CN109779784A - A kind of RBCC engine inner flow passage of the preposition center layout of rocket - Google Patents
A kind of RBCC engine inner flow passage of the preposition center layout of rocket Download PDFInfo
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- CN109779784A CN109779784A CN201811535859.7A CN201811535859A CN109779784A CN 109779784 A CN109779784 A CN 109779784A CN 201811535859 A CN201811535859 A CN 201811535859A CN 109779784 A CN109779784 A CN 109779784A
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Abstract
A kind of RBCC engine inner flow passage of the preposition center layout of rocket, comprising: air inlet runner, combustion chamber runner and rocket engine runner；Rocket engine runner is located at combustion chamber flow channel entry point center；Air inlet runner is located at rocket engine runner surrounding and imports combustion chamber runner together with rocket engine runner；Air inlet runner and combustion chamber runner constitute punching press runner, and punching press runner and rocket engine runner collectively form RBCC engine inner flow passage.The present invention can play the advantages such as combustion-supporting, the injection pushing of rocket motor ignition under the premise of as small as possible to the interference of punching press runner type face.
Description
Technical field
The invention belongs to rocket based combined cycle engine (RBCC engine) technical fields, relate generally to a kind of engine
Runner scheme, especially a kind of highly integrated wide area RBCC engine inner flow passage scheme, specifically a kind of preposition center layout of rocket
RBCC engine inner flow passage scheme, can be used as the runner design scheme of the similar engine such as RBCC engine, combined engine.
Background technique
RBCC engine is one of the main candidate power of the following near space vehicle and re-entry space vehicle, in last century
Since leaf, it is directed to different aerial missions both at home and abroad, has constructed a variety of RBCC engine inner flow passage schemes: Strutjet engine
With ISTAR engine using runner in rectangular section, rocket engine is arranged in runner center in the middle part of combustion chamber；A5 engine
Using rectangular section inner flow passage, rocket engine is arranged in entry of combustion chamber side wall；Japanese JAXA-RBCC engine uses rectangle
Section inner flow passage, rocket engine are arranged in entry of combustion chamber roof side；GTX aircraft is circumferentially equal by three RBCC engines
It is distributed in aircraft, every engine cross section of fluid channel is incomplete axially symmetric structure, and rocket engine is arranged in RBCC engine
Entry of combustion chamber is biased to axis side.
Above-mentioned RBCC engine inner flow passage scheme is not suitable for small scale axial symmetry aircraft or uses engine two sides
The aircraft of layout type is hung, and geometrical constraint suffered by rocket engine is strong, power thermal environment is severe, causes research of technique difficult
Degree is big.
The tackling key problem of RBCC power technology is being carried out in assembly power field at present, and urgent need, which designs one kind, can meet recent engine
Key technology integrates the RBCC engine inner flow passage scheme of flight test and small scale engineer application.
Summary of the invention
Technology of the invention solves the problems, such as: overcome the deficiencies in the prior art, propose a kind of rocket engine it is preposition in
The RBCC engine inner flow passage scheme of heart layout can play fire under the premise of as small as possible to the interference of punching press runner type face
The advantages such as combustion-supporting, the injection pushing of arrow engine ignition.
The technical solution of the invention is as follows: a kind of RBCC engine inner flow passage of the preposition center layout of rocket, including into
Flow channel, combustion chamber runner and rocket engine runner；
Rocket engine runner is located at combustion chamber flow channel entry point center；Air inlet runner is located at rocket engine runner four
Week and combustion chamber runner is imported together with rocket engine runner；Air inlet runner and combustion chamber runner constitute punching press runner, punching press
Runner and rocket engine runner collectively form RBCC engine inner flow passage.
Preferably, the combustion chamber runner be axial symmetry configuration, cross section be circle, area of section from entrance section to
Outlet gradually increases.
Preferably, combustion chamber cross section of fluid channel variable area given rule: combustion chamber cross section of fluid channel diameter increases along piecewise linearity is flowed to
Add, and the increased slope of each section of diameter of section is continuously increased along flow direction.
