CN105156212A - Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine - Google Patents
Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine Download PDFInfo
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- CN105156212A CN105156212A CN201510648492.XA CN201510648492A CN105156212A CN 105156212 A CN105156212 A CN 105156212A CN 201510648492 A CN201510648492 A CN 201510648492A CN 105156212 A CN105156212 A CN 105156212A
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- pressing board
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- intake duct
- air inlet
- inlet passage
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Abstract
The invention discloses a variable geometry side pressure type air inlet passage of a rocket-based-combined-cycle (RBCC) engine. Grading adjustment is conducted with the adoption of a variable geometry mode to ensure that the air inlet passage has good properties within the working range of 1.5-7 Ma. The variable geometry side pressure type air inlet passage captures the air volume by lowering the low Mach number to achieve low Mach number start of the air inlet passage; an auxiliary passage is opened by rotating a second pressure pushing plate; part of airflow is introduced into the tail end of a combustion chamber, so that the resistance of the air inlet passage in an ejecting mode is lowered, and meanwhile the airflow introduced into the tail end of the combustion chamber restrains a tail ejecting pipe from overexpansion to increasing thrust, and accordingly the performance of the whole engine is improved by a large margin, and the rate of fuel consumption in the ejecting mode is lowered. The auxiliary passage is closed during the operation in a subsonic-supersonic-combustion mode, and a lip opening plate is moved forward or backward to cover and shelter a certain part of a pressure difference overflow window, so that the flow coefficient of the air inlet passage and the total pressure recovery coefficient are effectively increased. The side pressure type air inlet passage has the advantages of being simple and easy to achieve, and it is ensured that the air inlet passage has good performance during the operation interval of the whole engine.
Description
Technical field
The present invention relates to rocket ramjet technical field, specifically, relate to a kind of rocket based combined cycle motor and become geometry Sidewall-compression inlet.
Background technique
Rocket based combined cycle (Rocket-Based-Combined-Cycle, RBCC) rocket motor and airbreathing motor organically combine in a runner by motor, by Mode-switch, all work can be carried out in an optimal manner when different flight Mach numbers and height.Along with the difference of flight Mach number, rocket based combined cycle motor mainly experiences four groundwork mode: rocket ejector mode, sub-combustion punching press mode, ultra-combustion ramjet mode and pure rocket mode.Rocket based combined cycle motor is made up of four parts substantially: intake duct, the main rocket be embedded in runner, firing chamber and jet pipe.Be subject to the impact that rocket based combined cycle starts the work of machine width envelope curve, rocket based combined cycle intake duct should ensure to start compared with low mach the accelerating ability improving the Ejector Mode later stage, ensures that sub-super burn mode has preferably performance again.The work range of Mach numbers under intake duct starting state can be widened by change geometry, and improve the combination property of intake duct.
At present, external existing disclosed technical paper, " Hyper-XFlightEngineGroundTestingforX-43FlightRiskReducti on [R] " (HuebnerlD of the U.S., RockKE, RufEG, etc.AIAA2001-1809), in literary composition, X-43A adopts the regulative mode rotating lip; X-43A by B-52 carry, and by " flying horse " booster rocket boosting, but the self-starting performance of not checking intake duct.The PIFA concept engine that the outer cover proposed in " French-RussianCooperationonHigh-SpeedAirbreathingPropuls ion [R] " (MarcBOUCHEZ, VadimLEVINE.2003-2907) literary composition of France and Russia's cooperation is movable; PIFA, by moving horizontally the geometric configuration changing whole motor to the outer cover part of fixing profile, adds difficulty to motor runner design.
In domestic disclosed technical paper, " hypersonic side-wall inlet becomes geometrical solution research " (Nanjing Aero-Space University, master thesis in 2012), for side pressure intake duct propose mobile lip, venturi top board venting and lip rotate three kinds become geometrical solution, to study intake duct operating range be 4 ~ 7Ma, do not relate to inlet characteristic under rocket based combined cycle motor Ejector Mode work Mach number.Therefore, in order to make rocket based combined cycle motor have comparatively dominance energy at whole operation interval, meet the change geometrical solution difference of intake duct required under different operating mode most important.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of rocket based combined cycle motor and becomes geometry Sidewall-compression inlet, by mobile lip and rotation second level top pressing board, improve intake duct starting performance, solve intake duct under low mach catch air mass flow and throat to allow by air mass flow between matching problem, while reducing Ejector Mode Inlet drag, suppress jet pipe overexpansion to increase thrust by a part of fluid being introduced burner ends, thus reduce Ejector Mode specific fuel consumption.
