CN106968835A - Full runner is combined in a kind of rocket punching press of wide scope work - Google Patents
Full runner is combined in a kind of rocket punching press of wide scope work Download PDFInfo
- Publication number
- CN106968835A CN106968835A CN201710244028.3A CN201710244028A CN106968835A CN 106968835 A CN106968835 A CN 106968835A CN 201710244028 A CN201710244028 A CN 201710244028A CN 106968835 A CN106968835 A CN 106968835A
- Authority
- CN
- China
- Prior art keywords
- support plate
- runner
- combustion
- punching press
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
Full runner is combined the invention discloses the rocket punching press of wide scope work, including being sequentially connected compression section in the air intake duct connect, combustion chamber and jet pipe from front to back, combustion chamber includes super burn combustion section and sub- combustion combustion section from front to back, longitudinally split at its in super burn combustion section is three independent runners, and runner is connected with Asia combustion combustion chamber；The front end of runner is inlet end, is correspondingly formed three independent air inlets；Three independent runners are surrounded by the two side for being arranged at intervals at super burn combustion section Nei Liangge center support plates and super burn combustion section；The rear end of center support plate offers multiple Rocket ejector jet pipe mounting holes being connected with cavity；The inside of center support plate is hollow cavity, and cavity is used to be connected with fuel tank, is spaced apart from front to back on the two sides of center support plate and is provided with multiple fuel nozzle ports being connected with cavity.The full runner of rocket punching press combination of wide scope work is multi-modal to share runner, and runner autgmentability is high, structure changes form is simple.
Description
Technical field
The invention belongs to rocket based combined cycle technical field of engines, and in particular to a kind of rocket punching of wide scope work
The full runner of pressure combination.
Background technology
Only needed to compared to existing dynamical system in narrower interval work, the big spatial domain of rocket punching press combination (RBCC) propulsion,
The characteristics of wide speed domain flight, the full runner design to rocket punching press assembly power brings great challenge.Fixed structure
The key of RBCC combustion chambers configurations design is to adapt to the inlet flow conditions change of wide Mach number, and keep combustion chamber flow area with
Burning heat release amount matches, to complete the work of the stability and high efficiency under different modalities.Chamber performance depends primarily on combustion chamber gas
The heating amount obtained is flowed, in Ejector Mode, in order to ensure the swabbing action of rocket jet and weaken second-time burning empty to injection
The influence of tolerance is, it is necessary to larger combustion chamber circulation area；Mode is fired in Asia, due to the limitation of distance piece pressure ratio, in order to ensure
The normal work of runner, combustion chamber needs appropriate reduction propellant spray equivalent proportion to reduce total thermal discharge, increases combustion chamber area
Divergence ratio can increase the heating amount of permission, but then be much smaller than Ejector Mode at this point for the demand of increase circulation area；Super
Mode is fired, because heating amount of the fuel combustion into air-flow reduces, it is necessary to which less combustion chamber divergence ratio is to meet to air-flow
Decelerating effect, so as to ensure combustion efficiency of the fuel under higher speed of incoming flow.
Structure changes runner is to realize that RBCC different modalities, come the necessary means for the demand of flowing, stream are can effectively improve by structure changes
Performance of the road under off-design point, reduce resistance, so as to realize the lifting of the integrated service behaviour of the full runners of RBCC.Compared to adopting
With the RBCC engines of thermal throat, structure changes jet pipe then can further lift the performance of injection and sub- combustion mode.
The content of the invention
The technical problems to be solved by the invention are to share stream there is provided multi-modal for above-mentioned the deficiencies in the prior art
Road, runner autgmentability is high, full runner is combined in the rocket punching press of the simple wide scope work of structure changes form.
In order to solve the above technical problems, the technical solution adopted by the present invention is, a kind of rocket punching press group of wide scope work
Full runner is closed, including is sequentially connected compression section in the air intake duct connect, combustion chamber and jet pipe from front to back, combustion chamber is from front to back
Including super burn combustion section and sub- combustion combustion section, longitudinally split at its in super burn combustion section is three independent runners, stream
Road is connected with Asia combustion combustion chamber；The front end of runner is inlet end, is correspondingly formed three independent air inlets；Three independent
Runner is surrounded by the two side for being arranged at intervals at super burn combustion section Nei Liangge center support plates and super burn combustion section；Center branch
The rear end of plate offers multiple Rocket ejector jet pipe mounting holes being connected with cavity；The inside of center support plate is hollow chamber
Body, cavity is used to be connected with fuel tank, is spaced apart from front to back provided with multiple with cavity phase on the two sides of center support plate
The fuel nozzle ports of connection.
