CN113154447B - Support plate stabilizer for enhanced combustion of afterburner - Google Patents
Support plate stabilizer for enhanced combustion of afterburner Download PDFInfo
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- CN113154447B CN113154447B CN202110285065.5A CN202110285065A CN113154447B CN 113154447 B CN113154447 B CN 113154447B CN 202110285065 A CN202110285065 A CN 202110285065A CN 113154447 B CN113154447 B CN 113154447B
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- plate stabilizer
- blade
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- 239000003381 stabilizer Substances 0.000 title claims abstract description 123
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 46
- 230000000694 effects Effects 0.000 claims abstract description 16
- 238000002156 mixing Methods 0.000 claims abstract description 15
- 239000000446 fuel Substances 0.000 claims abstract description 3
- 230000000903 blocking effect Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 8
- 238000010008 shearing Methods 0.000 claims description 6
- 230000006641 stabilisation Effects 0.000 claims description 6
- 238000011105 stabilization Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 4
- 230000010349 pulsation Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 230000002708 enhancing effect Effects 0.000 abstract 1
- 230000003014 reinforcing effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 7
- 230000000087 stabilizing effect Effects 0.000 description 4
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Of Fluid Fuel (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention discloses a support plate stabilizer for reinforcing combustion of an afterburner, which belongs to the field of combustion of aeroengines, wherein turbulent flow devices with different structural types are designed at the tail edge of the original support plate stabilizer along the height direction and are uniformly arranged along the height direction, the inlet high-speed incoming flow of the afterburner flows through the tail edge of the support plate stabilizer, a complex vortex structure with strong entrainment effect is formed at the rear end of the stabilizer along the height direction due to the action of the turbulent flow device, the development of the shear layer at the rear edge of the support plate is quickened, the mixing of fuel in the main flow is promoted, the mass, momentum and heat exchange between the air flow along the high-speed main flow and the high-temperature backflow area at the tail of the support plate are enhanced, thereby quickening the turbulent combustion speed, therefore, the invention can effectively improve the combustion efficiency of the afterburner, shorten the length of the afterburner, widen the flameout boundary of the afterburner and achieve the effect of enhancing combustion in the afterburner.
Description
Technical Field
The invention belongs to the field of combustion of aeroengines, and particularly relates to a support plate stabilizer for enhanced combustion of an afterburner.
Background
As military aircraft take-off, climb and maneuver, greater thrust is required. Currently, the thrust is increased in a short time by installing an afterburner. However, in the second generation engine and the previous engine, the oil injection device and the flame stabilizer of the afterburner are arranged separately, and the oil injection device is easy to coke and the stabilizer is easy to ablate due to the high-speed high-temperature air flow. In order to avoid the problems, in the afterburner of the third-generation machine, the stabilizer consists of radial and circumferential stabilizers, and oil injection devices are arranged in the two stabilizers. The circumferential stabilizer plays a role of flame transfer and conducts an external air flow, thereby cooling the radial stabilizer. The four-generation machine adopts the afterburner with the turbine rear frame integrated, combines the afterburner flame stabilizer with the turbine rear bearing bracket and cancels the circumferential stabilizer, thereby greatly shortening the length of the afterburner and effectively avoiding the occurrence of coking and ablation of the nozzle. However, the air flow speed of the inlet of the afterburner is too high, so that the mass, momentum and heat exchange between the main flow of the combustor and the air flow in a high-temperature area is less, the combustion efficiency of the afterburner is generally lower, and the flameout boundary is narrower.
Disclosure of Invention
Aiming at the problems existing in the prior art, the invention discloses an integrated afterburner support plate type flame stabilizing device for increasing the mixing degree of air flow in a combustion area, turbulence devices with different structural types are arranged at the tail edge of the stabilizing device and are uniformly arranged along the height direction.
