CN105156212B - A kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet - Google Patents
A kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet Download PDFInfo
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- CN105156212B CN105156212B CN201510648492.XA CN201510648492A CN105156212B CN 105156212 B CN105156212 B CN 105156212B CN 201510648492 A CN201510648492 A CN 201510648492A CN 105156212 B CN105156212 B CN 105156212B
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- pressing board
- intake duct
- air intake
- top pressing
- inlet
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Abstract
Become geometry Sidewall-compression inlet the invention discloses a kind of rocket based combined cycle engine, adjusted using geometric ways classification is become, it is ensured that air intake duct has preferably performance in 1.5~7Ma working ranges.Become geometry Sidewall-compression inlet and capture air capacity by reducing low mach, to realize that air intake duct low mach is started, by rotating the second top pressing board, secondary channels are opened, fraction introduces burner ends, while reduction Ejector Mode Inlet drag, and the air-flow suppression jet pipe for introducing burner ends crosses expansion to increase thrust, so as to which whole engine performance is substantially improved, Ejector Mode specific fuel consumption is reduced.During sub- super burn Modality work, secondary channels are closed, and certain pressure difference overflow window is blocked in movable lip plate covering, effectively improves Flow coefficient of inlet and total pressure recovery coefficient.Sidewall-compression inlet has advantage that is simple, easily realizing, and can guarantee that air intake duct has preferably performance in whole engine operation interval.
Description
Technical field
The present invention relates to rocket ramjet technical field, specifically, it is related to a kind of rocket based combined cycle and starts
Machine becomes geometry Sidewall-compression inlet.
Background technology
Rocket based combined cycle (Rocket-Based-Combined-Cycle, RBCC) engine by rocket engine and
Airbreathing motor is organically combined in a runner, by Mode-switch, the equal energy in different flight Mach numbers and height
It is operated in an optimal manner.With the difference of flight Mach number, rocket based combined cycle engine mainly undergoes four substantially
Operation mode:Rocket ejector mode, sub- combustion punching press mode, ultra-combustion ramjet mode and pure rocket mode.Rocket based combined cycle is sent out
Motivation is made up of four parts substantially:Air intake duct, main rocket, combustion chamber and the jet pipe being embedded in runner.By rocket base group
The influence of the wide envelope curve work of cycle engine is closed, rocket based combined cycle air intake duct should ensure to improve compared with low mach starting
The acceleration capacity in Ejector Mode later stage, ensures that sub- super burn mode has preferably performance again.By become geometry can widen into
Work range of Mach numbers under air flue starting state, and improve the combination property of air intake duct.
At present, the external technical literature being disclosed, the U.S.《Hyper-X Flight Engine Ground
Testing for X-43Flight Risk Reduction[R]》(Huebner l D,Rock K E,Ruf E G,
Etc.AIAA 2001-1809) text in, X-43A using rotate lip regulative mode；X-43A by B-52 carries, and by " fly
Horse " booster rocket boosting, but the self-starting performance of air intake duct is not verified.What France and Russia cooperated《French-
Russian Cooperation on High-Speed Airbreathing Propulsion[R]》(Marc BOUCHEZ,
Vadim LEVINE.2003-2907) the movable PIFA concept engines of the outer cover that proposes in text；PIFA passes through to fixation
The outer cover part in type face is moved horizontally to change the geometric configuration of whole engine, and difficulty is added to engine runner design
Degree.
In domestic disclosed technical literature,《Hypersonic side-wall inlet becomes geometrical solution research》(Nanjing aviation is navigated
Its university, master thesis in 2012), mobile lip, the venturi top plate proposed for side pressure air intake duct is deflated and lip revolves
Turn three kinds of change geometrical solutions, study air intake duct working range for 4~7Ma, power traction is started without reference to rocket based combined cycle
Penetrate inlet characteristic under Modality work Mach number.Therefore, in order that obtaining rocket based combined cycle engine in whole operation interval
With compared with dominance energy, the change geometrical solutions required under different operating mode the difference of air intake duct are met most important.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes that a kind of rocket based combined cycle engine becomes geometry side
Pressure type air intake duct, by mobile lip and rotation second level top pressing board, improves intake duct starting performance, solves to enter under low mach
Air flue, which captures air mass flow and throat, to be allowed, by the matching problem between air mass flow, to reduce Ejector Mode Inlet drag
While, increase thrust by the way that a part of fluid introducing combustion chamber latter end suppression jet pipe is crossed into expansion, so as to reduce injection
Mode specific fuel consumption.
