CN105351100B - A kind of rocket based combined cycle engine inlets distance piece structure design - Google Patents
A kind of rocket based combined cycle engine inlets distance piece structure design Download PDFInfo
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- CN105351100B CN105351100B CN201510716986.7A CN201510716986A CN105351100B CN 105351100 B CN105351100 B CN 105351100B CN 201510716986 A CN201510716986 A CN 201510716986A CN 105351100 B CN105351100 B CN 105351100B
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- air intake
- intake duct
- distance piece
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of rocket based combined cycle engine inlets distance piece structure design, it is located under the constraint in venturi section in air intake duct distance piece smallest cross-sectional, effectively circulated domain sectional area by improving distance piece, inlet throat section sectional area is increased to and is equal to entry of combustion chamber sectional area, effectively circulation domain uiform section product circulation is realized in air intake duct rocket support plate section, and by air intake duct rocket support plate section after etc. straight section be modified as contraction section, to match entry of combustion chamber section；Ensure that air intake duct distance piece minimum sectional area is located in venturi section；Air intake duct distance piece reduces the Start mach number of air intake duct, improves discharge coefficient and other performance parameter of the air intake duct under injection, sub- combustion mode.Rocket based combined cycle engine inlets isolator design expansion is strong, and air intake duct distance piece is designed according to different entry of combustion chamber sectional dimensions, can effectively widen the working range of air intake duct, is conducive to improving the overall performance of engine.
Description
Technical field
The present invention relates to rocket ramjet technical field, specifically, it is related to a kind of rocket based combined cycle to start
Machine air intake duct distance piece structure design.
Background technology
Rocket based combined cycle (Rocket-Based-Combined-Cycle, RBCC) engine have it is reusable,
The potential advantages such as inexpensive and higher reliability, are considered as most possibly being applied to pushing away for following earth to orbit and return transportation system
Enter one of system.Aircraft with rocket based combined cycle engine as propulsion system can be realized being taken off from ground zero-speed,
Constantly accelerate in flight course until reaching cruising condition, work Mach domain includes subsonic speed stage, transonic speed stage, supersonic speed
Stage, hypersonic speed stage；Spatially, rocket based combined cycle engine possesses from sea level up to exoatmosphere continues work
The ability of work.According to the working depth and Mach number of aircraft, rocket based combined cycle engine experiences following four mould successively
State, respectively Ejector Mode, Asia combustion punching press mode, ultra-combustion ramjet mode, pure rocket mode.But as the combination of this rocket base is followed
The research work of ring engine deepens continuously, and finds the quality of air intake duct service behaviour and has the overall performance of engine to pass
Important influence.Therefore, the corresponding air intake duct of rocket based combined cycle engine calls is in speed domain wide, in the working range in wide spatial domain
Stable, efficient can work, that is, require air intake duct starting capability under relatively low flight Mach number；It is required that air intake duct is in wide scope
It is interior with high flow coefficient；It is required that air intake duct has good total pressure recovery ability and anti-reflective pressure energy power in a wide range.
Additionally, rocket based combined cycle engine inlets should also have less resistance coefficient, and aircraft altitude can be met integrally
The design requirement of change.But, in existing rocket based combined cycle engine inlets method for designing, due to the built-in fire of distance piece
Arrow support plate, obstruction is jammed to flow by and be easily caused, and exacerbates contradiction of the air intake duct between Efficient Compression and low speed are started.
To realize the work that air intake duct can be normal, good in speed domain wide, wide spatial domain, it is several that domestic and foreign scholars propose different changes
Where case is improving service behaviour of the air intake duct under Ejector Mode, sub- combustion mode.The researcher in the U.S. is in document《Design
and Experimental Evaluation of a Mach 2-Mach 8 Inlet》In (AIAA 2001-1890,2001)
The X-43A aircraft of proposition employ rotation lip formula and become geometry air intake duct；And the scientific research personnel of France is in disclosed document
《Experimental Investigation of Starting Process for a variable Geometry Air
Inlet Operating from Mach 2 to Mach 8》Air intake duct lip is it is also proposed in (AIAA 2006-4513,2006)
Plate level moves the change geometrical solution with pivoting；The scientific research personnel of Japan is then in disclosed document《DESIGN STUDY ON
HYPERSONIC ENGINE COMPONENTS FOR TBCC SPACE PLANES》Carried in (AIAA 2003-7006,2003)
Go out by adjusting compressing surface angle to improve shrinkage ratio.
To adjust inlet lip or compressing surface, realize the structure changes air intake duct scheme that wide scope works, although can open up
Service behaviour of the working range, improvement air intake duct of air intake duct wide under Ejector Mode, sub- combustion mode, however it is necessary that with complexity
Mechanical structure is support, while sealing, easy implementation, a series of problems of additional structure quality can be brought, scheme can be real
Existing property is poor.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention propose a kind of rocket based combined cycle engine inlets every
From segment structure design；In the given entry of combustion chamber sectional dimension of engine total, on the premise of complicated structure changes device is not increased,
The Start mach number of air intake duct is reduced, discharge coefficient and other performance of the air intake duct under Ejector Mode, sub- combustion mode is improve
Parameter, while ensureing that air intake duct has good performance in super burn mode.