The technical solution adopted for the present invention to solve the technical problems is: comprise intake duct, firing chamber, jet pipe, drainage tube, characterized by further comprising the first top pressing board, the second top pressing board, side plate, distance piece top board, lip plate, center support plate, first top pressing board and the second top pressing board, distance piece top board lay respectively at bottom intake duct, distance piece top board is connected to the second top pressing board rear end, and drainage tube is connected with intake duct and is transitioned into firing chamber latter end; Lip plate to be moved forward and backward along side plate by Driven by Hydraulic Cylinder and changes contraction ratio in intake duct, regulates spillway discharge; Side plate bottom is arc line shaped, can not interfere with the second top pressing board junction plane position or occur gap when mobile; It is hinged that first top pressing board and the second top pressing board pass through rotating shaft, rotated around the axis by Driven by Hydraulic Cylinder second top pressing board, makes secondary channels be in the state of opening or closing; When intake duct low mach works, the second top pressing board rotates, and secondary channels is opened, and fraction introduces burner ends, reduces Ejector Mode Inlet drag, suppresses jet pipe overexpansion to increase thrust and promotes engine performance; When the sub-super burn Modality work of intake duct, secondary channels is closed, and movable lip plate blocks pressure reduction overflow window part to improve Flow coefficient of inlet.
Described center support plate semiapex angle θ is 5.7 °, and the first top pressing board wedge surface angle θ 1 is 6 °, and the second top pressing board wedge surface angle θ 2 is 6.5 °.
Described center support plate is received in distance piece, reduces intake duct low mach resistance, weaken simultaneously shoulder portion from, increase contraction section entrance Aspect Ratio in intake duct.
Beneficial effect
The rocket based combined cycle motor that the present invention proposes becomes geometry Sidewall-compression inlet, in 1.5 ~ 7Ma operating range, all have preferably performance by intake duct under different Mach number in classification regulating guarantee flight range.Compared with prior art, change geometry Sidewall-compression inlet is caught air quantity by reduction low mach and is realized the starting of intake duct low mach, by rotating second level top pressing board, while reducing Ejector Mode Inlet drag, a part of air-flow being introduced burner ends suppresses jet pipe overexpansion to increase thrust, thus significantly promotes whole rocket based combined cycle engine performance.Lip shape covers certain pressure reduction overflow window in " V " type, effectively improves Flow coefficient of inlet and total pressure recovery coefficient.
Rocket based combined cycle motor of the present invention becomes geometry Sidewall-compression inlet, adopts the advantage becoming geometric ways and have simply, easily realize, and can ensure that intake duct has preferably performance in whole rocket based combined cycle engine operation interval.
Accompanying drawing explanation
Become geometry Sidewall-compression inlet below in conjunction with drawings and embodiments to a kind of rocket based combined cycle motor of the present invention to be described in further detail.
Fig. 1 is rocket based combined cycle engine structure schematic diagram.
Fig. 2 is that RBCC motor becomes geometry Sidewall-compression inlet schematic diagram.
Fig. 3 is that RBCC motor becomes geometry Sidewall-compression inlet plan view.
Fig. 4 is Mach number cloud atlas under RBCC motor change geometry Sidewall-compression inlet design point.
Fig. 5 is Mach number cloud atlas plan view under RBCC motor change geometry Sidewall-compression inlet design point.
In figure:
1. intake duct 2. firing chamber 3. jet pipe 4. drainage tube 5. first top pressing board 6. second top pressing board 7. side plate 8. distance piece top board 9. lip plate 10. center support plate
Embodiment
The present embodiment is that a kind of rocket based combined cycle motor becomes geometry Sidewall-compression inlet.