The invention is realized in the following way:
The support plate stabilizer for the afterburner enhanced combustion is characterized in that a turbulence device is arranged at the tail part of the support plate stabilizer, the turbulence devices are uniformly arranged along the height direction, and the blade structure type of the turbulence devices has an influence on the shearing and blending effect and the exchange strength of mass, momentum and heat between the main flow and the high-temperature backflow along the tail part of the support plate; the blade structure of the turbulence device adopts various types, including rectangle, isosceles triangle and isosceles trapezoid; the blades of the turbulence device comprise straight blades and curved blades; the inlet of the afterburner flows through the tail of the support plate stabilizer at a high speed, and due to the action of the turbulence device arranged at the tail of the support plate stabilizer, a complex vortex structure with strong entrainment action is formed at the rear end of the stabilizer along the height direction, so that the development of a shearing layer at the rear edge of the support plate stabilizer is accelerated, the blending of fuel in the main flow is promoted, and the mass, momentum and heat exchange between the air flows of the support plate tail along the high-speed main flow and the high-temperature backflow area are enhanced.
Further, the tail width of the support plate stabilizer is set to be W, the blade height of the turbulence device is set to be h, the blade width of the turbulence device is set to be L, and the tail width W of the support plate stabilizer, the blade height of the turbulence device and the width ratio h/L have influence on the total pressure loss and the size of a backflow area of the stabilizer, so that the efficiency of the afterburner is influenced; the width W range of the tail part of the support plate stabilizer in rectangular, isosceles triangle and isosceles trapezoid configurations is 5-40 mm; the height and width ratio h/L of the blades of the rectangular turbulence device are in a range of 0.1-5; the height and width ratio h/L of the blades of the turbulence device with isosceles triangle configuration are in the range of 0.1-6; the height and the width ratio h/L of the blades of the turbulence device in the isosceles trapezoid configuration are in the range of 0.1-5.5, the upper bottom width is set as R for the turbulence blades in the isosceles trapezoid configuration, the ratio h/R of the height of the blades to the upper bottom width also has an effect on the total pressure loss of the stabilizer and the size of a backflow area, and the ratio h/R is in the range of 0.1-10.
Further, the angle between the blade of the turbulent device and the axial airflow is set to be the installation angle of the tail edge of the support plate stabilizer, and the installation angle of the tail edge of the support plate stabilizer has an influence on the size of a backflow area and the exchange strength of mass, momentum and heat between the high-speed incoming flow of the inlet of the afterburner and the high-temperature backflow of the tail part of the stabilizer, so that the reinforced combustion effect is influenced; when the blade of the turbulence device is a straight blade, the installation angle theta 1 of the turbulence blade is in the range of-60 degrees to 60 degrees; when the blade of the turbulence device is a bent blade, the installation angle theta 2 of the turbulence blade is in the range of-70 degrees to 70 degrees.
Further, setting the ratio of the orthographic projection area of the support plate stabilizer on the section of the afterburner to the section of the combustion chamber as the blocking ratio of the support plate stabilizer, wherein the blocking loss of the support plate stabilizer is determined by the parameters of the blocking ratio of the support plate stabilizer, so that the pressure loss coefficient of the support plate stabilizer is influenced; the blocking ratio range of the rectangular, isosceles triangle and isosceles trapezoid support plate stabilizer is 10% -50%.
Further, the height of the blade of the turbulence device is set to be h, the length of the support plate stabilizer is set to be n, and the ratio h/n of the height of the turbulence blade to the length of the support plate stabilizer has an influence on the length of the reflux area and the shearing blending effect, so that the combustion enhancement effect is influenced; the ratio h/n of the height of the tail spoiler blade of the rectangular, isosceles triangle and isosceles trapezoid support plate stabilizer to the length of the support plate stabilizer is 0.01-0.8, 0.01-0.9 and 0.01-0.85 respectively.
Further, when the blade structure of the turbulence device adopts an isosceles triangle and an isosceles trapezoid, the base angle angles of the turbulence blades of the isosceles triangle and the isosceles trapezoid are respectively set to be alpha 1, alpha 2,α1 and alpha 2, which have influence on the size of a backflow area and the total pressure loss of the stabilizer, so that the efficiency of the afterburner is influenced; the bottom angle alpha 1 of the turbulent flow blade in the isosceles triangle configuration ranges from 5 to 85 degrees, and the bottom angle alpha 2 of the turbulent flow blade in the isosceles trapezoid configuration ranges from 5 to 85 degrees.
