Low-pollution combustion chamber with main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow

Abstract

The invention discloses a low-pollution combustion chamber with a main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow. The low-pollution combustion chamber adopts a single annular cavity structure, and comprises a diffuser, a combustion outdoor box, a combustion indoor box, a flame cylinder outer wall, a flame cylinder inner wall and a combustion chamber head part; the combustion chamber adopts a classification combustion scheme; the combustion head part is divided into a pre-combustion stage and the main combustion stage; the pre-combustion stage adopts a mode of combining rotational flow-stable diffusion combustion with rotational flow premixing combustion; the combustion mode reduces the pollutant discharge under small working conditions when not influencing stable combustion; and the main combustion stage adopts a premixing pre-evaporation combustion mode to be in favor of uniform combustion. The combustion chamber adopts a center classification structure; the pre-combustion stage is simple in structure; the main combustion grade adopts a two-grade reverse cyclone distributed in the radial direction; and two parts of reverse rotational flows shear an oil film, so that the atomization effect is greatly improved, the atomization of fuel of the main combustion stage and the mixing with air are enhanced, the premixing pre-evaporation of the fuel is reinforced, and the pollution discharge of whole landing and taking-off circulation of an aero-engine combustion chamber is further reduced.

Description

technical field [0001] The invention relates to the technical field of aviation gas turbines, in particular to a low-pollution combustion chamber for aviation gas turbines in which the main combustion stage adopts a single-layer pre-film radial two-stage reverse swirl flow. The combustion chamber adopts a staged combustion mode, and the pre-combustion stage is The center uses a combination of diffusion combustion and premixed combustion to ensure stable combustion in the combustion chamber while reducing pollution emissions under small operating conditions; the main combustion stage is located on the periphery of the precombustion stage, using premixed pre-evaporative combustion. It is mainly used to reduce pollution emissions under large working conditions, thereby reducing pollution emissions of the entire landing and take-off (LTO) cycle of the aero-engine. Background technique [0002] The basic performance and structural distribution of modern aero-engine combustors hav...

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Problems solved by technology

[0023] The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art, and use the premixed pre-evaporation combustion technology to provide a low-pollution combustion chamber in which the main combustion stage adopts a single-layer pre-film radial two-stage reverse swirling flow. The combustion chamber adopts the mode of staged combustion, the pre-combustion stage is in the center, and the combination of diffusion combustion and premixed combustion is adopted to ensure the stable combustion of the combustion chamber and reduce the pollution emission under small working conditions; the main combustion stage is in the pre-combustion stage The periphery adopts the method of premixed pre-evaporative combustion, which is mainly used to reduce pollution emissions under large working conditions, thereby reducing the pollution emissions of the entire LTO cycle of the aeroengine

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