CN108561244B - The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist - Google Patents
The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist Download PDFInfo
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- CN108561244B CN108561244B CN201711479801.0A CN201711479801A CN108561244B CN 108561244 B CN108561244 B CN 108561244B CN 201711479801 A CN201711479801 A CN 201711479801A CN 108561244 B CN108561244 B CN 108561244B
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- combustion chamber
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- super burn
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- 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
- F02K7/16—Composite ram-jet/turbo-jet engines
-
- 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
- F02K7/14—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 with external combustion, e.g. scram-jet engines
-
- 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
Abstract
The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist, are related to combined engine.Overall performance requirement is formulated according to aerial mission, design basic flow field is required based on overall performance, and then obtain rotating into air flue in three-dimensional by streamlined impeller；Air passage outlet is rotated into three-dimensional, and super burn combustion chamber inlet and outlet parameter is obtained according to engine overall performance, designs super burn combustion chamber；Before super burn entry of combustion chamber, Rocket ejector channel of corresponding size is arranged based on the engine thrust requirements of Ma2~5, including center cone, rocket engine and sub- combustion combustion chamber；According to the stage engine flow demand of Ma0~2, flow formula is utilizedTurbine channel inlet area is calculated, air flue upper wall surface opening is rotated into three-dimensional, arranges turbine channel；Super burn combustor exit and turbine channel outlet are being stated, is arranging the adjustable common nozzle of geometric area, and flow distribution plate is designed according to jet pipe different working condition.
Description
Technical field
The present invention relates to combined engine, three power combinations coexisted more particularly, to a kind of super burn and sub- combustion combustion chamber are sent out
Motivation design method.
Background technique
Hypersonic flight is known as promoting the third time after flight and jet-propulsion flight in aviation history after propeller
" revolution " is commanding elevation ([1] Wang Xuhao, Wang Wenfa, Wang Zhaolei hypersonic flight of 21 century Aeronautics and Astronautics science and technology
The characteristics of device and its influence [J] cruising missile to future war, 2011 (5): 26-28.).Currently, re-entry space vehicle
Art study frontier hot spot, which is being turned to from the development of scramjet engine, can be realized horizontal take-off, independently accelerates to high ultrasound
Speed combined dynamic system development (the big sound of [2] Liu, Chen Guang .21 century aero-engine (under) [J] aviation knowledge, 2004
(6):34-37).Wherein turbine base assembly power has become the development emphasis of assembly power.Turbine base assembly power TBCC be with
Based on low speed (Ma0~Ma2) turbogenerator, the high ultrasound in the fast domain of the width that integrated high-speed (Ma3~Ma8) punching engine is formed
Powertrain system.The advantages such as it has than leaping high, flying speed range is wide, reuses, be All Speed Range hypersonic flight most
For ideal aviation power propulsion system ([3] Wang Fang, Gao Shuanlin hypersonic cruise missile ideal power system --- TBCC
Engine and its key technology [J] cruising missile, 2007 (11): 49-53).
But in 2~3 range of Mach, there are turbogenerator work Mach number " not increasing ", punching press for TBCC dynamical system
The problem of engine operation Mach number " being unable to come down "；And it is difficult to meet aircraft thrust in mode conversion process TBCC dynamical system
Demand falls into " the thrust wide gap " for being difficult to go beyond.In addition, sub- burning ramjet work Mach number concentrates on Ma3-5 at this stage,
Scramjet engine work Mach 2 ship Ma5-8.To realize the punching engine work within the scope of Ma3-8 speed domain, at this stage
Major measure be using Dual-mode Scramjet, be subsonic speed in Ma3-5 state combustion chamber inflow Mach number,
The above are supersonic speed by Ma5.However Dual-mode Scramjet technical maturity is lower at present, and farther out from engineering practice.
Summary of the invention
It the problem of it is an object of the invention to for turbine-punching press, sub- combustion-super burn mode conversion process, provides
Rocket carries out turbine-punching press thrust bridge joint, super burn coexists with sub- combustion combustion chamber a kind of super burn and Asia combustion combustion chamber is introduced to coexist
Three power combination engine design methods.
The three power combination engines that the super burn and sub- combustion combustion chamber coexist are logical equipped with air flue, turbine is rotated into three-dimensional
Road, ram rocket channel and jet pipe；The turbine channel and ram rocket channel, which share in a three-dimensional, rotates into air flue and tail
Jet pipe；The ram rocket channel is equipped with punching press channel and Rocket ejector channel, and the Rocket ejector channel is equipped with sub- combustion burning
Room, the punching press channel and Rocket ejector channel outlet are connected to a shared super burn combustion chamber.