Further, the working method of the support plate stabilizer comprises the following steps:
setting the incoming flow speeds at two sides of the afterburner flame stabilizer as I and II respectively, wherein when the incoming flows at two sides pass through the tail edge of the support plate stabilizer, the gas in the shielding area behind the support plate stabilizer is sucked under the action of viscous force to form a local low-pressure area III; as the airflow passes through the tail of iii, the airflow speed is slowed down and the static pressure is increased, thereby creating a pressure differential with the preceding negative pressure zone;
under the action of the front-back pressure difference, a part of gas flows to a shielding area behind the support plate stabilizer in a flow direction opposite to the main flow; because the whole process is continuous, namely the air flow behind the support plate stabilizer is continuously taken away and is continuously supplemented by the air flow behind the support plate stabilizer in a countercurrent way, symmetrical vortexes are formed behind the support plate stabilizer and continuously rotate, and the support plate stabilizer is called a backflow area;
the air flow speed in the backflow area is low, flame stabilization is realized, turbulent combustion occurs at the flame stabilization area, and a high-temperature backflow area is formed; because the tail edge of the support plate stabilizer is provided with different turbulence structures along the height direction, when the high-speed air flow passes through the tail edge of the flame stabilizer, the air flow speed difference of different positions along the height direction is larger, so that the speed pulsation is rapidly enhanced, the turbulence degree is increased, the turbulent combustion speed is accelerated, the mass, momentum and heat exchange between the high-temperature backflow area behind the stabilizer and the incoming flow of the afterburner inlet are enhanced, the combustion completeness is increased, the flameout boundary of the afterburner is widened, and the combustion efficiency is improved.
Compared with the prior art, the invention has the beneficial effects that:
1) According to the afterburner support plate type flame stabilizing device for increasing the turbulence and blending degree of the air flow in the combustion area, through designing the turbulence devices with different structural types at the tail edge of the support plate stabilizer along the height direction, the mass, momentum and heat exchange between the high-speed incoming flow of the inlet of the afterburner and the air flow in the high-temperature backflow area behind the flame stabilizer is enhanced, so that the aim of improving the combustion efficiency of the afterburner is fulfilled, the combustion performance of the combustion chamber is improved, and the emission of pollutants is reduced;
2) The combustion efficiency of the afterburner is improved, and the combustion is more complete, so that the combustion is enhanced without increasing the length of the afterburner, the length of the afterburner can be further shortened, the weight of the afterburner is reduced, and the thrust-weight ratio of the afterburner is improved;
3) The invention can improve the turbulence and blending degree of the airflow in the combustion area of the afterburner, thereby widening the flameout boundary of the afterburner and achieving the purpose of widening the flight envelope range of the military aircraft.
Drawings
FIG. 1 is a typical block diagram of a turbofan engine with afterburner;
FIG. 2 is a typical block diagram of an aft frame integrated afterburner for a turbine;
FIG. 3 is a three-dimensional block diagram of a strut stabilizer with different structural styles of turbulators;
FIG. 4 is a rear view of the stent stabilizer;
FIG. 5 is a side view of a strut stabilizer with rectangular spoiler blades;
FIG. 6 is a side view of a strut stabilizer with isosceles triangle spoiler blades;
FIG. 7 is a side view of a strut stabilizer with isosceles trapezoid spoiler blades;
FIG. 8 is a block diagram of a strut stabilizer with different mounting angle spoiler blades;
fig. 9 is a graph of airflow blending effect near a strut stabilizer.
Detailed Description
In order to make the objects and effects of the present invention more clear and clear, the present invention will be described in further detail with reference to the accompanying drawings. It should be noted that the detailed description herein is for purposes of illustration only and is not intended to limit the invention.
