Coaxial partition high-temperature-rise combustor head

A combustion chamber and head technology, which is applied in the field of coaxial partition high-temperature rise combustion chamber head, can solve the problems of inability to guarantee high-efficiency and low-smoke combustion in the main combustion area, smoke in the main combustion area, and carbon deposition.

Active Publication Date: 2018-09-21
AECC SICHUAN GAS TURBINE RES INST
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Problems solved by technology

With the increase of the total oil-gas ratio of the combustion chamber, if the flow distribution scheme of the original combustion chamber is designed, the residual gas coefficient of the main combustion area will be less than 1, which will lead to smoke and serious accumulation in the main combustion area. It can be seen that conventional combustion chamber technology can no longer guarantee high-efficiency and low-smoke combustion in the main combustion zone. At this time, the combustion organization of the combustion chamber, the flow distribution of air and fuel, and the structural form will all change.

Method used

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  • Coaxial partition high-temperature-rise combustor head
  • Coaxial partition high-temperature-rise combustor head
  • Coaxial partition high-temperature-rise combustor head

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Embodiment Construction

[0027] The present invention will be described in detail below in conjunction with the accompanying drawings and specific implementation examples.

[0028] refer to figure 1 , is a schematic structural diagram of a coaxial partitioned high-temperature rise combustion chamber 10, including a diffuser 11, an outer casing 12, an inner casing 13, a nozzle 14, a head 15, a flame cylinder 16, an electric nozzle 17, and a flame cylinder as required Main combustion hole 18 and mixing hole 19 are arranged, or can cancel main combustion hole 18 and keep mixing hole 19. The working conditions of the combustion chamber are: air enters the combustion chamber from the diffuser 11, more than 40% of the air enters the flame cylinder 16 from the head 15, and the remaining air enters the flame cylinder 16 through the combustion outer ring 20 and the combustion inner ring 21, and the fuel oil It enters the flame tube 16 through the nozzle 14. In the flame tube 16, after the electric nozzle 17 i...

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Abstract

The invention relates to a coaxial partition high-temperature-rise combustor head which comprises a first-stage axial hydrocyclone (31), a venturi (32), a main-stage fuel oil way (33), a second-stageaxial hydrocyclone (34), a baffling device (35), a three-stage axial hydrocyclone (36) and a splash pan (37). A middle cooling runner (41) is formed between the venturi (32) and the main-stage fuel oil way (33), an expansion section of the venturi (32) is provided with a plurality of rows of cooling small holes (42), part of air flowing into the middle cooling runner (41) flows out from the cooling small holes (42) in the expansion section of the venturi (32), the other part of air flows through the periphery of a main spraying opening (43) in the tail end of the main-stage fuel oil way (33) to flow out from a main-stage fuel oil atomization channel (44).

Description

technical field [0001] The patent of the invention belongs to the field of aero-engines, and relates to a head of a coaxial partitioned high-temperature rise combustion chamber. Background technique [0002] Modern high-performance fighter jets generally use small bypass ratio turbofan engines. In order to achieve high-speed maneuvering, the requirements for engine thrust-to-weight ratio are getting higher and higher (from 8 to 10 to 16 to 20), and the cycle parameters of the engine are also continuously improved. , the total boost ratio has reached over 40, and the temperature at the inlet and outlet of the combustion chamber has increased from 800 to 1650K to 1000 to 2150K. At present, major aero-engine manufacturers are vigorously conducting research on military high-temperature rise combustors. [0003] The research and development of high-temperature rise combustion technology began in the mid-1970s. The successful development of the RB-199 engine represented a first-s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/34F23R3/12
CPCF23R3/12F23R3/286F23R3/346
Inventor 桂韬房人麟邱伟黄兵夏丽敏王蓉隽
Owner AECC SICHUAN GAS TURBINE RES INST
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