The present invention the following steps are included:
1) overall performance requirement is formulated according to aerial mission, design basic flow field is required based on overall performance, and then pass through
Streamlined impeller obtains rotating into air flue in three-dimensional；
2) air passage outlet is rotated into the step 1) three-dimensional, the disengaging of super burn combustion chamber is obtained according to engine overall performance
Mouth parameter, designs super burn combustion chamber；
3) it before step 2) the super burn entry of combustion chamber, is arranged based on the engine thrust requirements of Ma2~5 of corresponding size
Rocket ejector channel, including center cone, rocket engine and sub- combustion combustion chamber；
4) according to the stage engine flow demand of Ma0~2, flow formula is utilizedCalculate turbine channel inlet face
Product, whereinIndicate that flow, ρ indicate density, A indicates that area, v indicate speed, rotates on air flue in the step 1) three-dimensional
Wall surface opening, arranges turbine channel；
5) in step 3) the super burn combustor exit and step 4) the turbine channel outlet, arrangement geometric area is adjustable
Common nozzle, and according to jet pipe different working condition design flow distribution plate.
The present invention uses (turbine/punching press/rocket) with by forming power, while Rocket ejector punching press and ultra-combustion ramjet are integrated
Runner form, can effectively across thrust wide gap and reduce by three dynamical system complexities.The combined engine collects propeller for turboprop
The advantages of machine high specific impulse, punching engine High Mach number and rocket engine All Speed Range, have technical difficulty it is moderate, can
The advantages that reuse.
The invention has the following advantages that
Wide fast domain flight and high-performance have been taken into account using the three power combination engines with double combustion chamber that the present invention generates
The characteristics of, not only solved Ma2-3 situation lower thrust divide problem, but also solve sub- combustion combustion chamber and super burn combustion chamber is difficult to coexist
The problem of.The configuration of the present invention is simple, work fast field width.Under High Mach number state, air flue is rotated into three-dimensional can guarantee that high flow capacity is caught
Incoming flow is obtained, reduces outflow resistance while increasing motor power；Under low mach state, air intake duct energy adjust automatically is overflow
Stream, widens power system operational range of Mach numbers.The double combustion chamber coexisted by the combustion of super burn Asia and three kinds of power engine groups
It closes, the flight requirement of wide speed domain Ma0~Ma8 can be met in the case where not reducing thrust performance.
Detailed description of the invention
Fig. 1 is super burn of the present invention and the sub- overall structure diagram for firing the three power combination engines that combustion chamber coexists.
Fig. 2 is that path partially is fired in super burn of the present invention and the sub- super burn for firing the three power combination engines that combustion chamber coexists-Asia
Enlarged drawing.
Specific embodiment
As depicted in figs. 1 and 2, the three power combination engines that the super burn and sub- combustion combustion chamber coexist include turning in three-dimensional
Air intake duct 1, turbine channel 2, ram rocket combination channel 3 and tail jet pipe 4.When flight Mach number 0~2, turbogenerator 8
Ignition operation, flow distribution plate 5 is in the top in three-dimensional contract air intake duct 1 at this time, i.e., state 1., in jet pipe 4 at flow distribution plate 6
In centre, i.e. 1. state, so that air-flow can both flow through turbine channel 2, can also flow through ram rocket channel 3.But punching press
Rocket channel 3 misfires and in bleed state；When flight Mach number 2~3, rocket engine 14 and sub- 9 points of combustion chamber of combustion
Firer makees, and the flow distribution plate 5 being now placed in air intake duct 1 is rotated down, and 2. in state, jet pipe 4 is punished flowing plate 6 and rotated upwards
2. to state, so that turbine channel 2 is closed.And aerial drainage is played in 11, punching press channel in ram rocket channel 3, Rocket ejector is logical
Road 10 works, and 14 exit flow of rocket flows into sub- combustion combustion chamber 9 and fuel oil is mixed and burned, and passes through 4 expansion work of jet pipe later
Generate thrust.When flight Mach number 3~5, rocket 14 stops working, Asia combustion 9 ignition of combustion chamber, nozzle throat area tune
It is inclined upwards to save plate 7,3. in state, aerial drainage is played the role of in punching press channel 11.When flight Mach number 5~8, ram rocket channel
Rocket ejector channel 10 stops working in 3, and it is mobile to direction of flow to be embodied in 10 inside center of Rocket ejector channel cone 13
To entrance, i.e. 5. state, causes air-flow that can not flow into 10 internal-combustion of Rocket ejector channel, rocket 14 and sub- combustion combustion chamber 9 are stopped
Only work.And super burn combustion chamber 12 starts ignition at this time, wherein air-flow is supersonic speed in 12 entrance of super burn combustion chamber, with
Fuel oil mixing is burnt in super burn combustion chamber 12.Later, air-flow generates thrust by 4 expansion work of jet pipe.In different incoming flow horses
Under conspicuous number state, jet pipe area is controlled by adjusting jet pipe throat area adjustable plate 7, and then guarantee thrust requirements.Wherein,
Under sub- combustion state, adjustable plate rotates upwards, i.e., state is 3.；Under super burn state, adjustable plate is rotated down, i.e., state is 4..Injection fire
Arrow channel 10 has solving that low mach punching engine is inoperative can not generate thrust, and it is continuous to play thrust
Effect.And punching press channel 11 is connected with super burn combustion chamber 12, ensure that engine (Ma5~Ma8) under High Mach number, that is, fires
It burns chamber inlet and generates thrust under the conditions of supersonic speed, to remain to work normally.
