CN109631085A - Sweepback circular arc type pneumatic nebulization vaporation-type stabilizer - Google Patents
Sweepback circular arc type pneumatic nebulization vaporation-type stabilizer Download PDFInfo
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- CN109631085A CN109631085A CN201811528926.2A CN201811528926A CN109631085A CN 109631085 A CN109631085 A CN 109631085A CN 201811528926 A CN201811528926 A CN 201811528926A CN 109631085 A CN109631085 A CN 109631085A
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- Prior art keywords
- ring
- circumferential
- face
- evaporation tube
- feed pump
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- 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
Abstract
The present invention relates to a kind of scramjet combustors, provide a kind of sweepback circular arc type pneumatic nebulization vaporation-type stabilizer, solve that existing machinery flameholder aerodynamic loss is big, steady flame narrow range, welding procedure is complicated, the problem of causing functional reliability low, being unable to satisfy under High Mach number efficiently steady flame requirement.The stabilizer includes circumferential evaporation tube, and circumferential evaporation tube direction of flow is equipped with annular turbulent, and the rear side tube wall of circumferential evaporation tube is equipped with a plurality of circumferentially spaced evaporation apertures of an at least row；Annular turbulent includes preceding ring-like body, and the ring-like face in the ring-like face in inside and outside being connected with preceding ring-like body；The front end of preceding ring-like body is provided with multiple bleed ports communicated with circumferential evaporation tube, and rear end is connected with circumferential evaporation tube；Preceding ring-like body with the fuel feed pump that communicates with external fuel oil is equipped in the type face of the ring-like face in outside and inside ring-like face circumferential direction junction, the fuel feed pump at bleed ports is equipped with atomizer, and injection direction intersects with direction of flow.
Description
Technical field
The present invention relates to a kind of scramjet combustors, more particularly to a kind of sweepback circular arc type pneumatic nebulization vaporation-type
Stabilizer.
Background technique
The combustion chamber of punching engine is the place that fuel chemical energy is converted to kinetic energy, how to realize punching engine in length
Wide scope, efficient stable burning under the conditions of voyage, high-altitude, high speed etc. are the key that Combustion chamber designs.In high speed inlet flow conditions
Under, in order to guarantee that the flame stabilization in scramjet combustor burns, needs to establish a local low speed in the combustion chamber and return
Area is flowed, flame propagation velocity is created and is equal to speed of incoming flow, fuel residence time greater than conditions such as ignition delay times, remain entire
The lasting presence and propagation of flame combustion chamber.
A kind of working range of existing sub- burning ramjet is very wide (Ma2~Ma5), far more than current more mature type
Number sub- burning ramjet working range, the efficiently steady flame problem of wide scope is than more prominent.
At present in punching engine common mechanical steady flame structure (such as vaporation-type stabilizer) although can satisfy lower horse
Efficient steady flame requirement of the conspicuous number (such as Ma4) below and in relatively narrow range of Mach numbers (Ma2~Ma4), but its obstruction is bigger, more
In High Mach number (such as Ma4~Ma5) and wider range of Mach numbers (Ma2~Ma5), it will generate biggish aerodynamic loss, reduce
Engine performance.
In addition, existing vaporation-type stabilizer is welding structure, at fillet weld or butt weld position up to hundred, outside oil pipe
It sets, weld seam is easy cracking in the course of work.
Summary of the invention
Existing machinery flameholder aerodynamic loss is big, steady flame narrow range in order to solve, and welding procedure is complicated, leads to work
The problem of reliability is low, is unable to satisfy under High Mach number efficiently steady flame requirement, the present invention provides a kind of sweepback circular arc type is pneumatic
Atomization and vaporization type stabilizer.The steady flame effect for enhancing existing vaporation-type stabilizer, by multichannel injection tubing, nozzle and stabilizer
Become one, realize the integration of oil spout, pneumatic nebulization, blending and steady flame, can satisfy the efficient steady of wide scope operating condition
Flame requirement.