Under Ejector Mode, when free stream Mach number is 0~2, three runners are unimpeded, meanwhile, two center support plates are relative
The fuel nozzle ports of side mix the stream that comes of fuel and intermediate flow channel towards intermediate flow channel spray fuel, and fire combustion chamber in Asia
Burnt in section；
Under Asia combustion mode, when free stream Mach number is 2~4, three runners are unimpeded, meanwhile, the two of two center support plates
The fuel nozzle ports of side are towards corresponding runner spray fuel, fuel and to flow in the burning of super burn combustion section；
Under super burn mode, when free stream Mach number is 5~7, two side runners are closed, and intermediate flow channel is unimpeded, two center branch
The fuel nozzle ports of the opposite side of plate are towards intermediate flow channel spray fuel, and in super burn combustion section mixed combustion.
Further, it is additionally provided with igniter on the center support plate.
Further, in addition to the pendulum cone that is arranged in jet pipe, pendulum cone is big wedge shape after paracone, and the front end of wedge shape
Tip is arranged on combustion chamber upper rear end, and pendulum cone is using its front end tip as fixed rotating shaft, on away from or towards jet pipe inside
It is lower to rotate.
Further, from front to back, being projected as in the horizontal plane is trapezoidal for the center support plate.
Further, the left and right sides is each provided with support plate, air inlet in an air intake duct in compression section in the air intake duct
Support plate compression section in air intake duct is moved in road, to open or close the air inlet of respective side.
Further, support plate in carriage, air intake duct is provided with the air intake duct on the side wall of compression section and is sliding dress
Put and move up and down, to realize opening or closing to air inlet.
A kind of rocket punching press of wide scope work of the present invention is combined full runner and had the following advantages that：1. runner is using parallel side
Runner can be shared between formula, each mode, fuel is caused by the way of multiple flow passages in width of flow path direction while organizing burning, contracting
Short burner interval.2. the integrated igniting of center support plate, fuel injection, afterbody install Rocket ejector, fuel blending distance can be shortened,
Improve the mixing effect of fuel and air.Center support plate lifting fuel penetration depth 30%.3. runner scalability is high, by increasing
Plus runner quantity can meet multiple module paralleling, by controlling switch runner quantity, to realize flow area and inlet flow rate
Matching.4. with the use of pendulum cone, jet pipe geometrical throat area is adjustable, improves combustibility.
Brief description of the drawings
Fig. 1 is the structural representation that full runner is combined in the rocket punching press that a kind of wide scope works；
Fig. 2 is that being provided with behind the combustion chamber of center support plate in full runner is combined in the rocket punching press that a kind of wide scope works
View；
Wherein：A. compression section in air intake duct；B. combustion chamber；C. jet pipe；1. super burn combustion section；2. Asia combustion combustion chamber
Section；3. runner；4. center support plate；5. fuel nozzle ports；6. Rocket ejector jet pipe mounting hole；7. pendulum cone；8. air inlet；9. air intake duct
Interior support plate.
Embodiment
Full runner is combined in a kind of rocket punching press of wide scope work of the present invention, as depicted in figs. 1 and 2, including from front to back
Compression section a in the air intake duct connect, combustion chamber b and jet pipe c are sequentially connected, combustion chamber a includes super burn combustion section 1 from front to back
It is three independent runners 3 to be fired longitudinally split at its in combustion section 2, super burn combustion section 1 with Asia, and runner 3 fires with Asia combustion
Room 2 is burnt to be connected；The front end of runner 3 is inlet end, is correspondingly formed three independent air inlets 8；Three independent runners 3 by
Surrounded every the two side for being arranged at the Nei Liangge centers support plate 4 of super burn combustion section 1 and super burn combustion section 1；Center support plate 4
Rear end offers multiple Rocket ejector jet pipe mounting holes 6 being connected with cavity；The inside of center support plate 4 is hollow cavity,
Cavity is used to be connected with fuel tank, is spaced apart and is connected provided with multiple with cavity from front to back on the two sides of center support plate 4
Logical fuel nozzle ports 5.Igniter is additionally provided with center support plate 4.
Under Ejector Mode, when free stream Mach number is 0~2, three runners 3 are unimpeded, meanwhile, two phases of center support plate 4
The fuel nozzle ports 5 of offside mix fuel and the stream that comes of intermediate flow channel 3 towards the spray fuel of intermediate flow channel 2, and in Asia combustion combustion
Burn in room section 2 and burn.
