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CN-117469694-B - Multistage lobe type concave cavity standing vortex type support plate flame stabilizer

CN117469694BCN 117469694 BCN117469694 BCN 117469694BCN-117469694-B

Abstract

A multistage lobe type concave cavity standing vortex type support plate flame stabilizer comprises a support plate, wherein the tail of the support plate is perpendicular to the flow direction of an afterburner, concave cavities are formed in two sides of the support plate, a first-stage lobe mixer and a second-stage lobe mixer are sequentially arranged on the lower side of each concave cavity, and the second-stage lobe mixers are located at the tail of the support plate and are staggered with the first-stage lobe mixers. According to the invention, aiming at the problem that the flow field distribution between any two support plates is poor when a plurality of support plates are arranged in an array manner in practical application, the asymmetric design is adopted to optimize, stable standing vortex is obtained by utilizing a concave cavity to primarily mix fuel and air, a primary lobe mixer is used for efficiently mixing fuel-air mixture primarily mixed in the concave cavity with external inflow air by generating a flow direction vortex structure, and after the primary lobe mixer passes, mixed oil gas is further mixed with the inflow air at a secondary lobe mixer, so that the fuel is more uniformly distributed in a combustion chamber, the distribution area of the fuel in an afterburner is enlarged, and the combustion is more sufficient during ignition.

Inventors

  • HUANG YUE
  • FENG ZIYI
  • LI ZHENYAO
  • BAI YUSONG
  • YOU YANCHENG

Assignees

  • 厦门大学

Dates

Publication Date
20260508
Application Date
20231212

Claims (8)

  1. 1. A multistage lobe type concave cavity standing vortex type support plate flame stabilizer is characterized by comprising a support plate, wherein the front edge of the support plate is in an airfoil shape, the tail of the support plate is perpendicular to the flow direction of an afterburner, concave cavities are formed in the middle of two sides of the support plate, a first-stage lobe mixer and a second-stage lobe mixer are sequentially arranged on the lower side of each concave cavity, the first-stage lobe mixer is combined with the concave cavities, the second-stage lobe mixers are located at the tail of the support plate and are staggered with the first-stage lobe mixer, the connecting line of the circle centers of the lobes of the first-stage lobe mixer is parallel to the boundary of the concave cavities, the lobes of the second-stage lobe mixer are perpendicular to the radial direction of the afterburner, the lobes of the first-stage lobe mixer are tangential to the concave cavity structure, and the depths of the lobes of the first-stage lobe mixer are consistent with the depths of the concave cavities at the same positions.
  2. 2. The multi-stage lobe type concave cavity standing vortex support flame stabilizer as set forth in claim 1, wherein the depth of the concave cavity is 20% -40% of the thickness of the support.
  3. 3. The multi-stage lobe type concave cavity trapped vortex support plate flame stabilizer of claim 1, wherein the width of the concave cavity is 7% -15% of the length of the support plate.
  4. 4. A multi-stage lobed concave cavity trapped vortex support flame holder as defined in claim 1 wherein said cavity extends longitudinally through the support.
  5. 5. The multi-stage lobe type concave cavity standing vortex type support plate flame stabilizer as set forth in claim 1, wherein the lobes of the primary lobe mixer and the secondary lobe mixer are of semicircular lobe structures, and the radius of a single semicircular lobe structure is 5% -20% of the height of the support plate.
  6. 6. A multi-stage lobe type concave cavity standing vortex support flame holder as defined in claim 1, wherein the two side primary lobe mixers are asymmetrically staggered.
  7. 7. A multi-stage lobe type concave cavity standing vortex type support plate flame holder as set forth in claim 1, wherein two-stage lobe mixers at two sides are asymmetrically staggered.
  8. 8. The multi-stage lobe type concave cavity trapped vortex support plate flame holder of claim 1, wherein said two-stage lobe mixer flow upwards occupies 20% -30% of the entire support plate length.

Description

Multistage lobe type concave cavity standing vortex type support plate flame stabilizer Technical Field The invention relates to the field of afterburners of aeroengines, in particular to a multistage lobe type concave cavity trapped vortex type support plate flame stabilizer for an integrated afterburner. Background The combat ability of a fighter aircraft is greatly affected by the aircraft engine. The afterburner is positioned between the turbine and the tail nozzle of the engine, and the fresh air introduced by the mixed outer duct is combusted by performing secondary oil injection on the fuel gas flowing through the turbine so as to obtain larger thrust. As one of important parts of the aero-engine, the mass of the afterburner accounts for only about 20% of the total mass of the engine, but the thrust of the turbofan engine can be improved by 40% -50% and the thrust of the turbojet engine can be improved by 60% -70%. Afterburners can fully improve the maneuverability of the engine and are important in the development of military aircraft. In a conventional afterburner, the flame holder is arranged separate from the support plate, taking up a relatively long space in the engine. At the same time, more components means that the overall pressure recovery coefficient of the afterburner is affected and the flow resistance loss is greater in cold conditions without opening the force. Therefore, the length of the engine can be shortened by integrally designing the traditional flame stabilizer and the support plate, and the quality of the engine can be further reduced. The existing integrated support plate flame stabilizer has difficulty in combining the mixing efficiency and the total pressure recovery coefficient performance. The flame stabilizer of the integrated support plate with the triangular spoiler at the tail part can greatly reduce the total pressure recovery coefficient while improving the mixing efficiency, and the support plate without the triangular spoiler has better total pressure recovery performance but lower mixing efficiency. In the advanced integrated afterburner, the inlet inflow temperature is obviously increased, the inlet airflow speed is also obviously increased, and the residence time of fuel in the combustor is shortened. Under the condition that the incoming flow speed of the engine is increased, the existing two types of integrated support plate flame stabilizers can inevitably influence the atomization effect and the mixing efficiency of fuel oil in use, and the problems of insufficient combustion and the like are caused. Meanwhile, in the current design, the flow field between the adjacent support plates is optimized at least when a plurality of support plate arrays are arranged in practical application, and the uniformity of fuel and cold and hot air flow distribution is difficult to improve by a symmetrical structure design method. Therefore, in the process of integrally designing the oil injection port, the support plate and the flame stabilizer in the afterburner, the mixing efficiency of fuel atomization and the total pressure recovery performance of the afterburner are considered. The combustion stability and economy of the afterburner can be improved by good design, the working performance is improved, and the afterburner has good development prospect. Disclosure of Invention The invention aims to solve the problems in the prior art, provides the multistage lobe type concave cavity standing vortex type support plate flame stabilizer which is reliable in structure, is optimally designed for flow field distribution when a plurality of support plates of an integrated afterburner are arranged in practical application, can keep good working performance in the cold state flow or the hot state working state of the afterburner, reduces flow loss, enhances the mixing effect of fuel and air, improves the combustion effect in the afterburner, improves the combustion efficiency, further increases the thrust, and can reduce the blocking ratio and improve the performance under the condition of arranging the plurality of support plates. The hot state flow refers to the working process that the high-temperature gas flowing out of the turbine is mixed with fresh air in the afterburner, and is injected with oil again to ignite, and the cold state flow refers to the working process that the engine does not start boosting, and the high-temperature gas flowing out of the turbine directly flows through the tail nozzle to be sprayed out. In order to achieve the above purpose, the invention adopts the following technical scheme: The multistage lobe type concave cavity standing vortex type support plate flame stabilizer comprises a support plate, wherein the front edge of the support plate is in an airfoil design, the tail of the support plate is perpendicular to the flow direction of an afterburner, concave cavities are formed in the middle of two sides of the support plate, a first-stage lobe