To achieve the above object, present invention provide the technical scheme that
A kind of sweepback circular arc type pneumatic nebulization vaporation-type stabilizer, is characterized in that the circumferential direction including being arranged concentrically
Evaporation tube and annular turbulent；The direction of flow of the circumferential direction evaporation tube is equipped with the annular turbulent, circumferential evaporation tube
Rear side tube wall is equipped with a plurality of circumferentially spaced evaporation apertures of an at least row；The annular turbulent includes preceding ring-like body, interior side ring
The ring-like face in type face and outside；The front end of the preceding ring-like body is provided with multiple bleed ports communicated with circumferential evaporation tube, forms overcurrent
Channel, its rear end are connected with circumferential evaporation tube；It is equipped between the preceding ring-like body and circumferential evaporation tube and to be connected with preceding ring-like body
The ring-like face in the outside and the ring-like face in inside, and the angle of the ring-like face in the ring-like face in outside and inside and preceding ring-like body is obtuse angle；
The outer fuel feed pump that communicates with external fuel oil is equipped in the type face of the preceding ring-like body and outside ring-like face circumferential direction junction, positioned at drawing
Outer fuel feed pump at port is equipped with outer atomizer, and injection direction intersects with direction of flow；The preceding ring-like body and interior side ring
It is equipped with the interior fuel feed pump communicated with external fuel oil in the type face of type face circumferential direction junction, is set on the interior fuel feed pump at bleed ports
There is interior atomizer, injection direction intersects with the direction of flow of bleed ports.
Further, the circumferential evaporation tube is equipped with multiple radial evaporation tubes communicated vertical with circumferential evaporation tube；Institute
The closed at both ends of radial evaporation tube is stated, the radial turbulent being connected with annular turbulent, radial evaporation tube are equipped in direction of flow
Rear side tube wall be equipped with the multiple radially distributed evaporation apertures of an at least row；The radial direction turbulent includes two and extends outwardly
Side type face forms chamber between two sides type face and radial evaporation tube.
Further, the ring-like face in the ring-like face in the outside and inside is the cambered surface for being convex to circumferential evaporation tube, and and front ring
Type body is rounding off；Side type face is the cambered surface for being convex to radial evaporation tube, and whole sweepback.
Further, the quantity of the radial evaporation tube is 3~9.
Further, the evaporation apertures on the rear side tube wall of the circumferential evaporation tube and radial evaporation tube are uniformly distributed two rows；
The diameter of evaporation apertures is 1~5mm.
Further, the outer fuel feed pump and interior fuel feed pump are ring pipe, and quantity is at least one；Outer fuel feed pump draws
Outer atomizer there are two setting at port, the injection direction of outer atomizer and the direction of flow of bleed ports are vertical；Interior fuel feed pump draws
Interior atomizer there are two setting at port, the injection direction of interior atomizer and the direction of flow of bleed ports are vertical.
Further, the outer fuel feed pump and interior fuel feed pump are one, set at the bleed ports of each fuel feed pump there are two
Atomizer.
Further, the atomizer hits for smooth-bore tip, swirl atomizer or certainly nozzle.
Further, the size of the flow channels is gradually increased from bleed ports to circumferential evaporation tube direction, and with circumferential direction
Evaporation tube junction rounding off avoids forming sudden expansion structure at circumferential evaporation tube.
Further, the shape of bleed ports is round, oval, kidney-shaped or polygon, and the quantity of bleed ports is diameter
To 1~3 times of turbulent, it is evenly arranged on annular turbulent.
Further, the section of radial evaporation tube be round, ellipse, kidney-shaped or polygon.
Compared with prior art, the invention has the advantages that
(1) leading portion of circumferential evaporation tube is equipped with annular turbulent, and the rear end of annular turbulent is the ring-like face in inside and outside
Ring-like face, whole sweepback can produce bigger recirculating zone in the identical situation of blockage ratio, be conducive to sharp in high-speed flow
Biggish steady flame effect is realized with lesser aerodynamic loss；
Oil supply pipe, flow channels, nozzle are arranged in annular turbulent, and simple and compact for structure, fuel feeding is reliable and stable, benefit
The pneumatic nebulization to fuel oil is realized with the shearing of incoming flow, is enhanced fuel-oil atmozation, air blending, is improved efficiency of combustion.