Under Asia combustion mode, when free stream Mach number is 2~4, three runners 3 are unimpeded, meanwhile, two center support plates 4
The fuel nozzle ports 5 of two sides fuel and are burnt towards the corresponding spray fuel of runner 3 to flow in super burn combustion section 1.
Under super burn mode, when free stream Mach number is 5~7, two side runners 3 are closed, and intermediate flow channel 3 is unimpeded, two centers
The fuel nozzle ports 5 of the opposite side of support plate 4 are towards the spray fuel of intermediate flow channel 3, and in the mixed combustion of super burn combustion section 1.
Also include the pendulum cone 7 being arranged in jet pipe c, pendulum cone 7 to make jet pipe geometrical throat area adjustable, in the present invention
For wedge shape big after paracone, and the front end tip of wedge shape is arranged on combustion chamber b upper rear ends, pendulum cone 7 using its front end tip be solid
Determine rotating shaft, rotated upwardly and downwardly to inside away from or towards jet pipe c.Center support plate 4 from front to back, in the horizontal plane be projected as ladder
Shape.The left and right sides is each provided with support plate 9 in an air intake duct, air intake duct support plate 9 described in a of compression section in air intake duct
Compression section a is moved in air intake duct, to open or close the air inlet of respective side.Set in the air intake duct on compression section a side wall
It is equipped with support plate 9 in carriage, air intake duct to move up and down on carriage, to realize opening or closing to air inlet 8.
Full runner is combined in a kind of rocket punching press of wide scope work in the present invention, and under Ejector Mode, free stream Mach number is 0
When~2, three runners 3 are opened simultaneously, the opposite side spray fuel of two center support plates 4, are existed with jet shielding injection SPI mode
Burnt in Asia combustion combustion section 2.Under Asia combustion mode, when free stream Mach number is 2~4, three runners 3 are unimpeded, meanwhile, two
The fuel nozzle ports 5 of the two sides of center support plate 4 are towards the corresponding spray fuel of runner 3, fuel and to flow in super burn combustion chamber
Section 1 is burnt；Meanwhile, pendulum cone 7 forms the geometry jet pipe with smaller throat opening area towards jet pipe c inner rotations.In super burn mould
Under state, when free stream Mach number is 5~7, two side runners 3 are closed, and intermediate flow channel 3 is unimpeded, the combustion of the opposite side of two center support plates 4
Spout 5 is expected towards the spray fuel of intermediate flow channel 3, and in the mixed combustion of super burn combustion section 1；Meanwhile, pendulum cone 7 is away from jet pipe c
Inner rotation.
The mentality of designing of the present invention is that multiple flow passages are set in the super burn combustion section 1, can be according to the width of super burn combustion section 1
The number of degree selection setting center support plate 4, the width of super burn combustion section 1 is wider, and the quantity of settable runner 3 is more.Not
It is confined to three runners 3 set in the present invention.
Claims (7)
1. full runner is combined in a kind of rocket punching press of wide scope work, it is characterised in that including being sequentially connected what is connect from front to back
Compression section (a), combustion chamber (b) and jet pipe (c) in air intake duct, the combustion chamber (a) include super burn combustion section from front to back
(1) and sub- combustion combustion section (2), the super burn combustion section (1) it is inherent its it is longitudinally split be three independent runners (3), institute
Runner (3) is stated to be connected with Asia combustion combustion chamber (2)；The front end of the runner (3) is inlet end, be correspondingly formed three it is independent
Air inlet (8)；
Three independent runners (3) are by being arranged at intervals at super burn combustion section (1) Nei Liangge centers support plate (4) and super burn
The two side of combustion section (1) is surrounded；The rear end of the center support plate (4) offers multiple Rocket ejectors being connected with cavity
Jet pipe mounting hole (6)；The inside of the center support plate (4) is hollow cavity, and the cavity is used to be connected with fuel tank,
It is spaced apart from front to back on the two sides of the center support plate (4) and is provided with multiple fuel nozzle ports (5) being connected with cavity.
2. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 1, it is characterised in that in injection mould
Under state, when free stream Mach number is 0~2, three runners (3) are unimpeded, meanwhile, two center support plate (4) opposite sides
Fuel nozzle ports (5) towards intermediate flow channel (2) spray fuel, mix fuel and the stream that comes of intermediate flow channel (3), and Asia combustion
Burnt in combustion section (2)；
Under Asia combustion mode, when free stream Mach number is 2~4, three runners (3) are unimpeded, meanwhile, two center branch
The fuel nozzle ports (5) of the two sides of plate (4) are towards corresponding runner (3) spray fuel, fuel and to flow in super burn combustion chamber
Section (1) burning；
Under super burn mode, when free stream Mach number is 5~7, two side runners (3) are closed, and intermediate flow channel (3) is unimpeded, described in two
The fuel nozzle ports (5) of the opposite side of center support plate (4) are mixed towards intermediate flow channel (3) spray fuel, and in super burn combustion section (1)
Combination burning.
3. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 2, it is characterised in that the center
Support plate is additionally provided with igniter on (4).
4. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 2 or claim 3, it is characterised in that also wrapped
Include the pendulum cone (7) being arranged in jet pipe (c), the pendulum cone (7) is big wedge shape after paracone, and the front end tip of wedge shape is installed
In combustion chamber (b) upper rear end, the pendulum cone (7) is using its front end tip as fixed rotating shaft, to away from or towards in jet pipe (c)
Portion is rotated upwardly and downwardly.
5. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 4, it is characterised in that the center
From front to back, being projected as in the horizontal plane is trapezoidal for support plate (4).
6. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 5, it is characterised in that the air inlet
The left and right sides is each provided with an air intake duct that support plate (9) exists in support plate (9), the air intake duct in compression section (a) in road
Compression section (a) is mobile in the air intake duct, to open or close the air inlet of respective side.
7. full runner is combined in a kind of rocket punching press of wide scope work as claimed in claim 6, it is characterised in that the air inlet
Support plate (9) in carriage, the air intake duct is provided with road on the side wall of compression section (a) to move up and down on carriage,
To realize opening or closing to air inlet (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710244028.3A CN106968835B (en) | 2017-04-14 | 2017-04-14 | Full runner is combined in a kind of rocket punching press of wide scope work |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710244028.3A CN106968835B (en) | 2017-04-14 | 2017-04-14 | Full runner is combined in a kind of rocket punching press of wide scope work |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106968835A true CN106968835A (en) | 2017-07-21 |
| CN106968835B CN106968835B (en) | 2018-07-06 |
Family
ID=59333307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710244028.3A Active CN106968835B (en) | 2017-04-14 | 2017-04-14 | Full runner is combined in a kind of rocket punching press of wide scope work |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106968835B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108798934A (en) * | 2018-04-28 | 2018-11-13 | 西北工业大学 | Become mode fractional combustion solid-rocket punching press combined engine |
| CN108825405A (en) * | 2018-07-03 | 2018-11-16 | 西北工业大学 | A kind of full runner of axially symmetric structure RBCC using multistep rocket |
| 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 |
| CN109779784A (en) * | 2018-12-14 | 2019-05-21 | 西安航天动力研究所 | A kind of RBCC engine inner flow passage of the preposition center layout of rocket |
| CN109882886A (en) * | 2018-12-21 | 2019-06-14 | 西安航天动力研究所 | A kind of the RBCC engine chamber and its design method of slope rocket layout type |
| CN112780442A (en) * | 2019-11-05 | 2021-05-11 | 北京动力机械研究所 | Adjustable runner ramjet engine and design and adjustment method |
| CN113028453A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN113586246A (en) * | 2021-09-08 | 2021-11-02 | 南京航空航天大学 | Fixed-geometry binary hypersonic inlet with pre-injection at precursor |
| CN114483381A (en) * | 2021-12-21 | 2022-05-13 | 西北工业大学 | Variable structure engine jet pipe using combined dynamic seal |
| CN115807716A (en) * | 2022-12-05 | 2023-03-17 | 西安交通大学 | Oblique detonation engine |
| CN116335852A (en) * | 2023-02-07 | 2023-06-27 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2701293B1 (en) * | 1993-02-05 | 1995-04-28 | Europ Propulsion | Combined engine incorporating ejector modes with turbocharged air cooled or liquefied ramjet and super ramjet. |
| CN102374071A (en) * | 2011-09-15 | 2012-03-14 | 西北工业大学 | Center rocket type bimodal ramjet with circular structure |
| FR2987081B1 (en) * | 2012-02-21 | 2017-03-31 | Snecma | PROPELLANT ASSEMBLY AND METHOD |
| CN105156227B (en) * | 2015-09-29 | 2017-04-19 | 清华大学 | Pre-cooling air-breathing type variable cycle engine |
| CN205578133U (en) * | 2016-03-29 | 2016-09-14 | 杨庆春 | Super combustion pressed engine |
| 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 |
-
2017
- 2017-04-14 CN CN201710244028.3A patent/CN106968835B/en active Active
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108798934B (en) * | 2018-04-28 | 2019-04-30 | 西北工业大学 | Become mode fractional combustion solid-rocket punching press combined engine |
