CN106642202A - Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber - Google Patents
Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber Download PDFInfo
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- CN106642202A CN106642202A CN201611209284.0A CN201611209284A CN106642202A CN 106642202 A CN106642202 A CN 106642202A CN 201611209284 A CN201611209284 A CN 201611209284A CN 106642202 A CN106642202 A CN 106642202A
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- Prior art keywords
- cavity
- chamber
- ante
- fuel injector
- cooling gas
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Classifications
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- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention provides a flame stabilizing device for a TBCC subsonic combustion ramjet engine combustion chamber. The flame stabilizing device for the TBCC subsonic combustion ramjet engine combustion chamber comprises a supporting plate, a cover hood and an on-duty fuel injector bar. The supporting plate and the cover hood are connected together to form a cavity, the on-duty fuel injector bar is arranged in the cavity, the supporting plate has an upper surface and a lower surface, the lower surface has a concave cavity while the upper surface has a convex cavity, the supporting plate has a front cavity and a back cavity, the front cavity is located between the cavity and the back cavity, the front cavity is used for introducing cooling gas, a primary oil way fuel injector bar is arranged in the back cavity, a cooling gas round channel communicating the front cavity with the back cavity is formed between the front cavity and the back cavity, and a cooling gas round channel communicating the front cavity with the cavity is formed between the front cavity and the cavity. By reasonably arranging the fuel supply positions of the on-duty fuel injector bar and the primary oil way and improving the atomizing effect by way of various modes such as pressure atomization, pneumatic atomization and colliding atomization, the ignition property of the TBCC subsonic combustion ramjet engine combustion chamber is improved, the combustion property in a wide range is considered, and the integral property of the TBCC subsonic combustion ramjet engine combustion chamber is improved.
Description
Technical field
The present invention relates to the flame stabilizer of engine chamber.Specifically, the present invention be more particularly directed to be used for TBCC (whirlpools
Wheel base combination circulation, Turbine-based combined cycle) sub- burning ramjet combustion chamber flame stabilizer.
Background technology
The work starting point of TBCC Asias burning ramjet is located at Mach number 2.5, and corresponding combustion chamber is flowing stagnation temperature about
486K, pressure is near the mark atmospheric pressure, and but up to 0.28, this reliable ignition and flame stabilization to combustion chamber is carried gasflow mach number
Huge challenge is gone out.Meanwhile, TBCC Asias burning ramjet also needs to real in the broad range that range of Mach numbers is 2.5～4
Now stably, efficient burning, this is another difficult problem that combustion chamber is faced.
The bluff body flameholder of traditional bluff is difficult to the demand of competent TBCC Asias burning ramjet combustion chamber.
By taking V-groove flameholder as an example, the stabilizer in 250 DEG C of temperature of incoming flow, speed of incoming flow coefficient 0.2, during pressure 0.11MPa,
Stable burning is just difficult to during oil-gas ratio 0.32, it is clear that cannot more adapt to the working range of broadness.
Cavity support plate flameholder is a kind of current flame stabilization scheme for receiving significant attention.
Patent document CN102200292A proposes that a kind of flame stabilization for gas turbine engine augmentor is filled
Put, i.e., the support plate flameholder with cavity, on the basis of aerofoil profile support plate, dashed forward by the curved cavity and trailing edge on support plate
Expand structure and form low speed recirculating zone, realize steady flame purpose.
Patent document CN104373964A proposes a kind of injection system and cavity support plate flame stabilizer integration sets
The scheme of meter, Fuel Injector Bar is built in cavity support plate internal cavities, reduces the amount of parts of after-burner, reduces flowing
Loss, improves the overall performance of after-burner.Meanwhile, built-in Fuel Injector Bar is entered using the cooling air-flow flow through in cavity support plate
Row pneumatic nebulization, further improves the tissue burning capacity of flameholder.
