CN108561244A - A kind of three power combination engine design methods that super burn coexists with sub- combustion combustion chamber - Google Patents
A kind of three power combination engine design methods that super burn coexists with sub- combustion combustion chamber Download PDFInfo
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- CN108561244A CN108561244A CN201711479801.0A CN201711479801A CN108561244A CN 108561244 A CN108561244 A CN 108561244A CN 201711479801 A CN201711479801 A CN 201711479801A CN 108561244 A CN108561244 A CN 108561244A
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- combustion chamber
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- combustion
- engine
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Toys (AREA)
Abstract
A kind of three power combination engine design methods that super burn coexists with sub- combustion combustion chamber, 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 by streamlined impeller rotating into air flue in three-dimensional；Air passage outlet is rotated into three-dimensional, obtaining super burn combustion chamber according to engine overall performance imports and exports parameter, design 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 demands 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 with sub- combustion combustion chamber more particularly, to a kind of super burn are sent out
Motivation design method.
Background technology
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 Zhao thunder hypersonic flights of 21 century Aeronautics and Astronautics science and technology
The characteristics of device and its influence [J] cruising missiles 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 realize horizontal take-off, independently accelerate to high ultrasound
Speed combined dynamic system development (the big sound of [2] Liu, Chen Guang .21 centuries aero-engine (under) [J] aviation knowledges, 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 fast domain of width that integrated high-speed (Ma3~Ma8) punching engine is formed is high ultrasonic
Powertrain is united.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, high double woods hypersonic cruise missile ideal power systems --- TBCC
Engine and its key technology [J] cruising missiles, 2007 (11):49-53).
But in 2~3 range of Mach, there are turbogenerator work Mach number " not increasing ", punching presses for TBCC dynamical systems
The problem of engine work Mach number " being unable to come down "；And it is difficult to meet aircraft thrust in mode conversion process TBCC dynamical systems
Demand is absorbed in " 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 use Dual-mode Scramjet, in Ma3-5 states combustion chamber inflow Mach number be subsonic speed,
Ma5 or more is supersonic speed.However Dual-mode Scramjet technical maturity is relatively low at present, and farther out from engineering practice.
Invention content
It is an object of the invention to be directed to turbine-punching press, sub- combustion-super burn mode conversion process, provide
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 super burn and the three power combination engines that sub- combustion combustion chamber coexists 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 and burns
Room, the punching press channel and Rocket ejector channel outlet connect that there are one shared super burn combustion chambers.
The present invention includes 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
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, design 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 demands of Ma0~2, flow formula is utilizedCalculate turbine channel inlet face
Product, whereinIndicate that flow, ρ indicate that density, A indicate that area, v indicate speed, rotated on air flue in the step 1) three-dimensional
Wall surface is open, and 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 cross over 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 present invention has the following advantages：
The three power combination engines with double combustion chamber generated using the present invention have taken into account wide fast domain flight and high-performance
The characteristics of, not only solved Ma2-3 situation lower thrust divide problems, 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 and can guarantee that high flow capacity is caught
Incoming 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.
Description of the drawings
Fig. 1 is the overall structure diagram for the three power combination engines that super burn of the present invention coexists with sub- combustion combustion chamber.
Fig. 2 is that path partially is fired in the super burn-Asia for the three power combination engines that super burn of the present invention coexists with sub- combustion combustion chamber
Enlarged drawing.
Specific implementation mode
As depicted in figs. 1 and 2, the three power combination engines that the super burn coexists with sub- combustion combustion chamber 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
1. in centre, i.e. 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 is 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 up
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 is mixed and burned with fuel oil, passes through 4 expansion work of jet pipe later
Generate thrust.When flight Mach number 3~5, rocket 14 is stopped, 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 is stopped in 3, is embodied in Rocket ejector channel 10 inside center cone 13 and is moved to direction of flow
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 mixes, and burns in super burn combustion chamber 12.Later, air-flow generates thrust by 4 expansion work of jet pipe.In different incoming horses
Under conspicuous number state, jet pipe area is controlled by adjusting jet pipe throat area adjustable plate 7, and then ensure thrust requirements.Wherein,
Under sub- combustion state, adjustable plate rotates up, 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 normal work.