Preferably, combustion chamber cross section of fluid channel variable area given rule: combustion chamber cross section of fluid channel diameter increases along piecewise linearity is flowed to
Add, final stage is cross-section area section, and the linearly increasing increased slope of each section of diameter of section is continuously increased along flow direction.
Preferably, the rocket engine runner is axial symmetry configuration, and outlet and combustion chamber flow channel entry point are cut
Face is concordant, and rocket engine runner and combustion chamber runner are coaxial, this axis is also the central axis of RBCC engine inner flow passage.
Preferably, the air inlet runner is looped around around rocket engine runner, and the entrance section of air inlet runner is separate
RBCC engine inner flow passage axis, air inlet runner section move closer to RBCC engine inner flow passage axis along air current flow direction,
Air inlet runner outlet is concordant with rocket engine runner exit section.
Preferably, the air inlet runner center line uses spline curve.
Preferably, the air inlet runner center line uses the smooth splicing of multi-section circular arc, and the smooth splicing refers to two sections
Circular arc is tangent in junction.
Preferably, increase supporting plate and Cavity Flame Holder in the middle and lower reaches of combustion chamber runner.
The present invention has the beneficial effect that compared with prior art
1 present invention is mentioned for small scale axial symmetry aircraft or using the aircraft of engine two sides hanging layout type
The RBCC engine inner flow passage scheme for having gone out a kind of preposition center layout of rocket engine, can give full play of rocket engine and
The integrated advantage of punching engine.
It is a variety of that the preposition rocket engine layout of 2 present invention can play combustion-supporting, injection pushing of rocket motor ignition etc.
Advantage.
The 3 preposition center layout modes of rocket engine of the present invention, so that round rocket engine runner exit section and ring
Shape air inlet runner outlet can well dock, and invalid geometric space significantly reduces, and reduce rocket engine outlet and firing
The area accounting for burning chamber inlet, is conducive to engine models face matched design.
4 present invention are in chamber front end center arrangement rocket engine and the air inlet on the outside of rocket engine, air inlet runner
The layout type gradually tightened to rocket engine runner exit using streamwise, may make rocket engine runner and punching
Press flow passage structure interference small, the space constraint of rocket engine design is looser, and design difficulty significantly reduces.
5 present invention are in chamber front end center arrangement rocket engine, with the rocket engine layout type for leaning near wall
It compares, for rocket engine high temp jet far from combustion chamber runner wall surface, the thermal protection that not will increase combustion chamber runner wall surface is difficult
Degree, the flameholder that will not be arranged to rocket downstream combustion chamber near wall have an adverse effect.
6 combustion chamber runners of the present invention use axial symmetry configuration, and chamber structure intensity is good, wetted area is small, combustion chamber heat
Difficulty is protected to reduce.
Detailed description of the invention
Fig. 1 is that basic system of the invention constitutes schematic diagram and working principle diagram；
Fig. 2 a, 2b are using inner flow passage plane of symmetry temperature profile when engine operation of the invention, and wherein Fig. 2 a is Ma
Temperature profile when=3.0, temperature profile when Fig. 2 b is Ma=6.0.
Specific embodiment
With reference to the accompanying drawing and example elaborates to the present invention.
RBCC engine is one of the main candidate power of the following near space vehicle and re-entry space vehicle, belongs to current state
Border study frontier and hot spot region.Nearly ten years, domestic to have carried out numerous studies for RBCC engine, there is certain technology
Basis.Be currently under key technology integrated verification and small scale engineer application demonstration stage, urgent need design a kind of integrated level it is high,
The RBCC engine runner scheme that structure is reliable, engineering is easy to accomplish.The novelty that the present invention exactly carries out regarding to the issue above
Research.