What above-mentioned two patent documents were directed to is following after-burner, and temperature of incoming flow is of a relatively high, can arrive
1000K, fuel oil can reach preferably atomization, evaporation effect, it is uniform with air blending after, it is possible to achieve aviation kerosine from
Combustion.But for the burning ramjet combustion chamber of TBCC Asias, only have 486K or so, fuel spray in work starting point temperature of incoming flow
Change, evaporation is a greater impact, it is necessary to strengthen atomization, the evaporation process of fuel oil in several ways, to ensure to light a fire successfully general
Rate.Simultaneously also must appropriate design combustion method, it is ensured that combustion chamber can have the efficient stable working range of broadness.
The content of the invention
It is therefore an object of the present invention to propose a kind of flame stabilization dress for TBCC Asias burning ramjet combustion chamber
Put, meet the reliable ignition of TBCC Asias burning ramjet combustion chamber, while ensureing stable, efficiently combustion in broad range
Burn.
The present invention proposes a kind of flame stabilizer for TBCC Asias burning ramjet combustion chamber, the flame stabilization
Device includes：Support plate, calotte, Fuel Injector Bar on duty, the support plate links together with the calotte, forms cavity, described on duty
Fuel Injector Bar is arranged in the cavity, and the support plate has upper and lower surface, and the lower surface has cavity, the upper table
Face does not have cavity.Preferably, the Fuel Injector Bar on duty is located at the approximate centre position of the cavity.
Preferred embodiment of the invention, the support plate has ante-chamber and back cavity, and the ante-chamber is used to introduce cooling
Gas, is provided with working connection Fuel Injector Bar in the back cavity, cold with back cavity with ante-chamber is connected between the ante-chamber and the back cavity
But gas circular channel, has the cooling gas circular channel for connecting ante-chamber and cavity between the ante-chamber and the cavity.Preferably,
The cavity is located between the ante-chamber and the back cavity in the orientation of the ante-chamber and the back cavity.
Preferred embodiment of the invention, the upper surface of the outer surface of the calotte and the support plate, lower surface it
Between smoothly transit, the support plate trailing edge is using blocking design.
Preferred embodiment of the invention, the depth capacity of the cavity be the support plate maximum height 1/4 to
1/3, the maximum length of the cavity is 2 with the ratio of depth capacity：1, the front surface of the cavity perpendicular to front direction of flow,
The rear surface of the cavity is skewed surface inclined to the support plate trailing edge.
Preferred embodiment of the invention, the angular range that the skewed surface flows with front is more than or equal to 30 °
And less than or equal to 45 °.
Preferred embodiment of the invention, the central axis of the support plate trailing edge is higher than the central shaft of the calotte
Line.
Preferred embodiment of the invention, the connection ante-chamber is 1 with the number of the cooling gas circular channel of back cavity
Bar, the connection ante-chamber is 1 with the number of the cooling gas circular channel of cavity；Or, the connection ante-chamber is cold with back cavity
But gas circular channel is 2 parallel channels, and the connection ante-chamber is 2 parallel channels with the cooling gas circular channel of cavity.
Preferred embodiment of the invention, the quantity of the working connection Fuel Injector Bar is 2, in the rear in chamber up and down
Arrangement, each described working connection Fuel Injector Bar is respectively provided with 1 or 2 nozzle openings, and the nozzle opening of the working connection Fuel Injector Bar is just to institute
The nozzle opening on back cavity is stated, the nozzle opening on the back cavity is corresponded with the nozzle opening of the working connection Fuel Injector Bar, and number
Measure equal, the side that the nozzle opening on the back cavity flows with the oil spout direction of the nozzle opening of the working connection Fuel Injector Bar with front
To vertical.
Preferred embodiment of the invention, the downside of the cavity has multiple outlets, and Way out and gravity
Direction is consistent, and 1 or 2 nozzle openings are provided with the upside of the Fuel Injector Bar on duty, and oil spout direction is contrary with gravity direction.