(2) the radial evaporation tube communicated vertical with circumferential evaporation tube being arranged, improves fuel efficiency efficiency, is conducive in high speed
Biggish steady flame effect is realized using lesser aerodynamic loss in air-flow.
(3) the side type face of the whole sweepback on rear side of the ring-like face in outside, the ring-like face in inside and radial turbulent is cambered surface,
The deflection for being conducive to air-flow forms biggish recirculating zone.
(4) at bleed ports, fuel oil is sprayed into arrangement of nozzles with vertical angle, and the gas to fuel oil is realized using the shearing of bleed
Dynamic atomization, fuel distribution is uniform, and combustion chamber operational is influenced small by air-flow and fuel oil switching.
(5) aerodynamic loss of stabilizer of the present invention is small, simple process, functional reliability are high.
Detailed description of the invention
Fig. 1 is the main view of stabilizer of the present invention；
Fig. 2 is the rearview of stabilizer of the present invention；
Fig. 3 is the left view of stabilizer of the present invention；
Fig. 4 is sectional view along A-A in Fig. 1；
Fig. 5 is the evaporation apertures distribution schematic diagram in stabilizer of the present invention on circumferential evaporation tube and radial evaporation tube；
Fig. 6 is the Complex Flow Status schematic diagram that incoming flow forms three-dimensional space in stabilizer of the present invention, wherein a is circumferential steams
Hair pipe and the circumferential evaporation tube place of communicating in terms of direction of flow, b is circumferential evaporation tube and circumferential direction evaporation tube communicate place from incoming flow side
It is seen to vertical direction；
Fig. 7 is evaporation tube rear of the present invention recirculating zone kerosene track schematic diagram, wherein a is that circumferential evaporation tube and circumferential direction steam
The pipe place of communicating is sent out from in terms of direction of flow vertical direction, b is that the inverse direction of flow of circumferential evaporation tube and the circumferential evaporation tube place of communicating is seen.
Wherein, appended drawing reference is as follows:
1- circumferential direction evaporation tube, 11- evaporation apertures, 2- annular turbulent, 20- bleed ports, ring-like body before 21- are ring-like on the inside of 22-
Face, ring-like face on the outside of 23-, the outer fuel feed pump of 3-, the outer atomizer of 31-, fuel feed pump in 4-, atomizer in 41-, 5- radial direction evaporation tube,
6- radial direction turbulent, the side 7- type face, 9- oil inlet, 10- fixing hanger.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.
As shown in Figure 1 to Figure 3, a kind of sweepback circular arc type pneumatic nebulization vaporation-type stabilizer, including the circumferential direction being arranged concentrically
Evaporation tube 1 and annular turbulent 2, the direction of flow of circumferential evaporation tube 1 are equipped with annular turbulent 2, the rear side of circumferential evaporation tube 1
Tube wall is equipped with a plurality of circumferentially spaced evaporation apertures 11 of an at least row, and annular turbulent 2 includes preceding ring-like body 21, the ring-like face in inside
22 and the ring-like face 23 in outside, preceding ring-like body 21, the ring-like face 23 in the ring-like face 22 in inside and outside are this integral piece；Preceding ring-like body 21
Front end is provided with multiple bleed ports 20 communicated with circumferential evaporation tube 1, formed flow channels (bleed ports 20 and circumferential evaporation tube 1 it
Between the channel that is formed), its rear end is connected with circumferential evaporation tube 1, between preceding ring-like body 21 and circumferential evaporation tube 1 equipped with it is preceding ring-like
The connected ring-like face in the ring-like face in outside and inside of body 21, and the ring-like face in the ring-like face in outside and inside and the angle of preceding ring-like body 21 are equal
For obtuse angle；Chamber, preceding ring-like body are surrounded between annular turbulent 2 (the ring-like face in the ring-like face in outside and inside) and circumferential evaporation tube 1
21 and the circumferential junction in the ring-like face in outside 23 type face in be equipped with the outer fuel feed pump 3 communicated with external fuel oil, positioned at bleed ports 20
The outer fuel feed pump 3 at place is equipped with outer atomizer 31, and injection direction intersects with direction of flow；The ring-like face of preceding ring-like body 21 and inside
It is equipped with the interior fuel feed pump 4 communicated with external fuel oil in the type face of 22 circumferential junctions, on the interior fuel feed pump 4 at bleed ports 20
Equipped with interior atomizer 41, injection direction intersects with the direction of flow of bleed ports 20.