The three power combination engine options that super burn of the present invention and sub- combustion combustion chamber coexist are keeping wide fast domain flight and high
While thrust advantage, coexisting for both modalities which combustion chamber is realized, improves the overall performance of propulsion system, and structure letter
It is single, it is easy to accomplish.
Claims (1)
1. the three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist, it is characterised in that the super burn with
The three power combination engines that Asia combustion combustion chamber coexists, which are equipped in three-dimensional, rotates into air flue, turbine channel, ram rocket channel and tail
Jet pipe；The turbine channel and ram rocket channel, which share in a three-dimensional, rotates into air flue and jet pipe；The ram rocket is logical
Road is equipped with punching press channel and Rocket ejector channel, and the Rocket ejector channel is equipped with sub- combustion combustion chamber, the punching press channel and draws
It penetrates rocket channel outlet and is connected to a shared super burn combustion chamber；
The three power combination engine design methods that the super burn and sub- combustion combustion chamber coexist, comprising the following steps:
1) overall performance requirement is formulated according to aerial mission, design basic flow field is required based on overall performance, and then pass through streamline
Tracking obtains rotating into air flue in three-dimensional；
2) air passage outlet is rotated into the step 1) three-dimensional, super burn combustion chamber inlet and outlet ginseng is obtained according to engine overall performance
Number designs super burn combustion chamber；
3) before step 2) the super burn entry of combustion chamber, injection of corresponding size is arranged based on the engine thrust requirements of Ma2~5
Rocket channel, including center cone, rocket engine and sub- combustion combustion chamber；
4) according to the stage engine flow demand of Ma0~2, flow formula is utilizedTurbine channel inlet area is calculated,
InIndicate that flow, ρ indicate density, A indicates that area, v indicate speed, rotates into air flue upper wall surface in the step 1) three-dimensional and opens
Mouthful, arrange turbine channel；
5) in step 3) the super burn combustor exit and step 4) the turbine channel outlet, arrangement geometric area is adjustable total
Flow distribution plate is designed with jet pipe, and according to jet pipe different working condition.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711479801.0A CN108561244B (en) | 2017-12-29 | 2017-12-29 | The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist |
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| CN201711479801.0A CN108561244B (en) | 2017-12-29 | 2017-12-29 | The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist |
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| Publication Number | Publication Date |
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| CN108561244A CN108561244A (en) | 2018-09-21 |
| CN108561244B true CN108561244B (en) | 2019-10-18 |
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| CN109408993B (en) * | 2018-11-02 | 2020-07-31 | 厦门大学 | Design method of turbofan and ramjet combined engine with rocket inside |
| CN109236496B (en) * | 2018-11-15 | 2020-03-27 | 厦门大学 | Design method of three-power combined engine with switchable sub-combustion and super-combustion channels |
| CN109538377B (en) * | 2018-11-15 | 2020-03-27 | 厦门大学 | Design method of three-power combined engine sharing sub-combustion chamber |
| CN109670269B (en) * | 2019-01-07 | 2021-03-05 | 厦门大学 | Design method of multi-channel parallel three-power combined engine |
| CN110020500B (en) * | 2019-04-19 | 2021-01-01 | 厦门大学 | Design method of common tail nozzle of single-side expansion four-channel combined engine |
| CN112627983B (en) * | 2020-12-25 | 2022-02-22 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
| CN112948967B (en) * | 2021-02-08 | 2022-05-17 | 厦门大学 | Series-parallel three-power combined engine design method |
| CN113279880B (en) * | 2021-07-06 | 2022-11-11 | 中国航空发动机研究院 | Combined cycle aircraft engine |
| CN114753930A (en) * | 2022-04-19 | 2022-07-15 | 南京航空航天大学 | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics |
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