Thinking of the invention is:When the combustion chamber of identical entrance section product is matched, by size proposed by the present invention
Constraint, inlet throat section sectional area is increased to and is equal to entry of combustion chamber sectional area, is realized in air intake duct rocket support plate section
Effectively circulation domain uiform section product circulation, and by air intake duct rocket support plate section after etc. straight section be modified as contraction section, to match burning
Chamber inlet section；Can ensure that air intake duct distance piece minimum sectional area is located in venturi section.
The technical solution adopted for the present invention to solve the technical problems is:Including etc. straight venturi section, unilateral expansion rocket branch
The air intake duct distance piece of plate section, unilateral contraction section, wherein, air intake duct distance piece width is D, and entry of combustion chamber is highly H；Deng straight
Venturi section height H0=H, length L0=H；Rocket support plate height H1=H, width is D1；The angle of wedge of support plate half is θ, length L1=D1/
2tanθ；The unilateral angle of flare of rocket support plate section is:
δ=arctan { [H-H* (1-D1/D)]/L1}=arctan [2tan θ * (H/D)]
Support plate is connected with unilateral expansion segment, the rocket support plate that formation partly runs through；Contraction segment length is L2=H, angle of throat
It is β=arctan (D1/D)；The minimum circulation domain sectional area of inlet throat section is H*D, and rocket support plate section is subject to unilateral expansion-fire
Arrow support plate shrink double action, realize effectively circulation domain uiform section product, minimum circulation domain sectional area be H*D, contraction section then by
Rocket support plate outlet is contracted to entry of combustion chamber section, and minimum circulation domain sectional area is H*D.
By above structure design, can reach in matching identical configuration combustion chamber, ensure air intake duct distance piece smallest cross-sectional
On the premise of product is located at venturi section, the negotiability of air intake duct distance piece is improved.
Beneficial effect
Rocket based combined cycle engine inlets distance piece structure design proposed by the present invention, it is given in engine total
In the case of entry of combustion chamber sectional dimension, set according to the air intake duct distance piece structure that changes of section rule in domain proposes that effectively circulates
Meter, on the premise of complicated structure changes mechanical device is not increased, reduces the Start mach number of air intake duct, improves air intake duct and is drawing
The discharge coefficient and other performance parameter penetrated under mode, sub- combustion mode, and ensure that air intake duct is not damaged in super burn Modal Performances
Lose.
Rocket based combined cycle engine inlets distance piece structure design expansion of the present invention is strong, can be according to different burnings
Chamber inlet sectional dimension is designed to air intake duct isolation segment structure, is located in venturi section in air intake duct distance piece smallest cross-sectional
Under the premise of, increase distance piece and effectively circulate domain sectional area, effectively widen the working range of air intake duct.Enter in given combustion chamber
Open height H and rocket support plate height H1=H0, width is D1On the premise of, as long as meeting geometrical relationship formula proposed by the present invention, i.e.,
Can obtain has more preferable starting performance and the air intake duct distance piece structure design of other service behaviours in Ejector Mode, sub- combustion mode
Scheme, is conducive to improving the overall performance of engine.
Brief description of the drawings
Below in conjunction with the accompanying drawings with implementation method to a kind of rocket based combined cycle engine inlets distance piece knot of the invention
Structure design is described in further detail.
Fig. 1 is rocket based combined cycle engine inlets structural representation；
Fig. 2 is rocket based combined cycle engine inlets distance piece top view；
Fig. 3 is rocket based combined cycle engine inlets distance piece Central Symmetry face sectional view.
Specific embodiment
The present embodiment is a kind of rocket based combined cycle engine inlets distance piece structure design.
Refering to Fig. 1~Fig. 3, the present embodiment rocket based combined cycle engine inlets distance piece structure design, in air inlet
Distance piece smallest cross-sectional in road is located under the constraint in venturi section, is effectively circulated domain sectional area Changing Pattern by improving distance piece,
Obtain the isolator design scheme for effectively widening air intake duct working range.Direction of flow as being direction shown in U in figure, flow by a distant place
Flowed into distance piece by after precursor precommpression section, the compression of interior compression section, and flow through venturi section, rocket successively in distance piece
Support plate section and contraction section.Wherein, venturi section is to wait straight section, by interior compression section outlet transition to rocket support plate section entrance；Rocket branch
Plate section is subject to the double action that unilateral expansion-rocket support plate shrinks, and realizes effectively circulation domain uiform section product；Contraction section has β degree
Angle of throat, entry of combustion chamber section is transitted to by rocket support plate outlet.
