A variable geometry ultra-compact combustor with adjustable boundary combustion

Abstract

The invention discloses a variable geometry ultra-compact combustion chamber with a boundary combustion adjustable function. According to the variable geometry ultra-compact combustion chamber, a center body is sequentially sleeved with a diffusion flow divider, a throttle disc and a composite guide vane channel, and an inner ring air outlet of the diffusion flow divider communicates with the composite guide vane channel through the throttle disc; a variable combustion cavity can achieve variable geometry adjusting, the adjustable wall surface of the variable combustion cavity adopts one of two adjusting modes, namely rotating inclining and parallel moving, and a corresponding mechanical adjusting mechanism is arranged outside the cavity; and the inner side of the variable combustion cavity communicates with one side of an air inlet of the composite guide vane channel, and an outer ring air outlet of the diffusion flow divider communicates with the combustion cavity through secondary flow air inlet holes in the front wall surface of the cavity to achieve coaxial axial air inlet of a primary flow and a secondary flow. The wall surface of the cavity can be adjusted, the space of thecombustion cavity is effectively controlled, the pressure loss of the combustion chamber can be effectively reduced within the same equivalence ratio range, outlet velocity distribution is improved, NO emission is reduced, and the working range of the combustor chamber is enlarged.

Description

technical field [0001] The invention relates to a variable geometry ultra-compact combustion chamber with adjustable boundary combustion, and belongs to the technical field of ultra-compact combustion chamber structures. Background technique [0002] As an important performance index, the thrust-to-weight ratio of an aero-engine directly affects the range, ceiling and load of an aircraft. In order to increase the thrust-to-weight ratio of the engine, first, it is necessary to increase the gas temperature in front of the turbine, increase the outlet speed, and increase the thrust of the engine, but an excessively high inlet temperature in front of the turbine will increase the difficulty of cooling the turbine guide vanes and shorten the life of the entire engine; Under certain thrust conditions, the thrust-to-weight ratio of the engine can be improved by reducing the engine mass. [0003] The main combustion chamber of a traditional engine includes not only the main combust...

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Problems solved by technology

[0003] The main combustion chamber of a traditional engine includes not only the main combustion zone for fuel-rich combustion, but also the intermediate zone and the mixing zone for supplementary combustion of the main combustion zone. The axial length of the combustion chamber is long and the mass is large; The combustion process of the combustion chamber is also carried out along the axial direction. The length and mass of the combustion chamber are relatively large, which is not conducive to improving the thrust-to-weight ratio of the engine.

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