The technical solution adopted for the present invention to solve the technical problems is:Including air intake duct, combustion chamber, jet pipe, drainage
Pipe, it is characterised in that also including the first top pressing board, the second top pressing board, side plate, distance piece top plate, lip plate, center support plate, first
Top pressing board and the second top pressing board, distance piece top plate are located at air intake duct bottom respectively, and distance piece top plate is connected to after the second top pressing board
End, drainage tube is connected with air intake duct is transitioned into combustion chamber latter end；Lip plate moves forward and backward to change by Driven by Hydraulic Cylinder along side plate
Become air intake duct contract ratio, adjust spillway discharge, center support plate is located at the rear portion of lip plate；Side plate bottom is arc line shaped, with second
Top pressing board faying face position will not interfere in movement or gap occurs；First top pressing board and the second top pressing board pass through rotating shaft
It is hinged, is rotated around the axis by the top pressing board of Driven by Hydraulic Cylinder second, secondary channels is in the state being turned on and off；Work as air intake duct
When low mach works, the second top pressing board is rotated down, and secondary channels are opened, and fraction introduces combustion chamber latter end, reduces injection
Mode Inlet drag, suppresses jet pipe and crosses expansion increase thrust to lift engine performance；When the sub- super burn mode work of air intake duct
When making, secondary channels are closed, and movable lip plate blocks pressure difference overflow window segment to improve Flow coefficient of inlet.
The center support plate semiapex angle θ is 5.7 °, the first top pressing board wedge surface angle, θ1For 6 °, the second top pressing board wedge surface angle
θ2For 6.5 °.
The center support plate is received to distance piece, reduces air intake duct low mach resistance, while weakening shoulder separation, increase
Air intake duct contract section entrance the ratio of width to height.
Beneficial effect
Rocket based combined cycle engine proposed by the present invention becomes geometry Sidewall-compression inlet, in 1.5~7Ma working ranges
It is interior that by being classified in regulating guarantee flight range under different Mach number, air intake duct has preferably performance.Compared with prior art,
Become geometry Sidewall-compression inlet by reducing low mach capture air capacity to realize that air intake duct low mach is started, pass through and rotate
Second level top pressing board, while reduction Ejector Mode Inlet drag, introduces combustion chamber latter end by a part of air-flow and suppresses tail spray
Pipe crosses expansion to increase thrust, so that whole rocket based combined cycle engine performance is substantially improved.Lip shape is covered in " V " type
The certain pressure difference overflow window of lid, effectively improves Flow coefficient of inlet and total pressure recovery coefficient.
Rocket based combined cycle engine of the present invention becomes geometry Sidewall-compression inlet, using become geometric ways have it is simple,
The advantage easily realized, and can guarantee that air intake duct has preferably performance in whole rocket based combined cycle engine operation interval.
Brief description of the drawings
Become geometry side compression type to a kind of rocket based combined cycle engine of the invention with embodiment below in conjunction with the accompanying drawings to enter
Air flue is described in further detail.
Fig. 1 is rocket based combined cycle engine structure schematic diagram.
Fig. 2 is that RBCC engines become geometry Sidewall-compression inlet schematic diagram.
Fig. 3 is that RBCC engines become geometry Sidewall-compression inlet top view.
Fig. 4 is that RBCC engines become Mach number cloud atlas under geometry Sidewall-compression inlet design point.
Fig. 5 is that RBCC engines become Mach number cloud atlas top view under geometry Sidewall-compression inlet design point.
In figure:
1. the side plate of 2. combustion chamber of air intake duct, 3. jet pipe, 4. drainage tube, 5. first 6. second top pressing board of top pressing board 7.
8. the center support plate of 9. lip plate of distance piece top plate 10.
Embodiment
The present embodiment is that a kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet.