The voltage-stablizer of the present embodiment, which further includes that be arranged on circumferential evaporation tube 1 multiple are vertical with circumferential evaporation tube 1, to be communicated
Radial evaporation tube 5；Radial evaporation tube 5 it is closed at both ends, direction of flow is equipped with the radial flow-disturbing that is connected with annular turbulent 2
Body 6, radial 5 rear side tube wall of evaporation tube are equipped with the multiple radially distributed evaporation apertures 11 of an at least row；The radial direction turbulent 6
Including two side type faces 7 that extend outwardly, chamber, radial turbulent 6 and diameter are formed between two sides type face 7 and radial evaporation tube 5
It is integrated to evaporation tube 5.
The ring-like face 22 in the ring-like face 23 in outside and inside is the cambered surface for being convex to circumferential evaporation tube 1, and is with preceding ring-like body 21
Rounding off connection；There is biggish deflection angle to incoming flow, can use lesser blockage ratio and generate biggish recirculating zone, favorably
Uniform, steady flame, efficient burning in the blending of fuel oil.The side type face 7 of radial 6 rear side of turbulent is the arc for being convex to radial evaporation tube 5
Face is conducive to also generate biggish recirculating zone in radial direction, and in conjunction with circumferential recirculating zone, the Complex Flow Status for forming three-dimensional space shows
It is intended to, as shown in fig. 6, fuel oil and air blending can be strengthened, improves efficiency of combustion.
The quantity of radial evaporation tube 5 is rationally designed according to the size of circumferential evaporation tube 1, and the quantity generally selected is 3
~9, preferably 6.The quantity of bleed ports 20 is rationally designed according to actual needs on circumferential evaporation tube 1, is usually selected
It is 1~3 times of radial turbulent 6, is evenly arranged on annular turbulent 2, preferably 6 bleed ports 20, is located at adjacent radial and evaporates
Between pipe 5.The size of flow channels is gradually increased from bleed ports 20 to circumferential 1 direction of evaporation tube, and is connect with circumferential evaporation tube 1
Locate rounding off, there is biggish deflection angle to incoming flow, can use lesser blockage ratio and generate biggish recirculating zone, be conducive to
The blending of fuel oil is uniform, steady flame, efficient burning.The shape of bleed ports 20 is circle, quadrangle, kidney-shaped or polygon.
As shown in figure 5, the evaporation apertures 11 on the rear side tube wall of circumferential evaporation tube 1 and radial evaporation tube 5 are uniformly distributed two rows,
The section of radial evaporation tube 5 is round, oval, kidney-shaped or shape changeable, and the diameter of evaporation apertures 11 is 1~5mm thereon.
As shown in figure 4, outer fuel feed pump 3 and interior fuel feed pump 4 are ring pipe, quantity is at least one, in annular turbulent 2
Upper setting oil inlet 9 gives 4 fuel feeding of outer fuel feed pump 3 and interior fuel feed pump by oil inlet.It is equipped at the bleed ports 20 of outer fuel feed pump 3
At least two outer atomizers 31, the injection direction of outer atomizer 31 are vertical with the direction of flow of bleed ports 20；Interior fuel feed pump 4 draws
Atomizer 41 at least two is equipped at port 20, the injection direction of interior atomizer 41 is vertical with the direction of flow of bleed ports 20.