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 (2)
1. the three power combination engines that a kind of super burn coexists with sub- combustion combustion chamber, it is characterised in that equipped with rotating into gas in three-dimensional
Road, turbine channel, ram rocket channel and jet pipe；The turbine channel and ram rocket channel share to be rotated into a three-dimensional
Air flue and jet pipe；The ram rocket channel is equipped with punching press channel and Rocket ejector channel, and the Rocket ejector channel is equipped with
Asia combustion combustion chamber, the punching press channel and Rocket ejector channel outlet connect that there are one shared super burn combustion chambers.
2. the three power combination engine design methods that a kind of super burn coexists with sub- combustion combustion chamber, it is characterised in that including following step
Suddenly：
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, design 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 demands of Ma0~2, flow formula is utilizedTurbine channel inlet area is calculated,
InIndicate that flow, ρ indicate that density, A indicate that area, v indicate speed, rotating into air flue upper wall surface in the step 1) three-dimensional 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| 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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| Publication Number | Publication Date |
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| CN108561244A true CN108561244A (en) | 2018-09-21 |
| CN108561244B CN108561244B (en) | 2019-10-18 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109236496A (en) * | 2018-11-15 | 2019-01-18 | 厦门大学 | The three power combination engine design methods that Asia combustion can be switched with super burn channel |
| CN109408993A (en) * | 2018-11-02 | 2019-03-01 | 厦门大学 | The design method of the turbofan punching press combined engine of rocket built in a kind of outer culvert |
| CN109538377A (en) * | 2018-11-15 | 2019-03-29 | 厦门大学 | Share three power combination engine design methods of sub- combustion combustion chamber |
| CN109670269A (en) * | 2019-01-07 | 2019-04-23 | 厦门大学 | A kind of three power combination engine design methods of Multi-channel parallel connection |
| CN110020500A (en) * | 2019-04-19 | 2019-07-16 | 厦门大学 | A kind of design method of unilateral expansion four-way combined engine common nozzle |
| CN112627983A (en) * | 2020-12-25 | 2021-04-09 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
| CN112948967A (en) * | 2021-02-08 | 2021-06-11 | 厦门大学 | Series-parallel three-power combined engine design method |
| CN113279880A (en) * | 2021-07-06 | 2021-08-20 | 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109408993A (en) * | 2018-11-02 | 2019-03-01 | 厦门大学 | The design method of the turbofan punching press combined engine of rocket built in a kind of outer culvert |
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| CN109538377A (en) * | 2018-11-15 | 2019-03-29 | 厦门大学 | Share three power combination engine design methods of sub- combustion combustion chamber |
| CN109236496A (en) * | 2018-11-15 | 2019-01-18 | 厦门大学 | The three power combination engine design methods that Asia combustion can be switched with super burn channel |
| CN109670269A (en) * | 2019-01-07 | 2019-04-23 | 厦门大学 | A kind of three power combination engine design methods of Multi-channel parallel connection |
| 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 |
| CN110020500A (en) * | 2019-04-19 | 2019-07-16 | 厦门大学 | A kind of design method of unilateral expansion four-way combined engine common nozzle |
| CN112627983A (en) * | 2020-12-25 | 2021-04-09 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC 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 |
| CN112948967A (en) * | 2021-02-08 | 2021-06-11 | 厦门大学 | Series-parallel three-power combined engine design method |
| CN112948967B (en) * | 2021-02-08 | 2022-05-17 | 厦门大学 | Series-parallel three-power combined engine design method |
| CN113279880A (en) * | 2021-07-06 | 2021-08-20 | 中国航空发动机研究院 | Combined cycle aircraft engine |
| 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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