Refering to Fig. 1~Fig. 5, rocket based combined cycle engine become geometry Sidewall-compression inlet by air intake duct 1, combustion chamber 2,
Jet pipe 3, the top pressing board 5 of drainage tube 4 and first, the second top pressing board 6, side plate 7, distance piece top plate 8, lip plate 9, center support plate 10
Composition；First top pressing board 5 and the second top pressing board 6, distance piece top plate 8 are separately mounted to the bottom of air intake duct 1, and distance piece top plate 8 connects
The rear end of the second top pressing board 6 is connected on, drainage tube 4 is connected with air intake duct 1 is transitioned into the latter end of combustion chamber 2, jet pipe 3 is arranged on burning
The rear end of room 2.Lip plate 9 moves forward and backward to change the contract ratio of air intake duct 1 by Driven by Hydraulic Cylinder along side plate 7, adjusts spillway discharge,
Ensure air intake duct normal work and meet the requirement of entry of combustion chamber condition.The bottom of side plate 7 is processed as arc line shaped, side plate 7 and second
The hardened face position of closing of top pressure 6 will not interfere in movement or gap occurs.First top pressing board 5 passes through with the second top pressing board 6
Rotating shaft is hinged, and is rotated around the axis by the second top pressing board of Driven by Hydraulic Cylinder 6, secondary channels is in the state being turned on and off；When
When the low mach of air intake duct 1 works, the second top pressing board 6 is rotated down, and secondary channels are opened, and fraction introduces the latter end of combustion chamber 2,
Inlet drag when reducing Ejector Mode work, suppresses jet pipe 3 and crosses expansion increase thrust to lift engine performance；Work as air inlet
During the super burn Modality work of road Asia, secondary channels are closed, and movable lip plate 9 blocks pressure difference overflow window segment to improve inlet duct flow
Coefficient of discharge.
Center support plate 10 is received to distance piece, reduce air intake duct low mach resistance, while weaken shoulder separation, increase into
Air flue contract section entrance the ratio of width to height.
In the present embodiment, rocket based combined cycle engine becomes geometry Sidewall-compression inlet and chooses Design of Inlet parameter
For:Capture flow is 3.2kg/s；Design Mach 2 ship 6.0；Start mach number is less than 2.0.Inlet mouth the ratio of width to height W1/H1
For 1.23, main support plate dutycycle D/W2 is 0.3, and total shrinkage ratio W1 × H1/W2 × H2 is 6.35, top pressure direction shrinkage ratio H1/H2
For 4.28, lateral shrinkage ratio W1/W2 is 1.48, self-starting Mach 2 ship 1.8.In order to reduce air intake duct length, center support plate half
Vertex angle theta is larger, is taken as 5.7 °.Two-stage top pressure wedge surface angle, θ1And θ2Respectively 6 ° and 6.5 °, shoulder arc transition, knuckle radius
For 500mm.Small big under the angle of side plate 7, gradually transition weakens side pressure shock wave and interfered with top plate boundary-layer, keeps top plate
Pressure difference overflow, increase air intake duct capture flow are reduced while boundary-layer stability.
In the present embodiment, rocket based combined cycle engine become geometry Sidewall-compression inlet level Four regulative mode into:
Ma working ranges are 1.5~2.0 in configuration I, and lip plate 9 is at position 1, and second level top pressing board 6 is rotated down, main
Passage and secondary channels are opened simultaneously, and while increase low mach capture air capacity, air intake port and burning are not resulted in again
The mismatch of chamber inlet configuration；
Ma working ranges are 2.0~2.8 in configuration II, and second level top pressing board 6 is rotated up, and secondary channels are closed, lip plate 9
Still at position 1；
Ma working ranges are 2.8~3.5 in configuration III, and lip plate 9 is moved forward at position 2；
Ma working ranges are 3.5~7 in configuration IV, and lip plate 9 is moved forward at position 3.
Become from rocket based combined cycle engine under geometry Sidewall-compression inlet design point and can be seen that in Mach number cloud atlas, lead to
Pressure difference overflow window segment is blocked in the change for crossing lip shape, it is ensured that Flow coefficient of inlet is 0.95 under design point Ma=6,
And general side pressure Design of Inlet point discharge coefficient is between 0.85~0.9, while improving the traffic capture characteristic of air intake duct
Effectively lift the compressibility of air intake duct High Mach number.
Referring to table 1, when being worked by low mach, second level top pressing board 6 is rotated down, secondary channels are opened, air intake duct
Resistance significantly reduces, and discharge coefficient is substantially improved.When free stream Mach number is 1.5, discharge coefficient improves 180%, air intake duct resistance
Power reduces 42%；When free stream Mach number is 2.0, discharge coefficient improves 173%, and Inlet drag reduces 39%.
