hydrocarbon etc., and ignition delay time is short, self-ignition point
Low, engine ignition lights fuel gas, persistently heats to engine wall surface, until kerosene or the hydrocarbon combustion of heat absorbing type
Material meets engine combustion tissue needs；Fuel gas is cut off by control unit 7, while feeding the kerosene after preheating or heat absorption
Type hydrocarbon fuel realizes engine fuel switching, completes engine cold-start process.
According to the corresponding engine excess air coefficient of engine cold-start state, the working condition of gas generator 2 is determined；Root
According to engine fuel preheating temperature and burning and heat transfer coupling analysis data, when determining that burning preheating and gas generator 2 work
Between index；According to 2 index of gas generator of above-mentioned determination, gas generator 2 is designed and tested, obtains factor of created gase, gas temperature
Degree, gas-composition data；Pipeline between coordinate design gas generator 2,5 ejector filler of fuel gas distributing valve meets flow resistance requirement
With anti-heat request, cold starting system is formed；Engine control system coordinated control cold starting system and engine fuel are pressurized, quasi-
The really work of control cold starting system and fuel filling, preheating, the sequential relationship between switching.
Claims (4)
1. a kind of airbreathing motor cold starting system, it is characterised in that: including gas generator (2), fuel gas distributing valve (5) and
It is opened on combustion chamber (16) inner wall and is located at least one first propellant spray device (18) of combustion chamber (16) front end；
The gas generator (2) includes sequentially connected gas generating unit, cooling device (3) and filter (4)；
The gas generating unit includes fuel cavity and generator igniter (1), and the fuel cavity is equipped with solid fuel, the hair
Raw device igniter (1) is lighted for solid fuel；
The entrance of the fuel gas distributing valve (5) is connect with the outlet of filter (4), and the fuel gas distributing valve (5) is provided with and the
At least one the one-to-one outlet of one propellant spray device (18), the outlet of the fuel gas distributing valve (5) and the first propellant spray
Device (18) is separately connected.
2. airbreathing motor cold starting system according to claim 1, it is characterised in that:
Solid fuel is the solid mixt fuel comprising alkaline-earth metal.
3. airbreathing motor cold starting system according to claim 2, it is characterised in that:
The generator igniter (1) is thunder cartridge.
4. a kind of starting method of airbreathing motor cold starting system, which comprises the following steps:
1) it fills
Before the engine is started up, engine fuel is fills up in the heat exchanger channels (14) of engine wall surface；
2) it preheats
2.1) so that the solid fuel in gas generating unit is decomposed, decomposition product is cooled down and filtered, gaseous state is obtained
Fuel simultaneously passes through Pipeline transport to the first propellant spray device (18)；
2.2) fuel gas is fed combustion chamber (16) by the first propellant spray device (18)；
2.3) engine ignition lights fuel gas, and using burning, generated heat persistently adds engine wall surface
Heat, until the interior kerosene of engine wall surface heat exchanger channels (14) or Endothermic Hydrocarbon Fuel meet engine combustion tissue needs；
3) start
The supply of fuel gas is cut off, while feeding the kerosene or Endothermic Hydrocarbon Fuel after preheating to combustion chamber (16), is started
Machine igniter completes fuel combustion, engine cold-start.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811527829.1A CN109630314B (en) | 2018-12-13 | 2018-12-13 | Cold start system and cold start method for air-breathing engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811527829.1A CN109630314B (en) | 2018-12-13 | 2018-12-13 | Cold start system and cold start method for air-breathing engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109630314A true CN109630314A (en) | 2019-04-16 |
| CN109630314B CN109630314B (en) | 2020-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811527829.1A Active CN109630314B (en) | 2018-12-13 | 2018-12-13 | Cold start system and cold start method for air-breathing engine |
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| Country | Link |
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| CN (1) | CN109630314B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111636966A (en) * | 2020-05-28 | 2020-09-08 | 清华大学 | Engine and its cooling system |
| CN112664352A (en) * | 2020-12-29 | 2021-04-16 | 上海空间推进研究所 | Solid-liquid mixed type fuel gas pressurization system and control method thereof |
| CN112816218A (en) * | 2021-01-07 | 2021-05-18 | 中国人民解放军国防科技大学 | Rich fuel gas generation control system and control method |
| CN112901353A (en) * | 2021-02-01 | 2021-06-04 | 中国科学院力学研究所 | System and method for starting ramjet engine through active cooling of hydrocarbon fuel and scramjet engine |
| CN113154448A (en) * | 2021-04-30 | 2021-07-23 | 西安航天动力研究所 | Device for fuel injection and flame stabilization of supersonic combustion chamber of ramjet engine |
| CN114109651A (en) * | 2021-11-09 | 2022-03-01 | 宁波天擎航天科技有限公司 | Solid fuel rocket combined ramjet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111636966A (en) * | 2020-05-28 | 2020-09-08 | 清华大学 | Engine and its cooling system |
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| CN112901353A (en) * | 2021-02-01 | 2021-06-04 | 中国科学院力学研究所 | System and method for starting ramjet engine through active cooling of hydrocarbon fuel and scramjet engine |
| CN113154448A (en) * | 2021-04-30 | 2021-07-23 | 西安航天动力研究所 | Device for fuel injection and flame stabilization of supersonic combustion chamber of ramjet engine |
| CN113154448B (en) * | 2021-04-30 | 2022-07-19 | 西安航天动力研究所 | Device for fuel injection and flame stabilization of supersonic combustion chamber of ramjet engine |
| CN114109651A (en) * | 2021-11-09 | 2022-03-01 | 宁波天擎航天科技有限公司 | Solid fuel rocket combined ramjet engine |
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| CN109630314B (en) | 2020-06-30 |
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