FIG. 1 is a typical block diagram of a turbofan engine with afterburner and FIG. 2 is a typical block diagram of an afterburner integrated with a turbine aft frame, the mounting location of the present invention being a strut stabilizer as shown in FIG. 2. FIG. 3 shows a flame stabilizing structure of the invention, wherein turbulence devices with different structural types are arranged at the tail part of the supporting plate stabilizer, and the structural types can be respectively designed into a rectangle, an isosceles triangle and an isosceles trapezoid for increasing the turbulence and the mixing degree of the air flow in the combustion area. FIG. 4 is a rear view of a strut stabilizer, and FIGS. 5-7 are side views of a stabilizer with three different configurations of turbulators, wherein the strut stabilizer tail width W, the height to width ratio of the turbulator blade h/L, the ratio of the height of the isosceles trapezoid to the upper sole width h/R, the ratio of the height of the turbulator blade to the stabilizer length h/n, and the values of the parameters of the isosceles triangle and trapezoid turbulator blade base angle angles α 1 and α 2 are related to the pressure loss of the strut stabilizer, Turbulence, blending effect, etc. are affected, so that reasonable selection is required. FIG. 8 is a block diagram of a strut stabilizer with differently angled spoiler blades, wherein blade mounting angles θ 1 and θ 2, and whether the blade is a straight blade or a curved blade, etc. have an impact on the size of the recirculation zone and blending efficiency, etc., and therefore a reasonable selection is also required. FIG. 9 is a graph of the effect of airflow blending near the plate stabilizer, where the incoming flow rates I and II on either side of the afterburner flame stabilizer are relatively high (typically 500-600 m/s), and when passing the trailing edge of the plate stabilizer, the gas in the shielding region behind the stabilizer is entrained by the viscous force, forming a localized low pressure region III. As the airflow passes through the tail of iii, the airflow slows down and the static pressure increases, creating a pressure differential with the preceding negative pressure zone. Under the action of the front-rear pressure difference, a part of gas flows to the shielding area behind the stabilizer in the flow direction opposite to the main flow. Since the whole process is continuous, i.e. the air flow behind the plate stabilizer is continuously taken away and is continuously supplemented by the backward air flow, a substantially symmetrical vortex is formed behind the stabilizer and constantly rotates, called a backflow zone. The air flow speed in the backflow area is low, flame stabilization can be realized, turbulent combustion occurs at the flame stabilization area, and a high-temperature backflow area is formed; because the tail edge of the support plate stabilizer is provided with different turbulence structures along the height direction, when the high-speed airflow passes through the tail edge of the flame stabilizer, the speed difference of the airflow at different positions along the height direction is larger, so that the speed pulsation is rapidly enhanced, the turbulence degree is increased, the turbulent combustion speed is accelerated, the mass, momentum and heat exchange between the high-temperature backflow area behind the stabilizer and the incoming flow of the afterburner inlet are enhanced, the combustion completeness is increased, the flameout boundary of the afterburner is widened, and the combustion efficiency is improved.
The foregoing is merely a preferred embodiment of the invention, and it should be noted that modifications could be made by those skilled in the art without departing from the principles of the invention, which modifications would also be considered to be within the scope of the invention.
Claims (7)
1. The support plate stabilizer for the afterburner enhanced combustion is characterized in that a turbulence device is arranged at the tail part of the support plate stabilizer, the turbulence devices are uniformly arranged along the height direction, and the blade structure type of the turbulence devices has an influence on the shearing and blending effect and the exchange strength of mass, momentum and heat between the main flow and the high-temperature backflow along the tail part of the support plate; the blade structure of the turbulence device adopts various types, including rectangle, isosceles triangle and isosceles trapezoid; the blades of the turbulence device comprise straight blades and curved blades; the inlet of the afterburner flows through the tail of the support plate stabilizer at a high speed, and due to the action of the turbulence device arranged at the tail of the support plate stabilizer, a complex vortex structure with strong entrainment action is formed at the rear end of the stabilizer along the height direction, so that the development of a shearing layer at the rear edge of the support plate stabilizer is accelerated, the blending of fuel in the main flow is promoted, and the mass, momentum and heat exchange between the air flows of the support plate tail along the high-speed main flow and the high-temperature backflow area are enhanced.