Preferred embodiment of the invention, the connection ante-chamber and the cooling gas circular channel of back cavity and described connects
Ante-chamber is kept at an angle with the cooling gas circular channel of cavity with front direction of flow, and the connection ante-chamber and cavity
Cooling gas circular channel the cooling gas circular channel with diameter greater than connection ante-chamber and the back cavity diameter.
The invention has the beneficial effects as follows：
1) present invention improves the atomization effect of fuel oil on duty using various ways such as pressure atomization, pneumatic nebulization, collision atomizations
Really, reliable, stable igniting is realized by high-energy ignition sparking plug at cavity edge.
2) present invention is flowed using cooling air and front carries out pneumatic nebulization to the fuel oil of working connection Fuel Injector Bar injection, increases
Atomization, the evaporation effect of strong fuel oil；Burn in the recirculating zone inner tissue of support plate trailing edge, so as to realize in broad range efficiently, surely
The purpose of fixed burning.
3) flame stabilizer of the invention is integrated design with oil supply system, and runner is smooth, and flow resistance is little, subtracts
Amount of parts is lacked, it is possible to increase the overall performance of TBCC Asias burning ramjet combustion chamber.
4) compared with traditional flame stabilizer, flame of the present invention suitable for TBCC Asias burning ramjet combustion chamber
Stabilising arrangement, by reasonable Arrangement fuel feeding on duty and the fuel feeding position of working connection, and improves atomizing effect using various ways, carries
The high ignition performance of TBCC Asias burning ramjet combustion chamber, and taken into account the combustibility in broad range.
Description of the drawings
The generalized section of Fig. 1 TBCC Asias burning ramjet flame combustion chamber stabilising arrangement.
The dynamic schematic diagram of internal cooling air flow of Fig. 2 TBCC Asias burning ramjet flame combustion chamber stabilising arrangement.
Symbol description is as follows in figure：1 support plate, 2 calottes, 3 cavitys, 4 Fuel Injector Bars on duty, 5 ante-chambers, 6 back cavities, the spray of 7 working connections
Beam hanger, the outer surface of 8 calottes, the upper surface of 9 support plates, the lower surface of 10 support plates, 11 cavitys, 12 support plate trailing edges, in 13 calottes
The cooling gas circular channel of heart axis, the central axis of 14 support plate trailing edges, the outlet of 15 cavitys, 16 connection ante-chambers and back cavity, 17
The cooling gas circular channel of connection ante-chamber and cavity, the nozzle opening of 18 working connection Fuel Injector Bars, the nozzle opening on 19 back cavities, 20 fronts
To flow.
Specific embodiment
Below, by accompanying drawing 1,2 is combined describing the fire for TBCC Asias burning ramjet combustion chamber of the invention
The specific embodiment of flame stabilising arrangement.
Fig. 1 is the generalized section of the TBCC Asias burning ramjet flame combustion chamber stabilising arrangement of the present invention, is tied below
Close the flame stabilizer for TBCC Asias burning ramjet combustion chamber that Fig. 1 describes the present invention in detail.The present invention's is used for
The flame stabilizer of TBCC Asias burning ramjet combustion chamber includes support plate 1, calotte 2, Fuel Injector Bar on duty 4, and support plate 1 and cap
Cover 2 links together, and forms cavity 3, and Fuel Injector Bar on duty 4 is arranged in cavity 3, it is preferred that Fuel Injector Bar on duty 4 is located at cavity 3
Approximate centre position；Support plate 1 has upper surface 9 and lower surface 10, and lower surface 10 has cavity 11, and upper surface 9 does not have recessed
Chamber.
The monnolithic case of flame stabilizer is airfoil structure, or other suitable structures.Wherein calotte 2 is outer
Smoothly transit between upper surface 9, the lower surface 10 of surface 8 and support plate 1, linked together using such as mode such as welding.It is preferred that
, support plate trailing edge 12 may also be employed other designs, such as concave design certainly using design is blocked.
Support plate 1 has ante-chamber 5 and back cavity 6, and ante-chamber 5 is used to introduce cooling gas, and working connection Fuel Injector Bar 7 is provided with back cavity 6,
There is the cooling gas circular channel 16 for connecting ante-chamber and back cavity between ante-chamber 5 and back cavity 6, have between ante-chamber 5 and cavity 3 and connect
The cooling gas circular channel 17 of ante-chamber and cavity.In the vertical direction, the outlet for cooling down gas circular channel 17 is higher than oil spout on duty
Bar 4；Preferably, referring to accompanying drawing 1, cavity 11 is located between ante-chamber 5 and back cavity 6 in the orientation of ante-chamber 5 and back cavity 6.
Central axis 13 of the central axis 14 of plate trailing edge higher than calotte 2.The number of the cooling gas circular channel 16 of connection ante-chamber and back cavity
Mesh can be 1, and the number for connecting ante-chamber with the cooling gas circular channel 17 of cavity can be 1；Connection ante-chamber and back cavity
Cooling gas circular channel 16 can also be 2 parallel channels, and the cooling gas circular channel 17 for connecting ante-chamber with cavity can also be 2
Bar parallel channels (Fig. 1 is not shown).The cooling air that ante-chamber 5 is introduced is by connection ante-chamber and the cooling gas circular channel 17 of cavity
It is incorporated in cavity 3.The cooling air that ante-chamber 5 is introduced also is incorporated into by connection ante-chamber with the cooling gas circular channel 16 of back cavity
In back cavity 6.
The depth capacity of cavity 11 is the 1/4 to 1/3 of the maximum height of support plate 1, the maximum length and depth capacity of cavity 11
Ratio be 2:1 to 3:1, preferably 2:1.The front surface of cavity 11 flows 20 directions perpendicular to front, the rear surface of cavity 11 be to
The inclined skewed surface of support plate trailing edge 12.Skewed surface flows 20 angular range with front and is more than or equal to 30 ° and is less than or equal to
45°。
The quantity of working connection Fuel Injector Bar 7 is 2, is arranged above and below in back cavity 6, and each working connection Fuel Injector Bar 7 is respectively provided with 1
Or 2 nozzle openings 18 (Fig. 1 illustrate only the situation with 1 nozzle opening), the nozzle opening 18 of working connection Fuel Injector Bar 7 is just to back cavity
Nozzle opening 19 on 6, the nozzle opening 19 on back cavity 6 is corresponded with the nozzle opening 18 of working connection Fuel Injector Bar 7, and quantity is equal
(Fig. 1 shows the nozzle opening of the upside of back cavity 6 and the corresponding feelings of nozzle opening 18 of the working connection Fuel Injector Bar 7 positioned at the top of back cavity 6
Shape, and the corresponding situation of nozzle opening 18 of the nozzle opening of the downside of back cavity 6 and the working connection Fuel Injector Bar 7 for being located at the bottom of back cavity 6), after
It is vertical that nozzle opening 19 on chamber 6 flows 20 direction with the oil spout direction of the nozzle opening 18 of working connection Fuel Injector Bar 7 with front.Spray
The shape of oilhole 18 and nozzle opening 19 can be rectangle, circle etc..
To avoid occurring oil-collecting phenomenon inside cavity 3, the downside of cavity 3 has multiple outlets 15, such as 1,2, and 4
It is individual, 6,8,10,12,14 (Fig. 1 illustrate only 1), the shape for exporting 15 can be slot, circular port,
Or other suitable shapes.And the direction of outlet 15 is consistent with gravity direction, the upside of Fuel Injector Bar on duty 4 is provided with 1 or 2
Nozzle opening (Fig. 1 illustrate only 1), oil spout direction is contrary with gravity direction.
Connection ante-chamber and back cavity cool down gas circular channel 16 and to connect ante-chamber equal with the cooling gas circular channel 17 of cavity
Flow 20 directions with front to be kept at an angle, preferably 2 ° to 20 °.And the cooling gas circular channel 17 of connection ante-chamber and cavity
The cooling gas circular channel 16 with diameter greater than connection ante-chamber and back cavity diameter.
The cooling air introduced from ante-chamber 5 is entered behind the inside of support plate 1, and sub-fraction cooling air flows to back cavity 6, to support plate
1 is cooled down, meanwhile, the part cooling air carries out pneumatic nebulization to the fuel oil that working connection Fuel Injector Bar 7 sprays, by nozzle opening
During 19 are ejected into front to flow 20 primary air, under 20 horizontal pneumatic nebulization effect is flowed in front, further improve atomization
Effect, and stably burn in the recirculating zone that support plate trailing edge 12 is formed.Another most of cooling air is entered in cavity 3, right
The fuel oil of the injection of Fuel Injector Bar on duty 4 carries out pneumatic nebulization, while the cooling air pressure of design is higher, can be by after pneumatic nebulization
Fuel oil impact the inwall of calotte 2, carry out collision atomization again with inwall, by the wall temperature heated fuel oil of calotte 2, promote combustion
The evaporation of oil, finally, outlet 15 of the gas mixture of fuel particle, fuel vapor together with cooling down gas and being mingled with from cavity 3
Eject, 20 are flowed using front to its further atomization, increase the evaporation rate of fuel oil, gas mixture is drawn onto cavity by volume
In 11 low speed recirculating zone, at the edge of cavity 11, by high-energy ignition sparking plug reliable, stable igniting is realized.
Fig. 2 is that the internal cooling air flow of the flame stabilizer of the TBCC Asias burning ramjet combustion chamber of the present invention is moved
Schematic diagram.
An embodiment of the invention, TBCC Asia burning ramjet combustion chamber operational in little operating mode, only
The fuel feeding of Fuel Injector Bar on duty 4.Now, the cooling air for introducing from ante-chamber 5 passes through the cooling gas circular channel of connection ante-chamber and cavity
17 enter in cavity 3, and the fuel oil of Fuel Injector Bar on duty 4 is touched after pressure atomization with the big stock cooling air into cavity 3
Hit, shear action (similar to pneumatic nebulization), while design cooling air pressure it is higher, can be by the fuel oil after pneumatic nebulization
The inwall of calotte 2 is impacted, with inwall collision atomization is carried out again, by the wall temperature heated fuel oil of calotte, promote fuel particle
Evaporation, finally, fuel particle, fuel vapor with cooling gas be mingled with together with gas mixture spray from the outlet 15 of cavity 3
During 20 primary air is flowed in front of being mapped to, using front air-flow 20 to its further atomization, increase the evaporation rate of fuel oil, and utilize
Cavity oil suction gas mixtures of volume 11, the low speed recirculating zone that cavity 11 is produced provides advantage for igniting.Meanwhile, from ante-chamber 5
The cooling air of introducing flows to back cavity 6 by ante-chamber with the cooling gas circular channel 16 of back cavity, support plate 1 is cooled down, finally
Flow out back cavity 6 and enter main flow.The unburned completely fuel oil on duty in cavity 11, in the recirculating zone that support plate trailing edge 12 is produced after
Afterflame burns.
According to another implementation of the invention, TBCC Asias burning ramjet combustion chamber operational is worth in big operating mode
Class's Fuel Injector Bar 4 and working connection Fuel Injector Bar 7 are while fuel feeding.Now, compared with little operating mode, difference is that from the introducing of ante-chamber 5 is little
Part cooling air carries out pneumatic nebulization to the fuel oil that working connection Fuel Injector Bar 7 sprays, and is ejected into front to flow 20 after the two blending
Primary air in.Under the shearing, the collision effect that flow in front, further improve atomizing effect, and formed in support plate trailing edge 12
Recirculating zone in stably burn.
The preferred embodiment of the present invention is these are only, the scope of the claims of the present invention is not thereby limited, it is every using this
Equivalent structure or equivalent flow conversion that description of the invention and accompanying drawing content are made, or directly or indirectly it is used in other correlations
Technical field, is included within the scope of the present invention.
Claims (10)
1. a kind of flame stabilizer for TBCC Asias burning ramjet combustion chamber, including：
Support plate (1)；
Calotte (2)；
Fuel Injector Bar (4) on duty；
The support plate (1) links together with the calotte (2), forms cavity (3)；
The Fuel Injector Bar on duty (4) is arranged in the cavity (3)；
It is characterized in that：
, with upper surface (9) and lower surface (10), the lower surface (10) is with cavity (11), the upper table for the support plate (1)
Face (9) does not have cavity；
The support plate (1) with ante-chamber (5) and back cavity (6), the ante-chamber (5) positioned at the cavity (3) and the back cavity (6) it
Between, the ante-chamber (5) is provided with working connection Fuel Injector Bar (7) for introducing cooling gas in the back cavity (6), the ante-chamber (5) with
There is cooling gas circular channel (16) of connection ante-chamber and back cavity, the ante-chamber (5) and the cavity between the back cavity (6)
(3) there is cooling gas circular channel (17) of connection ante-chamber and cavity between.
2. flame stabilizer according to claim 1, it is characterised in that：
The cavity (11) be located in the orientation of the ante-chamber (5) and the back cavity (6) ante-chamber (5) and it is described after
Between chamber (6)；The Fuel Injector Bar on duty (4) is positioned at the approximate centre position of the cavity (3).
3. flame stabilizer according to claim 1 and 2, it is characterised in that：
The outer surface (8) of the calotte (2) smoothly transits with the upper surface (9) of the support plate (1), lower surface between (10), institute
State support plate trailing edge (12) employing and block design.
4. the flame stabilizer according to any one of claims 1 to 3, it is characterised in that：
The depth capacity of the cavity (11) is the 1/4 to 1/3 of the support plate (1) maximum height, the maximum of the cavity (11)
Length is 2 with the ratio of depth capacity：1, the front surface of the cavity (11) flows (20) direction, the cavity perpendicular to front
(11) rear surface is skewed surface inclined to the support plate trailing edge (12).
5. flame stabilizer according to claim 4, it is characterised in that：
The angular range that the skewed surface flows (20) with front is more than or equal to 30 ° and less than or equal to 45 °.
6. the flame stabilizer according to any one of claim 1 to 5, it is characterised in that：
Central axis (13) of the central axis (14) of the support plate trailing edge higher than the calotte (2).
7. the flame stabilizer according to any one of claim 1 to 6, it is characterised in that：
The connection ante-chamber is 1 with the number of cooling gas circular channel (16) of back cavity, and the connection ante-chamber is cold with cavity
But the number of gas circular channel (17) is 1；Or, the connection ante-chamber is 2 with cooling gas circular channel (16) of back cavity
Parallel channels, the connection ante-chamber is 2 parallel channels with cooling gas circular channel (17) of cavity.
8. the flame stabilizer according to any one of claim 1 to 7, it is characterised in that：
The quantity of the working connection Fuel Injector Bar (7) is 2, is arranged above and below in chamber (6) in the rear, each described working connection oil spout
Bar (7) is respectively provided with 1 or 2 nozzle openings (18), and the nozzle opening (18) of the working connection Fuel Injector Bar (7) is just to the back cavity (6)
On nozzle opening (19), the nozzle opening (18) of the nozzle opening (19) on the back cavity (6) and the working connection Fuel Injector Bar (7) is one by one
Correspondence, and quantity is equal, the nozzle opening (18) of the nozzle opening (19) on the back cavity (6) and the working connection Fuel Injector Bar (7)
To flow the direction of (20) with front vertical in oil spout direction.
9. the flame stabilizer according to any one of claim 1 to 8, it is characterised in that：
The downside of the cavity (3) has multiple outlets (15), and outlet (15) direction is consistent with gravity direction, described on duty
1 or 2 nozzle openings are provided with the upside of Fuel Injector Bar (4), oil spout direction is contrary with gravity direction.
10. the flame stabilizer according to any one of claim 1 to 9, it is characterised in that：
The connection ante-chamber is logical with the cooling gas circle of cavity with cooling gas circular channel (16) of back cavity and the ante-chamber that connects
(20) direction is flowed with front and is kept at an angle in road (17)；The cooling gas circular channel of the connection ante-chamber and cavity
(17) diameter of cooling gas circular channel (16) with diameter greater than the connection ante-chamber and back cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611209284.0A CN106642202B (en) | 2016-12-23 | 2016-12-23 | A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611209284.0A CN106642202B (en) | 2016-12-23 | 2016-12-23 | A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106642202A true CN106642202A (en) | 2017-05-10 |
| CN106642202B CN106642202B (en) | 2019-02-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611209284.0A Active CN106642202B (en) | 2016-12-23 | 2016-12-23 | A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109057993A (en) * | 2018-07-25 | 2018-12-21 | 湖南云顶智能科技有限公司 | A kind of plasma spray burner of belt electrode refrigerating function |
| CN115164233A (en) * | 2022-08-18 | 2022-10-11 | 中国航空发动机研究院 | Baffle assembly and stabilizer |
| CN115164232A (en) * | 2022-08-18 | 2022-10-11 | 中国航空发动机研究院 | Baffle, baffle subassembly and stabilizer |
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| US20060016192A1 (en) * | 2004-07-21 | 2006-01-26 | Snecma | Turbojet with protection means for a fuel injection device, an injection device and a protective plate for the turbojet |
| CN101435586A (en) * | 2007-11-15 | 2009-05-20 | 周建兴 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
| CN102966974A (en) * | 2012-12-18 | 2013-03-13 | 中国人民解放军国防科学技术大学 | Supersonic combustor wall surface concave cavity structure and engine combustor comprising same |
| CN103499106A (en) * | 2013-09-11 | 2014-01-08 | 中国科学院力学研究所 | Method for expanding stability limit of supersonic combustion flames |
| CN104373964A (en) * | 2014-10-20 | 2015-02-25 | 北京航空航天大学 | Cavity supporting plate flame stabilizer with built-in oil rod |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060016192A1 (en) * | 2004-07-21 | 2006-01-26 | Snecma | Turbojet with protection means for a fuel injection device, an injection device and a protective plate for the turbojet |
| CN101435586A (en) * | 2007-11-15 | 2009-05-20 | 周建兴 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
| CN102966974A (en) * | 2012-12-18 | 2013-03-13 | 中国人民解放军国防科学技术大学 | Supersonic combustor wall surface concave cavity structure and engine combustor comprising same |
| CN103499106A (en) * | 2013-09-11 | 2014-01-08 | 中国科学院力学研究所 | Method for expanding stability limit of supersonic combustion flames |
| CN104373964A (en) * | 2014-10-20 | 2015-02-25 | 北京航空航天大学 | Cavity supporting plate flame stabilizer with built-in oil rod |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109057993A (en) * | 2018-07-25 | 2018-12-21 | 湖南云顶智能科技有限公司 | A kind of plasma spray burner of belt electrode refrigerating function |
| CN115164233A (en) * | 2022-08-18 | 2022-10-11 | 中国航空发动机研究院 | Baffle assembly and stabilizer |
| CN115164232A (en) * | 2022-08-18 | 2022-10-11 | 中国航空发动机研究院 | Baffle, baffle subassembly and stabilizer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106642202B (en) | 2019-02-12 |
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