Table 1
| Ma | H(km) | Mae | Pressure rises | Discharge coefficient | Resistance (N) | Total pressure recovery coefficient |
| 1.5 (after rotations) | 6 | 1.03 | 1.72 | 0.424 | 1249 | 0.93 |
| 1.5 (before rotations) | 6 | 1.18 | 1.16 | 0.144 | 2142 | 0.85 |
| (2.0 after rotation) | 8 | 1.23 | 2.46 | 0.52 | 1597 | 0.82 |
| 2.0 (before rotations) | 8 | 1.28 | 2.2 | 0.19 | 2635 | 0.82 |
Claims (3)
1. a kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet, including air intake duct, combustion chamber, jet pipe, draw
Flow tube, it is characterised in that:Also include the first top pressing board, the second top pressing board, side plate, distance piece top plate, lip plate, center support plate,
First top pressing board and the second top pressing board, distance piece top plate are located at air intake duct bottom respectively, and distance piece top plate is connected to the second top pressure
Plate rear end, drainage tube is connected with air intake duct is transitioned into combustion chamber latter end；Lip plate is movable along side plate by Driven by Hydraulic Cylinder
To change air intake duct contract ratio, spillway discharge is adjusted, center support plate is located at the rear portion of lip plate；Side plate bottom is arc line shaped, with
Second top pressing board faying face position will not interfere in movement or gap occurs；First top pressing board passes through with the second top pressing board
Rotating shaft is hinged, and is rotated around the axis by the top pressing board of Driven by Hydraulic Cylinder second, secondary channels is in the state being turned on and off；When entering
When air flue low mach works, the second top pressing board is rotated down, and secondary channels are opened, and fraction introduces combustion chamber latter end, reduction
Ejector Mode Inlet drag, suppresses jet pipe and crosses expansion increase thrust to lift engine performance；When the sub- super burn mould of air intake duct
When state works, secondary channels are closed, and movable lip plate blocks pressure difference overflow window segment to improve Flow coefficient of inlet.
2. rocket based combined cycle engine according to claim 1 becomes geometry Sidewall-compression inlet, it is characterised in that:Institute
It is 5.7 °, the first top pressing board wedge surface angle, θ to state center support plate semiapex angle θ1For 6 °, the second top pressing board wedge surface angle, θ2For 6.5 °.
3. rocket based combined cycle engine according to claim 1 becomes geometry Sidewall-compression inlet, it is characterised in that:Institute
The center support plate of stating is received to distance piece, reduces air intake duct low mach resistance, while weakening shoulder separation, is received in increase air intake duct
Contracting section entrance the ratio of width to height.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510648492.XA CN105156212B (en) | 2015-10-09 | 2015-10-09 | A kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet |
Applications Claiming Priority (1)
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| CN201510648492.XA CN105156212B (en) | 2015-10-09 | 2015-10-09 | A kind of rocket based combined cycle engine becomes geometry Sidewall-compression inlet |
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| CN105156212B true CN105156212B (en) | 2017-08-29 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107061010B (en) * | 2017-03-23 | 2019-01-01 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN108915894B (en) * | 2018-07-03 | 2023-09-26 | 西北工业大学 | RBCC variable geometry full flow passage working in wide range |
| CN109236472B (en) * | 2018-11-27 | 2019-08-16 | 北京航空航天大学 | A kind of axial symmetry change geometry bimodal air intake duct adapting to broad Mach number |
| CN111412066B (en) * | 2020-04-27 | 2023-04-04 | 南昌航空大学 | Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube and design method |
| CN111594345B (en) * | 2020-05-01 | 2023-03-31 | 西北工业大学 | Method for improving starting capability of RBCC (radial basis channel charge coupled device) air inlet |
| CN111946462B (en) * | 2020-08-04 | 2021-10-26 | 中山大学 | Design structure for improving total pressure recovery coefficient of combustion chamber inlet and optimizing air inlet channel |
| CN112627990B (en) * | 2020-12-23 | 2021-11-19 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| 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 |
| CN113236424B (en) * | 2021-06-22 | 2022-07-05 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN114876666B (en) * | 2022-06-10 | 2024-04-19 | 厦门大学 | Design method of suction type scramjet engine considering secondary flow system |
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| IL62132A0 (en) * | 1980-02-26 | 1981-03-31 | Gen Electric | Inlet cowl for a two-dimensional inlet |
| CN102748135B (en) * | 2012-07-29 | 2013-12-25 | 西北工业大学 | Method for designing fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel |
| CN104632411B (en) * | 2015-01-28 | 2016-08-24 | 南京航空航天大学 | Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways |
| CN104899418B (en) * | 2015-04-24 | 2016-07-13 | 南京航空航天大学 | The inoperative frequency of oscillation Forecasting Methodology of mixed pressure formula supersonic speed, hypersonic inlet |
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