Preferably, the outer fuel feed pump 3 and interior fuel feed pump 4 are one, are located relatively at the two sides of flow channels, each fuel feed pump respectively
Atomizer there are two being set at bleed ports 20.Two-way nozzle is arranged at bleed ports 20, and fuel oil is sprayed into perpendicular to side wall, is being drawn
High-speed flow at port 20 shears lower pneumatic nebulization, and runs through entire evaporation tube with air-flow, most arranges through evaporation apertures 11 afterwards
Out, equally distributed fuel-rich fuel concentration field is formed in the recirculating zone of stabilizer rear, as shown in fig. 7, after giving evaporation tube
Square recirculating zone kerosene trajectory line, the fuel-rich gas mixture come out through evaporation apertures 11 are carried to reach by stabilizer recirculating zone and be stablized
Device trailing edge position, secondary pneumatic nebulization blending, forms uniform fuel oil under the further shearing of stabilizer trailing edge high-speed flow
Concentration field.The circumferential evaporation tube 1 of the present embodiment, annular turbulent 2, radial evaporation tube 5 and radial turbulent 6 are structure as a whole,
Two-way oil passage and all nozzles are integrated in inside stabilizer, and nozzle is arranged at bleed ports 20, and fuel oil is sprayed perpendicular to side wall
Enter, form pneumatic nozzle structure, can realize biggish steady flame effect using lesser aerodynamic loss in high-speed flow.
Oil feed line, nozzle, bleed ports 20, evaporation tube become one, and simple and compact for structure, fuel feeding is reliable and stable, benefit
The pneumatic nebulization to fuel oil is realized with the shearing of incoming flow, is enhanced fuel-oil atmozation, air blending, is improved efficiency of combustion.
It is equipped with fixing hanger 10 in the front side of radial turbulent 6, engine load-carrying construction is fixed on using pull rod, pin etc.
On.
The above is only the preferred embodiment of the present invention is described, technical solution of the present invention is not limited to
This, those skilled in the art's made any known deformation on the basis of major technique of the present invention is conceived belongs to institute of the present invention
Technology scope to be protected.
Claims (10)
1. a kind of sweepback circular arc type pneumatic nebulization vaporation-type stabilizer, it is characterised in that: including the circumferential evaporation tube being arranged concentrically
(1) and annular turbulent (2)；
The direction of flow of the circumferential direction evaporation tube (1) is equipped with the annular turbulent (2), the rear tube of circumferential evaporation tube (1)
Wall is equipped with a plurality of circumferentially spaced evaporation apertures of an at least row (11)；
The annular turbulent (2) includes preceding ring-like body (21), the ring-like face in the ring-like face in inside (22) and outside (23)；
The front end of the preceding ring-like body (21) is provided with multiple bleed ports (20) communicated with circumferential evaporation tube (1), forms circulation
Road, its rear end are connected with circumferential evaporation tube (1)；
The ring-like face in the outside being connected with preceding ring-like body (21) is equipped between the preceding ring-like body (21) and circumferential evaporation tube (1)
(23) and the ring-like face in inside (22), and the ring-like face in the ring-like face in outside (23) and inside (22) is equal with the angle of preceding ring-like body (21)
For obtuse angle；
It is outer equipped with what is communicated with external fuel oil in the type face of the circumferential junction of the preceding ring-like body (21) and the ring-like face in outside (23)
Fuel feed pump (3) is located at the outer fuel feed pump (3) at bleed ports (20) and is equipped with outer atomizer (31), injection direction and incoming flow side
To intersection；
It is equipped in the type face of the circumferential junction of the preceding ring-like body (21) and the ring-like face in inside (22) in being communicated with external fuel oil
Fuel feed pump (4) is located at the interior fuel feed pump (4) at bleed ports (20) and is equipped with interior atomizer (41), injection direction and bleed ports
(20) direction of flow intersection.
2. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer according to claim 1, it is characterised in that: the circumferential steaming
Hair pipe (1) is equipped with multiple radial evaporation tubes (5) communicated vertical with circumferential evaporation tube (1)；
The radial direction evaporation tube (5) it is closed at both ends, be equipped with the radial turbulent that is connected with annular turbulent (2) in direction of flow
(6), the rear side tube wall of radial evaporation tube (5) is equipped with the multiple radially distributed evaporation apertures (11) of an at least row；
The radial direction turbulent (6) includes two sides type face (7), forms chamber between two sides type face (7) and radial evaporation tube (5)
Room.
3. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer according to claim 2, it is characterised in that: the outer side ring
The ring-like face in type face (23) and inside (22) is the cambered surface for being convex to circumferential evaporation tube (1), and is round and smooth mistake with preceding ring-like body (21)
It crosses；
Side type face (7) is the cambered surface for being convex to radial evaporation tube (5), and whole sweepback.
4. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer according to claim 3, it is characterised in that: the radial steaming
The quantity of hair pipe (5) is 3~9.
5. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer according to claim 4, it is characterised in that: the circumferential steaming
Evaporation apertures (11) on hair pipe (1) and the rear side tube wall of radial evaporation tube (5) are uniformly distributed two rows；
The diameter of evaporation apertures (11) is 1~5mm.
6. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer structure according to any one of claims 1 to 4, feature exist
It is ring pipe in: the outer fuel feed pump (3) and interior fuel feed pump (4), quantity is at least one；
At least two outer atomizers (31), the injection direction of outer atomizer (31) are equipped at the bleed ports (20) of outer fuel feed pump (3)
It is vertical with the direction of flow of bleed ports (20)；
Atomizer (41) at least two, the injection direction of interior atomizer (41) are equipped at the bleed ports (20) of interior fuel feed pump (4)
It is vertical with the direction of flow of bleed ports (20).
7. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer structure according to claim 6, it is characterised in that: described outer
Fuel feed pump (3) and interior fuel feed pump (4) are one, are set at the bleed ports (20) of each fuel feed pump there are two atomizer.
8. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer structure according to claim 1, it is characterised in that: the mistake
The size of circulation road is gradually increased from bleed ports (20) Xiang Huanxiang evaporation tube (1) direction, and round with circumferential evaporation tube (1) junction
It slips over and crosses.
9. according to claim 8 plunder circular arc type pneumatic nebulization vaporation-type stabilizer structure, it is characterised in that: bleed ports
(20) shape is round, ellipse, kidney-shaped or polygon, the quantity of bleed ports (20) be radial turbulent (6) 1~
It 3 times, is evenly arranged on annular turbulent (2).
10. sweepback circular arc type pneumatic nebulization vaporation-type stabilizer structure according to claim 2, it is characterised in that: described
The section of radial evaporation tube (5) is round, oval, kidney-shaped or polygon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811528926.2A CN109631085B (en) | 2018-12-13 | 2018-12-13 | Sweepback arc type pneumatic atomization evaporation type stabilizer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811528926.2A CN109631085B (en) | 2018-12-13 | 2018-12-13 | Sweepback arc type pneumatic atomization evaporation type stabilizer |
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| Publication Number | Publication Date |
|---|---|
| CN109631085A true CN109631085A (en) | 2019-04-16 |
| CN109631085B CN109631085B (en) | 2020-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811528926.2A Active CN109631085B (en) | 2018-12-13 | 2018-12-13 | Sweepback arc type pneumatic atomization evaporation type stabilizer |
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| Country | Link |
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| CN (1) | CN109631085B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112503571A (en) * | 2020-12-04 | 2021-03-16 | 中国科学院工程热物理研究所 | Afterburner structure of combined flame stabilizer and control method |
| CN113701188A (en) * | 2021-08-19 | 2021-11-26 | 中国航发贵阳发动机设计研究所 | Evaporation formula stabilizer structure |
| CN115371080A (en) * | 2022-07-05 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Enhanced tissue combustion chamber |
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| CN108716695A (en) * | 2018-04-02 | 2018-10-30 | 西北工业大学 | A kind of tiny engine combustion chamber mononuclear type evaporation tube structure design |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
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| JPH0579628A (en) * | 1991-08-19 | 1993-03-30 | Natl Aerospace Lab | Combustion machine for high-speed aeronautical engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112503571A (en) * | 2020-12-04 | 2021-03-16 | 中国科学院工程热物理研究所 | Afterburner structure of combined flame stabilizer and control method |
| CN113701188A (en) * | 2021-08-19 | 2021-11-26 | 中国航发贵阳发动机设计研究所 | Evaporation formula stabilizer structure |
| CN115371080A (en) * | 2022-07-05 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Enhanced tissue combustion chamber |
| CN115371080B (en) * | 2022-07-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Reinforced tissue combustion chamber |
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| Publication number | Publication date |
|---|---|
| CN109631085B (en) | 2020-06-30 |
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