A low-pollution combustion chamber in which the main combustion stage adopts an axial two-stage distributed swirler

Abstract

The invention discloses a low-pollution combustion chamber in which the main combustion stage adopts an axial two-stage distributed swirler, adopts a single-ring cavity structure, and includes a diffuser, a casing outside the combustion chamber, a casing inside the combustion chamber, the outer wall of the flame cylinder, The inner wall of the flame tube and the head of the combustion chamber, the combustion chamber adopts a staged combustion scheme, and the combustion head is divided into a pre-combustion stage and a main combustion stage. This combustion method reduces the emission of pollutants under small working conditions without affecting stable combustion; the main combustion stage adopts a premixed pre-evaporative combustion method, which is conducive to uniform combustion. The present invention adopts a centrally graded structure, and the structure of the pre-combustion stage is simple; the main combustion stage adopts a unique axial two-stage distributed swirler, which enhances the mixing of the main combustion stage fuel oil and air, and makes the oil mist distribution more uniform. Therefore, the pollution discharge of the entire landing and take-off cycle of the combustion chamber of the aero-engine 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 axial two-stage distributed swirlers. The combination of diffusion combustion and premixed combustion ensures stable combustion in the combustion chamber and reduces pollution emissions under small operating conditions; Reduce pollution emissions under large operating conditions, thereby reducing pollution emissions of the entire landing and take-off (LTO) cycle of the aeroengine. 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 It is the source to ensure its continuous progress. [0...

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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 to provide a low-pollution combustion chamber in which the main combustion stage adopts an axial two-stage distributed swirler by using the premixed pre-evaporative combustion technology. Combustion mode, the pre-combustion stage is in the center, adopting the combination of diffusion combustion and pre-mixed combustion, while ensuring the stable combustion of the combustion chamber, and reducing pollution emissions under small working conditions; the main combustion stage is on the periphery of the pre-combustion stage, using The way of premixed pre-evaporative combustion is mainly used to reduce pollution emissions under large operating conditions, thereby reducing pollution emissions of the entire LTO cycle of aero-engines

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