Consult Fig. 1 ~ Fig. 5, rocket based combined cycle motor becomes geometry Sidewall-compression inlet and is made up of intake duct 1, firing chamber 2, jet pipe 3, drainage tube 4 and the first top pressing board 5, second top pressing board 6, side plate 7, distance piece top board 8, lip plate 9, center support plate 10; First top pressing board 5 and the second top pressing board 6, distance piece top board 8 are arranged on bottom intake duct 1 respectively, and distance piece top board 8 is connected to the rear end of the second top pressing board 6, and drainage tube 4 is connected with intake duct 1 and is transitioned into firing chamber 2 latter end, and jet pipe 3 is arranged on rear end, firing chamber 2.Lip plate 9 to be moved forward and backward along side plate 7 by Driven by Hydraulic Cylinder and changes contraction ratio in intake duct 1, regulates spillway discharge, ensures that intake duct normally works and meets entry of combustion chamber conditional request.Side plate 7 bottom is processed as arc line shaped, and side plate 7 and second pushes up pressure 6 and hardens and close facial position and can not interfere or occur gap when mobile.It is hinged that first top pressing board 5 and the second top pressing board 6 pass through rotating shaft, rotated around the axis, make secondary channels be in the state of opening or closing by Driven by Hydraulic Cylinder second top pressing board 6; When intake duct 1 low mach works, the second top pressing board 6 rotates, and secondary channels is opened, and fraction introduces firing chamber 2 end, reduces Inlet drag when Ejector Mode works, and suppresses jet pipe 3 overexpansion to increase thrust and promotes engine performance; When the sub-super burn Modality work of intake duct, secondary channels is closed, and movable lip plate 9 blocks pressure reduction overflow window part to improve Flow coefficient of inlet.
Center support plate 10 is received in distance piece, reduces intake duct low mach resistance, weaken simultaneously shoulder portion from, increase contraction section entrance Aspect Ratio in intake duct.
In the present embodiment, rocket based combined cycle motor become geometry Sidewall-compression inlet choose Design of Inlet parameter into: catching flow is 3.2kg/s; Design Mach 2 ship 6.0; Start mach number is lower than 2.0.Inlet mouth Aspect Ratio W1/H1 is 1.23, and main support plate dutycycle D/W2 is 0.3, and total contraction ratio W1 × H1/W2 × H2 is 6.35, and top pressure direction contraction ratio H1/H2 is 4.28, and side direction contraction ratio W1/W2 is 1.48, self-starting Mach 2 ship 1.8.In order to reduce intake duct length, center support plate semiapex angle θ is comparatively large, is taken as 5.7 °.Two-stage top pressure wedge surface angle θ 1 and θ 2 is respectively 6 ° and 6.5 °, shoulder arc transition, and knuckle radius is 500mm.Little greatly upper under side plate 7 angle, transition gradually, weakens side pressure shock wave and top board boundary layer disturbs mutually, reduces pressure reduction overflow while keeping top board boundary layer stability, increases intake duct and catches flow.
In the present embodiment, rocket based combined cycle motor become geometry Sidewall-compression inlet level Four regulative mode into:
Configuration I operating range is Ma=1.5 ~ 2.0, lip plate 9 is at position 1 place, and second level top pressing board 6 rotates, and main passage and secondary channels are opened simultaneously, increase while low mach catches air quantity, not mating of air intake port and entry of combustion chamber configuration can not be caused again;
Configuration II operating range is Ma=2.0 ~ 2.8, and second level top pressing board 6 upwards rotates, and secondary channels is closed, and lip plate 9 is still at position 1 place;
Configuration III operating range is Ma=2.8 ~ 3.5, and lip plate 9 moves forward to position 2 place;
Configuration IV operating range is Ma=3.5 ~ 7, and lip plate 9 moves forward to position 3 place.
Become geometry Sidewall-compression inlet design point from rocket based combined cycle motor and can find out in Mach number cloud atlas, by the change of lip shape by pressure reduction overflow window partial occlusion, ensure that Flow coefficient of inlet is 0.95 under design point Ma=6, and general side pressure Design of Inlet point flow coefficient is between 0.85 ~ 0.9, while improving the traffic capture characteristic of intake duct, effectively promote the compressibility of intake duct High Mach number.
See table 1, when being worked by low mach, rotated by second level top pressing board 6, secondary channels is opened, and Inlet drag significantly reduces, and flow coefficient significantly promotes.When free stream Mach number is 1.5, flow coefficient improves 180%, and Inlet drag reduces 42%; When free stream Mach number is 2.0, flow coefficient improves 173%, and Inlet drag reduces 39%.