As shown in Figure 1, the present invention is a kind of RBCC engine inner flow passage of preposition center layout of rocket, it include inlet air flow
Road inner wall 1, air inlet runner outside wall surface 2, combustion chamber runner wall surface 3 and rocket engine runner wall surface 4, air inlet runner inner wall
1 and air inlet runner outside wall surface 2 constitute air inlet runner 5, combustion chamber runner wall surface 3 constitute combustion chamber runner 6, rocket engine runner
Wall surface 4 constitutes rocket engine runner 7, and air inlet runner, combustion chamber runner constitute punching press runner, and with rocket engine runner
Together constitute RBCC engine inner flow passage.RBCC engine inner flow passage integrated level of the present invention is high, space layout is reasonable, can be more preferable
Performance rocket engine effect, engine thermal protect difficulty it is low, structural strength is good, can be used as recent engine key technology collection
At the RBCC engine runner scheme of flight test and small scale engineer application (such as short-range missile).
Combustion chamber runner be axial symmetry configuration, i.e., cross section be circle, area of section from entrance section to outlet with
Certain changing rule gradually increases.Such as combustion chamber cross section of fluid channel diameter increases along piecewise linearity is flowed to, and each section of section is straight
The increased slope of diameter is continuously increased along flow direction；It can also increase for combustion chamber cross section of fluid channel diameter along piecewise linearity is flowed to, last
Section (i.e. combustor exit section) is cross-section area section, and the linearly increasing increased slope of each section of diameter of section constantly increases along flow direction
Add.Above-mentioned second of changing rule is used when embodiment numerical simulation model.It can be adjusted as the case may be when actual design
Whole combustion chamber and each section of length and slope.
Rocket engine runner is axial symmetry configuration, and outlet is concordant with combustion chamber flow channel entry point section, rocket hair
Motivation runner and combustion chamber runner are coaxial, this axis is also the central axis of RBCC engine inner flow passage.
Air inlet runner is looped around around rocket engine runner, and air inlet runner entrance section is far from RBCC engine inner flow passage
Axis, air inlet runner section move closer to RBCC engine inner flow passage axis, i.e. streamwise gradually along air current flow direction
It is tightened to rocket engine runner exit section, air inlet runner outlet closely rocket engine runner exit section, air inlet
Runner exit section is concordant with rocket engine runner exit section.
In order to realize burning tissues, on the basis of engine inner flow passage scheme, in combustion chamber, runner middle and lower reaches are increased
Supporting plate and Cavity Flame Holder.Embodiment numerical simulation model is divided in combustion chamber runner along 1/2 position and 3/4 position is flowed to
Supporting plate and Cavity Flame Holder are not arranged.
Through numerical simulation, obtains engine inner flow passage flow field parameter and be distributed, inner flow passage plane of symmetry Temperature Distribution reference Fig. 2 a,
2b.It can be seen from the figure that rocket engine outlet jet initial segment is located at inner flow passage axis, the cross section of fluid channel product of occupancy
It is small, air inlet runner punching press incoming flow is influenced small；After a distance, rocket engine outlet jet and air inlet runner incoming flow are empty
Gas blends rapidly, and incoming air takes part in the burning of rocket engine Jet Flow Field in blending procedure, the blending burning of upstream for
The burning tissues of combustion chamber flow paths downstream flameholder layout area, have played preferable igniting, steady flame and combustion-supporting effect, into
And improve motor power；Before rocket jet stream is fully immersed into fired downstream flow field, rocket jet stream is flowed far from combustion chamber
Road wall surface, combustion chamber heat protection design difficulty significantly reduce.