2. The support plate stabilizer for the afterburner enhanced combustion according to claim 1, wherein the tail width of the support plate stabilizer is set to be W, the blade height of the turbulence device is set to be h, the blade width of the turbulence device is set to be L, and the tail width W of the support plate stabilizer, the blade height of the turbulence device and the width ratio h/L have influence on the total pressure loss and the size of a backflow zone of the stabilizer, so that the afterburner efficiency is influenced; the width W range of the tail part of the support plate stabilizer in rectangular, isosceles triangle and isosceles trapezoid configurations is 5-40 mm; the height and width ratio h/L of the blades of the rectangular turbulence device are in a range of 0.1-5; the height and width ratio h/L of the blades of the turbulence device with isosceles triangle configuration are in the range of 0.1-6; the height and the width ratio h/L of the blades of the turbulence device in the isosceles trapezoid configuration are in the range of 0.1-5.5, the upper bottom width is set as R for the turbulence blades in the isosceles trapezoid configuration, the ratio h/R of the height of the blades to the upper bottom width also has an effect on the total pressure loss of the stabilizer and the size of a backflow area, and the ratio h/R is in the range of 0.1-10.
3. The support plate stabilizer for the afterburner intensified combustion according to claim 1, wherein the angle between the blade of the turbulent device and the axial air flow is set as the installation angle of the support plate stabilizer tail along the turbulent blade, and the installation angle of the support plate stabilizer tail along the turbulent blade has an influence on the size of a backflow area and the quality, momentum and heat exchange strength between the high-speed incoming flow of the afterburner inlet and the high-temperature backflow of the stabilizer tail, so that the intensified combustion effect is influenced; when the blade of the turbulence device is a straight blade, the installation angle theta 1 of the turbulence blade is in the range of-60 degrees to 60 degrees; when the blade of the turbulence device is a bent blade, the installation angle theta 2 of the turbulence blade is in the range of-70 degrees to 70 degrees.
4. A plate stabilizer for afterburner enhanced combustion as claimed in claim 1, wherein the ratio of the orthographic projection area of the plate stabilizer on the afterburner cross-section to the combustion chamber cross-section is set to be the plate stabilizer blocking ratio, and the parameters of the plate stabilizer blocking ratio determine the blocking loss of the plate stabilizer, thereby affecting the pressure loss coefficient of the plate stabilizer; the blocking ratio range of the rectangular, isosceles triangle and isosceles trapezoid support plate stabilizer is 10% -50%.
5. The support plate stabilizer for the afterburner enhanced combustion according to claim 1, wherein the height of the blade of the turbulence device is set as h, the length of the support plate stabilizer is set as n, and the ratio h/n of the height of the blade of the turbulence device to the length of the support plate stabilizer has an influence on the length of the return zone and the shearing blending effect, thereby influencing the enhanced combustion effect; the ratio h/n of the height of the tail spoiler blade of the rectangular, isosceles triangle and isosceles trapezoid support plate stabilizer to the length of the support plate stabilizer is 0.01-0.8, 0.01-0.9 and 0.01-0.85 respectively.
6. The support plate stabilizer for enhanced combustion of afterburner according to claim 1, wherein when the vane structure of the turbulence device adopts isosceles triangle or isosceles trapezoid, the base angle angles of the turbulence vanes of isosceles triangle and isosceles trapezoid are set to be α 1, α 2,α1 and α 2 respectively, which have influence on the size of the backflow area and the total pressure loss of the stabilizer, thereby influencing the efficiency of afterburner; the bottom angle alpha 1 of the turbulent flow blade in the isosceles triangle configuration ranges from 5 to 85 degrees, and the bottom angle alpha 2 of the turbulent flow blade in the isosceles trapezoid configuration ranges from 5 to 85 degrees.