Table 1
| Ma | H(km) | Mae | Voltage rise | Flow coefficient | Resistance (N) | Total pressure recovery coefficient |
| 1.5 (after rotating) | 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 rotating) | 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 rocket based combined cycle motor becomes geometry Sidewall-compression inlet, comprise intake duct, firing chamber, jet pipe, drainage tube, it is characterized in that: also comprise the first top pressing board, the second top pressing board, side plate, distance piece top board, lip plate, center support plate, first top pressing board and the second top pressing board, distance piece top board lay respectively at bottom intake duct, distance piece top board is connected to the second top pressing board rear end, and drainage tube is connected with intake duct and is transitioned into firing chamber latter end; Lip plate to be moved forward and backward along side plate by Driven by Hydraulic Cylinder and changes contraction ratio in intake duct, regulates spillway discharge; Side plate bottom is arc line shaped, can not interfere with the second top pressing board junction plane position or occur gap when mobile; It is hinged that first top pressing board and the second top pressing board pass through rotating shaft, rotated around the axis by Driven by Hydraulic Cylinder second top pressing board, makes secondary channels be in the state of opening or closing; When intake duct low mach works, the second top pressing board rotates, and secondary channels is opened, and fraction introduces burner ends, reduces Ejector Mode Inlet drag, suppresses jet pipe overexpansion to increase thrust and promotes engine performance; When the sub-super burn Modality work of intake duct, secondary channels is closed, and movable lip plate blocks pressure reduction overflow window part to improve Flow coefficient of inlet.
2. rocket based combined cycle motor according to claim 1 becomes geometry Sidewall-compression inlet, it is characterized in that: described center support plate semiapex angle θ is 5.7 °, and the first top pressing board wedge surface angle θ 1 is 6 °, and the second top pressing board wedge surface angle θ 2 is 6.5 °.
3. rocket based combined cycle motor according to claim 1 becomes geometry Sidewall-compression inlet, it is characterized in that: described center support plate is received in distance piece, reduce intake duct low mach resistance, weaken simultaneously shoulder portion from, increase contraction section entrance Aspect Ratio in intake duct.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107061010A (en) * | 2017-03-23 | 2017-08-18 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN108915894A (en) * | 2018-07-03 | 2018-11-30 | 西北工业大学 | A kind of RBCC change full runner of geometry of wide scope work |
| CN109236472A (en) * | 2018-11-27 | 2019-01-18 | 北京航空航天大学 | A kind of axial symmetry change geometry bimodal air intake duct adapting to broad Mach number |
| CN111412066A (en) * | 2020-04-27 | 2020-07-14 | 南昌航空大学 | Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube and design method |
| CN111594345A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Method for improving starting capability of RBCC (radial basis function) air inlet passage |
| CN111946462A (en) * | 2020-08-04 | 2020-11-17 | 中山大学 | Design structure for improving total pressure recovery coefficient of combustion chamber inlet and optimizing air inlet channel |
| CN112627990A (en) * | 2020-12-23 | 2021-04-09 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| 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 |
| CN113236424A (en) * | 2021-06-22 | 2021-08-10 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN114876666A (en) * | 2022-06-10 | 2022-08-09 | 厦门大学 | Design method of air-breathing scramjet engine considering secondary flow system |
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| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN104899418A (en) * | 2015-04-24 | 2015-09-09 | 南京航空航天大学 | Method for predicting unstart oscillation frequency of mixed-compression supersonic and hypersonic speed air inlet passage |
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Patent Citations (4)
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| GB2070139A (en) * | 1980-02-26 | 1981-09-03 | Gen Electric | Inlet Cowl for Supersonic Aircraft Engine |
| CN102748135A (en) * | 2012-07-29 | 2012-10-24 | 西北工业大学 | Method for designing fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel |
| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN104899418A (en) * | 2015-04-24 | 2015-09-09 | 南京航空航天大学 | Method for predicting unstart oscillation frequency of mixed-compression supersonic and hypersonic speed air inlet passage |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107061010A (en) * | 2017-03-23 | 2017-08-18 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes air intake duct |
| CN108915894A (en) * | 2018-07-03 | 2018-11-30 | 西北工业大学 | A kind of RBCC change full runner of geometry of wide scope work |
| CN108915894B (en) * | 2018-07-03 | 2023-09-26 | 西北工业大学 | RBCC variable geometry full flow passage working in wide range |
| CN109236472A (en) * | 2018-11-27 | 2019-01-18 | 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 |
| CN111412066A (en) * | 2020-04-27 | 2020-07-14 | 南昌航空大学 | Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube and design method |
| CN111594345A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Method for improving starting capability of RBCC (radial basis function) air inlet passage |
| CN111946462A (en) * | 2020-08-04 | 2020-11-17 | 中山大学 | Design structure for improving total pressure recovery coefficient of combustion chamber inlet and optimizing air inlet channel |
| 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 |
| CN112627990A (en) * | 2020-12-23 | 2021-04-09 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| 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 |
| CN113236424A (en) * | 2021-06-22 | 2021-08-10 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN114876666A (en) * | 2022-06-10 | 2022-08-09 | 厦门大学 | Design method of air-breathing scramjet engine considering secondary flow system |
| 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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