In brief, the RBCC engine inner flow passage scheme of the preposition center layout of rocket provided by the invention.Before center
Set rocket engine runner, the combustion chamber runner that circumferential direction gradually converges on the air inlet runner of axis attachment and sectional area gradually expands
Together constitute RBCC engine inner flow passage scheme.Studies have shown that the present invention can preferably play rocket motor ignition
The advantages of combustion-supporting, injection pushing；Rocket engine space constraint is more loose, and design difficulty reduces, and it is dry to punching press runner
Relate to it is small, be conducive to improve punching press runner wide area working performance；Rocket engine high temp jet adds far from combustion chamber runner wall surface
Combustion chamber sheet as axially symmetric structure, chamber structure intensity is good, light weight.Very good solution of the present invention long-standing problem
The big problem of the rocket engine and punching press runner difficulty of matching of RBCC engine gives full play of rocket engine and punching press hair
The integrated advantage of motivation.The present invention can be used as recent engine key technology and integrate flight test and small scale engineer application
RBCC engine inner flow passage scheme is used for reference when also studying for other air suction type assembly powers.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (9)
1. a kind of RBCC engine inner flow passage of the preposition center layout of rocket, characterized by comprising: air inlet runner, combustion chamber stream
Road and rocket engine runner；
Rocket engine runner is located at combustion chamber flow channel entry point center；Air inlet runner be located at rocket engine runner surrounding and
Combustion chamber runner is imported together with rocket engine runner；Air inlet runner and combustion chamber runner constitute punching press runner, punching press runner
RBCC engine inner flow passage is collectively formed with rocket engine runner.
2. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 1, it is characterised in that: institute
The combustion chamber runner stated is axial symmetry configuration, and cross section is circle, and area of section is gradually increased from entrance section to outlet.
3. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 2, it is characterised in that: combustion
Burn room cross section of fluid channel variable area given rule: combustion chamber cross section of fluid channel diameter increases along piecewise linearity is flowed to, and each section of diameter of section
Increased slope is continuously increased along flow direction.
4. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 2, it is characterised in that: combustion
Burn room cross section of fluid channel variable area given rule: combustion chamber cross section of fluid channel diameter is to wait to cut along piecewise linearity increase, final stage is flowed to
Face area section, the linearly increasing increased slope of each section of diameter of section are continuously increased along flow direction.
5. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 1, it is characterised in that: institute
The rocket engine runner stated is axial symmetry configuration, and outlet is concordant with combustion chamber flow channel entry point section, rocket engine
Runner and combustion chamber runner are coaxial, this axis is also the central axis of RBCC engine inner flow passage.
6. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 1, it is characterised in that: institute
The air inlet runner stated is looped around around rocket engine runner, and the entrance section of air inlet runner is far from RBCC engine inner flow passage axis
Line, air inlet runner section move closer to RBCC engine inner flow passage axis along air current flow direction, air inlet runner outlet and
Rocket engine runner exit section is concordant.
7. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 6, it is characterised in that: institute
The air inlet runner center line stated uses spline curve.
8. a kind of RBCC engine inner flow passage of the preposition center layout of rocket according to claim 6, it is characterised in that: institute
The air inlet runner center line stated uses the smooth splicing of multi-section circular arc, and the smooth splicing refers to that two sections of circular arcs are tangent in junction.
9. a kind of RBCC engine inner flow passage of the preposition center layout of rocket, feature described in one of -8 according to claim 1
Be: in combustion chamber, the middle and lower reaches of runner increase supporting plate and Cavity Flame Holder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811535859.7A CN109779784A (en) | 2018-12-14 | 2018-12-14 | A kind of RBCC engine inner flow passage of the preposition center layout of rocket |
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| CN201811535859.7A CN109779784A (en) | 2018-12-14 | 2018-12-14 | A kind of RBCC engine inner flow passage of the preposition center layout of rocket |
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Cited By (3)
| 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 |
| CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
| CN116447042A (en) * | 2023-06-09 | 2023-07-18 | 西安航天动力研究所 | Rocket-based combined engine |
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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 |
| CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
| CN112627982B (en) * | 2020-12-15 | 2021-12-07 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
| CN116447042A (en) * | 2023-06-09 | 2023-07-18 | 西安航天动力研究所 | Rocket-based combined engine |
| CN116447042B (en) * | 2023-06-09 | 2023-10-20 | 西安航天动力研究所 | Rocket-based combined engine |
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Application publication date: 20190521 |