In the present embodiment, to ensure that air intake duct distance piece smallest cross-sectional is located in venturi section, certain physical dimension need to be met
Constraint；Wherein, air intake duct distance piece width is determined for D according to totality and Combustion chamber design scheme, entry of combustion chamber is highly
H；
Etc. straight venturi section height H0=H, length L0=H；
Rocket support plate height H1=H, width is D1；
The angle of wedge of support plate half is θ, length L1=D1/2tanθ；
The unilateral angle of flare of rocket support plate section is:
δ=arctan { [H-H* (1-D1/D)]/L1}=arctan [2tan θ * (H/D)]
Support plate is connected with unilateral expansion segment, the rocket support plate that formation partly runs through；Contraction segment length is L2=H, angle of throat
It is β=arc tan (D1/D)。
Design shows more than, and the minimum circulation domain sectional area of inlet throat section is H*D, and rocket support plate section is subject to one side
The double action that expansion-rocket support plate shrinks, realizes effectively circulation domain uiform section product, and its minimum circulation domain sectional area is H*D, and
Contraction section is then contracted to entry of combustion chamber section by rocket support plate outlet, and its minimum circulation domain sectional area is still H*D.Cause
This, the present embodiment rocket based combined cycle engine inlets distance piece structure design, can in matching identical configuration combustion chamber, really
On the premise of guarantor's air intake duct distance piece minimum sectional area is located at venturi section, the effective circulation domain section in increase and decrease air intake duct distance piece
Product.
For further checking the present embodiment, to the improvement result of air intake duct service behaviour under Ejector Mode, sub- combustion mode, leads to
The method for crossing numerical simulation is verified.
Influence of the different distance piece configurations to inlet characteristic under the Ma3 operating modes of table 1
| Air intake duct configuration | Exit Mach number | Pressure rises ratio | Temperature rise ratio | Discharge coefficient | Total pressure recovery coefficient | Resistance coefficient |
| Traditional distance piece | 1.739 | 4.556 | 1.745 | 0.310 | 0.675 | 0.408 |
| Optimization distance piece | 1.054 | 11.951 | 2.278 | 0.552 | 0.662 | 0.438 |
As can be seen from Table 1, risen in exit Mach number and pressure in compressibility using the air intake duct configuration of optimization distance piece
Than, temperature rise ratio aspect, discharge coefficient aspect has greater advantage, wherein, pressure is risen than improving 162.3%, and discharge coefficient is improved
78.1%；And total pressure recovery coefficient is only slightly reduced, resistance coefficient slightly has rising.Meanwhile, the self-starting Mach number of air intake duct by
Mach 2.4 is reduced to Mach 2.1, has effectively widened the working range of rocket based combined cycle engine inlets.Illustrate excellent
Change distance piece structural design scheme, Ejector Mode, sub- combustion mould can be effectively improved under the precursor for improving intake duct starting performance
Service behaviour under state, while air intake duct performance loss under super burn mode will not be caused.
Claims (1)
1. a kind of rocket based combined cycle engine inlets distance piece structure design, it is characterised in that:Including etc. straight venturi section,
Rocket support plate section, the air intake duct distance piece of unilateral contraction section are expanded in one side, wherein, air intake duct distance piece width is D, and combustion chamber enters
Open height is H；Etc. straight venturi section height H0=H, length L0=H；Rocket support plate height H1=H, width is D1；Rocket support plate half
The angle of wedge is θ, length L1=D1/2tanθ；The unilateral angle of flare of rocket support plate section is:
δ=arctan { [H-H* (1-D1/D)]/L1}=arctan [2tan θ * (H/D)]
Rocket support plate is connected with unilateral expansion segment, the rocket support plate that formation partly runs through；Contraction segment length is L2=H, angle of throat is
β=arctan (D1/D)；The minimum circulation domain sectional area of inlet throat section is H*D, and rocket support plate section is subject to unilateral expansion and fire
Arrow support plate shrink double action, realize effectively circulation domain uiform section product, minimum circulation domain sectional area be H*D, contraction section then by
Rocket support plate outlet is contracted to entry of combustion chamber section, and minimum circulation domain sectional area is H*D.
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106150757A (en) * | 2016-08-10 | 2016-11-23 | 西北工业大学 | A kind of dual pathways becomes geometry rocket based combined cycle electromotor |
| CN107120210B (en) * | 2017-06-25 | 2023-05-23 | 北京航天三发高科技有限公司 | Supersonic jet pipe |
| CN109184951B (en) * | 2018-08-10 | 2019-06-18 | 西安理工大学 | Distance piece transverse direction supporting plate magnetic charging device and its to distance piece flow control method |
| CN112555052B (en) * | 2020-12-04 | 2021-10-01 | 中国人民解放军国防科技大学 | Contraction type isolation section and scramjet engine |
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| US5419117A (en) * | 1993-07-30 | 1995-05-30 | The Boeing Company | Turbo jet/RAM jet propulsion system |
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