Low-pollution combustion chamber with premixed and pre-evaporated precombustion part

Abstract

The invention relates to a low-pollution combustion chamber with a premixed and pre-evaporated precombustion part, which adopts a monocylic cavity structure and comprises a pressure diffuser, an outer receiver of a combustion chamber, an outer wall of a flame tube, an inner wall of the flame tube and a combustion chamber head, wherein all air for combustion enters the flame tube from the combustion chamber head, a grade combustion scheme is adopted and comprises a precombustion grade and a main combustion grade ; the main combustion grade adopts a premixed combustion mode, and the precombustion grade adopts a mode of combining diffusion combustion with stable rotational flow and rotational-flow premixed combustion; and the precombustion grade adopts the mode of combining the diffusion combustion and the premixed combustion, and pollutant discharge under a small working condition is reduced without influencing stable combustion. In the invention, the precombustion grade structure is simple, and the pollutant discharge is reduced under a small working condition without influencing the combustion stability so as to ensure that the pollution discharge of the whole landing and take-off (LTO) of an aircraft engine combustion chamber is further reduced.

Description

technical field [0001] The invention relates to a low-pollution combustor of an aviation gas turbine utilizing premixed pre-evaporative combustion technology. The staged combustion mode is adopted, and the main combustion stage adopts premixed combustion, which is mainly used to reduce pollution emissions under large working conditions; the precombustion stage adopts a combination of diffusion combustion and premixed combustion to ensure stable combustion in the combustion chamber. At the same time, it reduces the pollution emissions under small working conditions, thereby reducing the pollution emissions of the entire LTO cycle of the aero-engine. Background technique [0002] The basic performance and structural distribution of modern aero-engine combustors have reached a fairly high level, but there are still a lot of problems and challenges for modern aero-engine combustors. The development and application of new materials, new processes, new structures, and new concepts...

AI Technical Summary

Problems solved by technology

[0022] The technical problem to be solved by the present invention is: to overcome the deficiencies in the prior art, and to provide a low-pollution combustion chamber with pre-mixed pre-evaporation in the pre-combustion stage, the main combustion stage of the combustion chamber adopts pre-mixed pre-evaporation combustion technology. The co-combustion me

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