7. The plate stabilizer for afterburner enhanced combustion as claimed in claim 1, wherein the plate stabilizer is operated by:
setting the incoming flow speeds at two sides of the afterburner flame stabilizer as I and II respectively, wherein when the incoming flows at two sides pass through the tail edge of the support plate stabilizer, the gas in the shielding area behind the support plate stabilizer is sucked under the action of viscous force to form a local low-pressure area III; as the airflow passes through the tail of iii, the airflow speed is slowed down and the static pressure is increased, thereby creating a pressure differential with the preceding negative pressure zone;
under the action of the front-back pressure difference, a part of gas flows to a shielding area behind the support plate stabilizer in a flow direction opposite to the main flow; because the whole process is continuous, namely the air flow behind the support plate stabilizer is continuously taken away and is continuously supplemented by the air flow behind the support plate stabilizer in a countercurrent way, symmetrical vortexes are formed behind the support plate stabilizer and continuously rotate, and the support plate stabilizer is called a backflow area;
the air flow speed in the backflow area is low, flame stabilization is realized, turbulent combustion occurs at the flame stabilization area, and a high-temperature backflow area is formed; because the tail edge of the support plate stabilizer is provided with different turbulence structures along the height direction, when the high-speed air flow passes through the tail edge of the flame stabilizer, the air flow speed difference of different positions along the height direction is larger, so that the speed pulsation is rapidly enhanced, the turbulence degree is increased, the turbulent combustion speed is accelerated, the mass, momentum and heat exchange between the high-temperature backflow area behind the stabilizer and the incoming flow of the afterburner inlet are enhanced, the combustion completeness is increased, the flameout boundary of the afterburner is widened, and the combustion efficiency is improved.
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| CN202110285065.5A CN113154447B (en) | 2021-03-17 | 2021-03-17 | Support plate stabilizer for enhanced combustion of afterburner |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114857617B (en) * | 2022-05-20 | 2023-07-14 | 南昌航空大学 | Support plate flame stabilizer of band saw tooth type groove vortex generator |
| CN115307179B (en) * | 2022-08-15 | 2023-08-01 | 北京航空航天大学 | Curved support plate double-concave-cavity integrated afterburner |
| CN116025926B (en) * | 2023-03-10 | 2024-07-05 | 中国航发沈阳发动机研究所 | Afterburner of aeroengine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE956898C (en) * | 1953-07-01 | 1957-01-24 | Carborundum Co | Flame holder for Pitot tube jet engines |
| US3269116A (en) * | 1965-04-29 | 1966-08-30 | United Aircraft Corp | Centrally supported flameholder |
| JP2798338B2 (en) * | 1993-04-07 | 1998-09-17 | 株式会社日立製作所 | Gas turbine combustor and gas turbine engine |
| JP3956882B2 (en) * | 2002-08-22 | 2007-08-08 | 株式会社日立製作所 | Gas turbine combustor and gas turbine combustor remodeling method |
| CN105650677B (en) * | 2016-02-26 | 2018-04-17 | 南京航空航天大学 | Flameholder with novel cooling structure integrated design |
| CN105841191B (en) * | 2016-03-30 | 2018-07-06 | 中国科学院工程热物理研究所 | A kind of V-flame stabilizer trailing edge structures |
| CN106678876B (en) * | 2016-11-18 | 2019-03-01 | 西北工业大学 | A kind of after-burner designing airflow channel in rectification supporting plate |
| CN107191968A (en) * | 2017-06-05 | 2017-09-22 | 西北工业大学 | One kind combination cooled rectification support plate flameholder |
| CN110762555B (en) * | 2019-10-24 | 2024-04-19 | 南京航空航天大学 | Pneumatic auxiliary type cavity support plate flame stabilizer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| BE682403A (en) * | 1965-10-01 | 1966-11-14 | ||
| CN105402769A (en) * | 2015-11-30 | 2016-03-16 | 南京航空航天大学 | Novel flame stabilizer with boss turbulence structures |
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