| CN108798934A (en) * | 2018-04-28 | 2018-11-13 | 西北工业大学 | Become mode fractional combustion solid-rocket punching press combined engine |
| CN108825405A (en) * | 2018-07-03 | 2018-11-16 | 西北工业大学 | A kind of full runner of axially symmetric structure RBCC using multistep rocket |
| 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 |
| CN109779784A (en) * | 2018-12-14 | 2019-05-21 | 西安航天动力研究所 | A kind of RBCC engine inner flow passage of the preposition center layout of rocket |
| CN109882886A (en) * | 2018-12-21 | 2019-06-14 | 西安航天动力研究所 | A kind of the RBCC engine chamber and its design method of slope rocket layout type |
| CN112780442A (en) * | 2019-11-05 | 2021-05-11 | 北京动力机械研究所 | Adjustable runner ramjet engine and design and adjustment method |
| CN112780442B (en) * | 2019-11-05 | 2022-05-20 | 北京动力机械研究所 | Adjustable runner ramjet engine and design and adjustment method |
| CN113028453B (en) * | 2021-04-09 | 2022-07-01 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN113028453A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN113586246A (en) * | 2021-09-08 | 2021-11-02 | 南京航空航天大学 | Fixed-geometry binary hypersonic inlet with pre-injection at precursor |
| CN113586246B (en) * | 2021-09-08 | 2022-07-26 | 南京航空航天大学 | Fixed-geometry binary hypersonic inlet with pre-injection at precursor |
| CN114483381B (en) * | 2021-12-21 | 2023-08-11 | 西北工业大学 | Variable structure engine spray pipe using combined dynamic seal |
| CN114483381A (en) * | 2021-12-21 | 2022-05-13 | 西北工业大学 | Variable structure engine jet pipe using combined dynamic seal |
| CN115807716A (en) * | 2022-12-05 | 2023-03-17 | 西安交通大学 | Oblique detonation engine |
| CN115807716B (en) * | 2022-12-05 | 2024-07-09 | 西安交通大学 | Oblique knocking engine |
| CN116335852A (en) * | 2023-02-07 | 2023-06-27 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
| CN116335852B (en) * | 2023-02-07 | 2023-09-01 | 中国空气动力研究与发展中心空天技术研究所 | Stamping engine tail nozzle of integrated enhanced rocket and design and working methods thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106968835B (en) | 2018-07-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106968835B (en) | Full runner is combined in a kind of rocket punching press of wide scope work | |
| CN106907272B (en) | Structure changes Rocket based combined cycle engine | |
| CN107013368B (en) | Turbine base double combustion chamber's punching press combined cycle engine control method | |
| CN107013367B (en) | Turbine base double combustion chamber's punching press combined cycle engine | |
| CN109139297B (en) | A kind of device combining enhancing blending for solid-rocket scramjet engine | |
| CN107620653B (en) | A kind of disturbing flow device for solid-rocket combustion gas scramjet engine | |
| CN110307563B (en) | Wide-area stamping combustion chamber and combustion organization method | |
| CN104373964A (en) | Cavity supporting plate flame stabilizer with built-in oil rod | |
| CN108825405B (en) | Axial symmetry structure RBCC full flow channel adopting multi-stage rocket | |
| CN203517805U (en) | Backfire-preventing nozzle connecting section assembly of combustion chamber of gas turbine | |
| CN108915894A (en) | A kind of RBCC change full runner of geometry of wide scope work | |
| CN203906118U (en) | Gas cooling system for turbine-based combined-cycle engine | |
| CN109539310A (en) | A kind of integrated after-burner using adjustable preheating rectification supporting plate | |
| CN106524223A (en) | Combustion chamber with main nozzle module and micro nozzle module | |
| CN203823810U (en) | Advanced vortex combustor with flow deflectors | |
| CN108954393A (en) | A kind of advanced standing vortex burning chamber of built-in flow spoiler | |
| CN102297426B (en) | Hydrogen gas combustor | |
| CN106642202A (en) | Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber | |
| CN110131048B (en) | Self-contained internal combustion wave rotor ignition device and method | |
| CN110319456B (en) | Solid rocket scramjet engine adopting multistage combustion enhancing device | |
| CN102472485A (en) | Stabilizing the flame of a burner | |
| CN109340818B (en) | A kind of engine chamber with guidance combustion chamber | |
| CN115628464B (en) | Three-way scramjet engine combustion chamber | |
| CN106523188B (en) | A kind of distributed air intake duct Exit Cone of Solid Rocket Nozzle aftercombustion device | |
| CN106545434B (en) | A kind of annular inlet Exit Cone of Solid Rocket Nozzle aftercombustion device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |