CN106642202B - A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber - Google Patents
A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber Download PDFInfo
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- CN106642202B CN106642202B CN201611209284.0A CN201611209284A CN106642202B CN 106642202 B CN106642202 B CN 106642202B CN 201611209284 A CN201611209284 A CN 201611209284A CN 106642202 B CN106642202 B CN 106642202B
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- cooling air
- supporting plate
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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 present invention provides a kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber, including supporting plate, calotte, Fuel Injector Bar on duty, supporting plate links together with calotte, form cavity, Fuel Injector Bar on duty is set in cavity, supporting plate has upper and lower surfaces, lower surface has cavity, upper surface does not have cavity, supporting plate has ante-chamber and back cavity, ante-chamber is between cavity and back cavity, ante-chamber is for introducing cooling air, working connection Fuel Injector Bar is provided in back cavity, there is the cooling air circular channel for being connected to ante-chamber and back cavity between ante-chamber and back cavity, there is the cooling air circular channel for being connected to ante-chamber and cavity between ante-chamber and cavity.The present invention passes through the fuel feeding position of reasonable Arrangement fuel feeding on duty and working connection, and improve atomizing effect using various ways such as pressure atomization, pneumatic nebulization, collision atomizations, improve the ignition performance of the Asia TBCC burning ramjet combustion chamber, and the combustibility in broad range has been taken into account, improve the overall performance of the Asia TBCC burning ramjet combustion chamber.
Description
Technical field
The present invention relates to the flame stabilizers of engine chamber.Specifically, the present invention is more particularly directed to be used for (the whirlpool TBCC
Take turns base combination circulation, Turbine-based combined cycle) flame stabilizer of sub- burning ramjet combustion chamber.
Background technique
The work starting point of the Asia TBCC burning ramjet is located at Mach number 2.5, and corresponding combustion chamber incoming flow total temperature is about
486K, pressure are near the mark atmospheric pressure, and for gasflow mach number but up to 0.28, this mentions the reliable ignition and flame stabilization of combustion chamber
Huge challenge is gone out.Meanwhile the Asia TBCC burning ramjet also needs in the broad range that range of Mach numbers is 2.5~4 in fact
Now stable, efficient burning, this is another problem that combustion chamber is faced.
The bluff body flameholder of traditional bluff has been difficult to the demand of the competent Asia TBCC burning ramjet combustion chamber.
By taking V-groove flameholder as an example, the stabilizer is at 250 DEG C of temperature of incoming flow, speed of incoming flow coefficient 0.2, when pressure 0.11MPa,
It is just difficult to stablize burning when oil-gas ratio 0.32, it is clear that it is even more impossible to adapt to wide working range.
Cavity supporting plate flameholder is a kind of current flame stabilization scheme received significant attention.
Patent document CN102200292A proposes that a kind of flame stabilization for gas turbine engine augmentor fills
It sets, i.e. the supporting plate flameholder with cavity, it is prominent by curved cavity on supporting plate and trailing edge on the basis of aerofoil profile supporting plate
Expand structure and form low speed recirculating zone, realizes steady flame purpose.
Patent document CN104373964A proposes a kind of injection system and cavity supporting plate flame stabilizer integration is set
Fuel Injector Bar is built in cavity supporting plate internal cavities by the scheme of meter, reduces the amount of parts of after-burner, reduces flowing
Loss, improves the overall performance of after-burner.Meanwhile built-in Fuel Injector Bar using the cooling air-flow flowed through in cavity supporting plate into
Row pneumatic nebulization further increases 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 relatively high, can arrive
1000K, fuel oil can achieve preferable atomization, evaporation effect, after air blending uniformly, may be implemented aviation kerosine from
Combustion.But for the burning ramjet combustion chamber of the Asia TBCC, 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 reinforce atomization, the evaporation process of fuel oil in several ways, it is successfully general to guarantee to light a fire
Rate.Combustion method must be also rationally designed simultaneously, guarantee that combustion chamber there can be wide efficient stable working range.
Summary of the invention
Therefore, the purpose of the present invention is to propose a kind of flame stabilization dress for the Asia TBCC burning ramjet combustion chamber
It sets, meets the reliable ignition of the Asia TBCC burning ramjet combustion chamber, while guaranteeing the stabilization in broad range, efficiently combustion
It burns.
The invention proposes a kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber, the flame stabilizations
Device includes: supporting plate, calotte, Fuel Injector Bar on duty, and the supporting plate links together with the calotte, forms cavity, described on duty
Fuel Injector Bar is arranged in the cavity, and the supporting plate has upper and lower surfaces, 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.
According to the preferred embodiment of the present invention, the supporting plate has ante-chamber and back cavity, and the ante-chamber is for introducing cooling
Gas is provided with working connection Fuel Injector Bar in the back cavity, has between the ante-chamber and the back cavity and is connected to the cold of ante-chamber and back cavity
But gas circular channel has the cooling air circular channel for being connected to ante-chamber and cavity between the ante-chamber and the cavity.Preferably,
The cavity is in the orientation of the ante-chamber and the back cavity between the ante-chamber and the back cavity.
According to the preferred embodiment of the present invention, the upper surface, lower surface of the outer surface of the calotte and the supporting plate it
Between smoothly transit, the supporting plate trailing edge is using truncation design.
According to the preferred embodiment of the present invention, the depth capacity of the cavity be the supporting plate maximum height 1/4 to
1/3, the ratio between maximum length and depth capacity of the cavity are 2:1, the front surface of the cavity perpendicular to front direction of flow,
The rear surface of the cavity is to the inclined skewed surface of supporting plate trailing edge.
According to the preferred embodiment of the present invention, the angular range of the skewed surface and front incoming flow is more than or equal to 30 °
And it is less than or equal to 45 °.
According to the preferred embodiment of the present invention, the central axis of the supporting plate trailing edge is higher than the central axis of the calotte
Line.
According to the preferred embodiment of the present invention, the number of the cooling air circular channel of the connection ante-chamber and back cavity is 1
The number of the cooling air circular channel of item, the connection ante-chamber and cavity is 1；Alternatively, it is described connection ante-chamber and back cavity it is cold
But gas circular channel is 2 parallel channels, and the cooling air circular channel of the connection ante-chamber and cavity is 2 parallel channels.
According to the preferred embodiment of the present invention, the quantity of the working connection Fuel Injector Bar is 2, in the back cavity up and down
Arrangement, each working connection Fuel Injector Bar all have 1 or 2 nozzle openings, the nozzle opening face institute of the working connection Fuel Injector Bar
The nozzle opening on back cavity is stated, the nozzle opening of the nozzle opening on the back cavity and the working connection Fuel Injector Bar corresponds, and number
Measure equal, side of the oil spout direction of the nozzle opening of nozzle opening and the working connection Fuel Injector Bar on the back cavity with front incoming flow
To vertical.
According to the preferred embodiment of the present invention, the downside of the cavity has multiple outlets, and export direction and gravity
Direction is consistent, and 1 is provided on the upside of the Fuel Injector Bar on duty or 2 nozzle openings, oil spout direction are opposite with gravity direction.
According to the preferred embodiment of the present invention, it the connection ante-chamber and the cooling air circular channel of back cavity and described is connected to
The cooling air circular channel of ante-chamber and cavity is kept at an angle with front direction of flow, and the connection ante-chamber and cavity
Cooling air circular channel diameter be greater than it is described connection ante-chamber and back cavity cooling air circular channel diameter.
The beneficial effects of the present invention are:
1) present invention improves the atomization effect of fuel oil on duty using various ways such as pressure atomization, pneumatic nebulization, collision atomizations
Fruit realizes reliable, stable igniting by high-energy ignition sparking plug at cavity edge.
2) present invention carries out pneumatic nebulization to the fuel oil that working connection Fuel Injector Bar sprays using cooling air and front incoming flow, increases
The atomization of strong fuel oil, evaporation effect；It burns in the recirculating zone inner tissue of supporting plate trailing edge, to realize in broad range efficiently, surely
Surely the purpose burnt.
3) flame stabilizer of the invention and oil supply system are integrated design schemes, and runner is smooth, and flow resistance is small, subtracts
Lack amount of parts, can be improved the overall performance of the Asia TBCC burning ramjet combustion chamber.
4) compared with traditional flame stabilizer, the present invention is suitable for the flame of the Asia TBCC burning ramjet combustion chamber
Stabilising arrangement improves atomizing effect by the fuel feeding position of reasonable Arrangement fuel feeding on duty and working connection, and using various ways, mentions
The high ignition performance of the Asia TBCC burning ramjet combustion chamber, and taken into account the combustibility in broad range.
Detailed description of the invention
The diagrammatic cross-section of the Asia Fig. 1 TBCC burning ramjet flame combustion chamber stabilising arrangement.
The internal cooling air flow of the Asia Fig. 2 TBCC burning ramjet flame combustion chamber stabilising arrangement moves schematic diagram.
Symbol description is as follows in figure: 1 supporting 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 supporting plates, the lower surface of 10 supporting plates, 11 cavitys, 12 supporting plate trailing edges, in 13 calottes
Mandrel line, the central axis of 14 supporting plate trailing edges, the outlet of 15 cavitys, the cooling air circular channel of 16 connection ante-chambers and back cavity, 17
It is connected to the cooling air circular channel of ante-chamber and cavity, the nozzle opening of 18 working connection Fuel Injector Bars, the nozzle opening on 19 back cavities, 20 fronts
Incoming flow.
Specific embodiment
In the following, by the fire according to the present invention for being used for the Asia TBCC burning ramjet combustion chamber is described in conjunction with attached drawing 1,2
The specific embodiment of flame stabilising arrangement.
Fig. 1 is the diagrammatic cross-section of the Asia TBCC burning ramjet flame combustion chamber stabilising arrangement of the invention, is tied below
Close the flame stabilizer that Fig. 1 detailed description of the present invention is used for the Asia TBCC burning ramjet combustion chamber.Of the invention is used for
The flame stabilizer of the Asia TBCC burning ramjet combustion chamber includes supporting plate 1, calotte 2, Fuel Injector Bar on duty 4, and supporting plate 1 and cap
Cover 2 links together, and forms cavity 3, and Fuel Injector Bar 4 on duty is set in cavity 3, it is preferred that Fuel Injector Bar 4 on duty is located at cavity 3
Approximate centre position；Supporting 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, is also possible to other suitable structures.Wherein calotte 2 is outer
It smoothly transits between surface 8 and the upper surface of supporting plate 19, lower surface 10, is linked together using such as modes such as welding.It is preferred that
, other designs, such as concave design can also be used using truncation design in supporting plate trailing edge 12 certainly.
Supporting plate 1 has ante-chamber 5 and back cavity 6, and ante-chamber 5 is used to introduce cooling air, and working connection Fuel Injector Bar 7 is provided in back cavity 6,
There is the cooling air circular channel 16 for being connected to ante-chamber and back cavity between ante-chamber 5 and back cavity 6, have between ante-chamber 5 and cavity 3 and be connected to
The cooling air circular channel 17 of ante-chamber and cavity.In the vertical direction, the outlet of cooling air circular channel 17 is higher than oil spout on duty
Bar 4；Preferably, referring to attached drawing 1, cavity 11 is in the orientation of ante-chamber 5 and back cavity 6 between ante-chamber 5 and back cavity 6.Branch
The central axis 14 of plate trailing edge is higher than the central axis 13 of calotte 2.It is connected to the number of the cooling air circular channel 16 of ante-chamber and back cavity
Mesh can be 1, and the number for being connected to the cooling air circular channel 17 of ante-chamber and cavity can be 1；It is connected to ante-chamber and back cavity
Cooling air circular channel 16 is also possible to 2 parallel channels, and the cooling air circular channel 17 for being connected to ante-chamber and cavity is also possible to 2
Parallel channels (Fig. 1 is not shown).The cooling air circular channel 17 that the cooling air that ante-chamber 5 introduces passes through connection ante-chamber and cavity
It is introduced into cavity 3.The cooling air that ante-chamber 5 introduces also passes through connection ante-chamber and the cooling air circular channel 16 of back cavity is introduced into
In back cavity 6.
The depth capacity of cavity 11 is the 1/4 to 1/3 of 1 maximum height of supporting plate, the maximum length and depth capacity of cavity 11
The ratio between be 2:1 to 3:1, preferably 2:1.The front surface of cavity 11 perpendicular to 20 direction of front incoming flow, the rear surface of cavity 11 be to
The inclined skewed surface of supporting plate trailing edge 12.The angular range of skewed surface and front incoming flow 20 is more than or equal to 30 ° and to be 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, each working connection Fuel Injector Bar 7 all has 1
Or 2 nozzle openings 18 (Fig. 1 illustrates only the situation with 1 nozzle opening), the 18 face back cavity of nozzle opening of working connection Fuel Injector Bar 7
The nozzle opening 18 of nozzle opening 19 on 6, nozzle opening 19 and working connection Fuel Injector Bar 7 on back cavity 6 corresponds, and quantity is equal
(Fig. 1 shows the nozzle opening feelings corresponding with the nozzle opening 18 of working connection Fuel Injector Bar 7 on 6 top of back cavity is located at of 6 upside of back cavity
The nozzle opening situation corresponding with the nozzle opening 18 of working connection Fuel Injector Bar 7 of 6 lower part of back cavity is located at of 6 downside of shape and back cavity), after
Nozzle opening 19 and the oil spout direction of the nozzle opening 18 of working connection Fuel Injector Bar 7 on chamber 6 is vertical with the direction of front incoming flow 20.Spray
The shape of oilhole 18 and nozzle opening 19 can be rectangle, circle etc..
To avoid occurring inside cavity 3 oil-collecting phenomenon, the downside of cavity 3 has multiple outlets 15, such as 1, and 2,4
A, 6,8,10,12,14 (Fig. 1 illustrates only 1), the shape for exporting 15 can be slot, round hole,
Or other suitable shapes.And the direction of outlet 15 is consistent with gravity direction, the upside of Fuel Injector Bar 4 on duty is provided with 1 or 2
Nozzle opening (Fig. 1 illustrates only 1), oil spout direction is opposite with gravity direction.
Connection ante-chamber and the cooling air circular channel 16 of back cavity and it is connected to the cooling air circular channel 17 of ante-chamber and cavity
It is kept at an angle with 20 direction of front incoming flow, preferably 2 ° to 20 °.And it is connected to the cooling air circular channel 17 of ante-chamber and cavity
Diameter be greater than connection ante-chamber and back cavity cooling air circular channel 16 diameter.
After the cooling air introduced from ante-chamber 5 enters 1 inside of supporting plate, sub-fraction cooling air stream is to back cavity 6, to supporting plate
1 is cooled down, meanwhile, which carries out pneumatic nebulization to the fuel oil that working connection Fuel Injector Bar 7 sprays, and passes through nozzle opening
19 are ejected into the primary air of front incoming flow 20, under the lateral pneumatic nebulization effect of front incoming flow 20, further improve atomization
Effect, and stablize burning in the recirculating zone that supporting plate trailing edge 12 is formed.Another major part cooling air enters in cavity 3, right
The fuel oil that Fuel Injector Bar 4 on duty sprays carries out pneumatic nebulization, while the cooling air pressure designed is higher, can will be after pneumatic nebulization
Fuel oil impact the inner wall of calotte 2, carry out collision atomization again with inner wall, by the wall temperature heated fuel oil of calotte 2, promote combustion
The evaporation of oil, finally, fuel particle, fuel vapor be mingled with cooling air together with gas mixture from the outlet of cavity 3 15
It ejects, it is further atomized using front incoming flow 20, increases the evaporation rate of fuel oil, gas mixture, which is rolled up, is drawn onto cavity
In 11 low speed recirculating zone, at 11 edge of cavity, reliable, stable igniting is realized by high-energy ignition sparking plug.
Fig. 2 is that the internal cooling air flow of the flame stabilizer of the Asia TBCC burning ramjet combustion chamber of the invention is dynamic
Schematic diagram.
According to embodiment of the present invention, the Asia TBCC burning ramjet combustion chamber operational is in small operating condition, only
4 fuel feeding of Fuel Injector Bar on duty.At this point, the cooling air circular channel that the cooling air introduced from ante-chamber 5 passes through connection ante-chamber and cavity
17 enter in cavity 3, and 4 fuel oil of Fuel Injector Bar on duty is touched after pressure atomization with the big stock cooling air for entering cavity 3
It hits, shear action (being similar to pneumatic nebulization), while the cooling air pressure designed is higher, it can be by the fuel oil after pneumatic nebulization
The inner wall for impacting calotte 2 carries out collision atomization with inner wall again, by the wall temperature heated fuel oil of calotte, promotes fuel particle
Evaporation, finally, fuel particle, fuel vapor be mingled with cooling air together with gas mixture from the outlet of cavity 3 15 spray
It is mapped in the primary air of front incoming flow 20, it is further atomized using front air-flow 20, increases the evaporation rate of fuel oil, and utilize
Cavity oil suction gas mixtures of volume 11, the low speed recirculating zone that cavity 11 generates provide advantage for igniting.Meanwhile from ante-chamber 5
The cooling air of introducing flows to back cavity 6 by the cooling air circular channel 16 of ante-chamber and back cavity, cools down to supporting plate 1, finally
It flows out back cavity 6 and enters mainstream.The unburned complete fuel oil on duty in cavity 11, in the recirculating zone that supporting plate trailing edge 12 generates after
Afterflame is burnt.
According to another implementation of the invention, the Asia TBCC burning ramjet combustion chamber operational is in big operating condition, value
Class's Fuel Injector Bar 4 and working connection Fuel Injector Bar 7 while fuel feeding.At this point, difference is compared with small operating condition, one introduced from ante-chamber 5 is small
Part cooling air carries out pneumatic nebulization to the fuel oil that working connection Fuel Injector Bar 7 sprays, and front incoming flow 20 is ejected into after the two blending
Primary air in.Under the shearing of front incoming flow, collision effect, further improve atomizing effect, and in the formation of supporting plate trailing edge 12
Recirculating zone in stablize burning.
The above is only the preferred embodiment of the present invention, are not intended to limit the scope of the invention, all to utilize this
Equivalent structure or equivalent flow shift made by description of the invention and accompanying drawing content, it is relevant to be applied directly or indirectly in other
Technical field is included within the scope of the present invention.
Claims (8)
1. a kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber, comprising:
Supporting plate (1)；
Calotte (2)；
Fuel Injector Bar (4) on duty；
The supporting plate (1) links together with the calotte (2), is formed cavity (3)；
The Fuel Injector Bar on duty (4) is set in the cavity (3)；
It is characterized by:
The supporting plate (1) has upper surface (9) and lower surface (10), and the lower surface (10) has cavity (11), the upper table
Face (9) does not have cavity；
The supporting plate (1) has ante-chamber (5) and a back cavity (6), the ante-chamber (5) be located 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 air in the back cavity (6), the ante-chamber (5) with
There is the cooling air 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 the cooling air circular channel (17) of connection ante-chamber and cavity between；
The cavity (11) in the orientation of the ante-chamber (5) and the back cavity (6) be located at the ante-chamber (5) and it is described after
Between chamber (6)；The Fuel Injector Bar on duty (4) is located at the approximate centre position of the cavity (3)；
The connection ante-chamber and the cooling air circular channel (16) of back cavity and the cooling air circle for being connected to ante-chamber and cavity are logical
Road (17) is kept at an angle with front incoming flow (20) direction；The cooling air circular channel of the connection ante-chamber and cavity
(17) diameter is greater than the diameter of the cooling air circular channel (16) of the connection ante-chamber and back cavity.
2. flame stabilizer according to claim 1, it is characterised in that:
The outer surface (8) of the calotte (2) and upper surface (9), the lower surface of the supporting plate (1) smoothly transit between (10), institute
Supporting plate trailing edge (12) are stated using truncation design.
3. flame stabilizer according to claim 1 or 2, it is characterised in that:
The depth capacity of the cavity (11) is the 1/4 to 1/3 of the supporting plate (1) maximum height, the maximum of the cavity (11)
The ratio between length and depth capacity are 2:1, and the front surface of the cavity (11) is perpendicular to front incoming flow (20) direction, the cavity
(11) rear surface is to the inclined skewed surface of the supporting plate trailing edge (12).
4. flame stabilizer according to claim 3, it is characterised in that:
The angular range of the skewed surface and front incoming flow (20) is more than or equal to 30 ° and to be less than or equal to 45 °.
5. flame stabilizer according to claim 1, it is characterised in that:
The central axis (14) of the supporting plate trailing edge is higher than the central axis (13) of the calotte (2).
6. flame stabilizer according to claim 1, it is characterised in that:
It is described connection ante-chamber and back cavity cooling air circular channel (16) number be 1, it is described connection ante-chamber and cavity it is cold
But the number of gas circular channel (17) is 1；Alternatively, the cooling air circular channel (16) of the connection ante-chamber and back cavity is 2
The cooling air circular channel (17) of parallel channels, the connection ante-chamber and cavity is 2 parallel channels.
7. according to the described in any item flame stabilizers of claim 4 to 6, it is characterised in that:
The quantity of the working connection Fuel Injector Bar (7) is 2, is arranged above and below in the back cavity (6), each working connection oil spout
Bar (7) all has 1 or 2 nozzle openings (18), back cavity (6) described in nozzle opening (18) face of the working connection Fuel Injector Bar (7)
On nozzle opening (19), the nozzle opening (18) of nozzle opening (19) and the working connection Fuel Injector Bar (7) on the back cavity (6) is one by one
It is corresponding, 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)
Oil spout direction it is vertical with the direction of front incoming flow (20).
8. flame stabilizer according to claim 1, 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
It is provided with 1 on the upside of Fuel Injector Bar (4) or 2 nozzle openings, oil spout direction are opposite with gravity direction.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201611209284.0A 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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| CN201611209284.0A 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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| CN106642202B true CN106642202B (en) | 2019-02-12 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109057993B (en) * | 2018-07-25 | 2019-12-31 | 湖南云顶智能科技有限公司 | Plasma spray combustion device with electrode cooling function |
| CN115164233B (en) * | 2022-08-18 | 2023-04-25 | 中国航空发动机研究院 | Baffle assembly and stabilizer |
| CN115164232B (en) * | 2022-08-18 | 2023-04-25 | 中国航空发动机研究院 | Baffle, baffle assembly and stabilizer |
| CN115751380B (en) * | 2022-11-24 | 2025-01-28 | 保定市玄云涡喷动力设备研发有限公司 | A micro atomizing nozzle |
| CN115899768B (en) * | 2022-12-29 | 2025-02-18 | 中国航发沈阳发动机研究所 | Large-size stamping combustion chamber |
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|---|---|---|---|---|
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2873411B1 (en) * | 2004-07-21 | 2009-08-21 | Snecma Moteurs Sa | TURBOREACTOR WITH PROTECTIVE MEANS FOR A FUEL INJECTION DEVICE, INJECTION DEVICE AND PROTECTIVE COVER FOR THE TURBOJET ENGINE |
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2016
- 2016-12-23 CN CN201611209284.0A patent/CN106642202B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| CN106642202A (en) | 2017-05-10 |
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