Premixing pre-evaporation low-pollution combustion chamber with multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage

Abstract

The invention relates to a premixing pre-evaporation low-pollution combustion chamber with a multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage, which adopts a single ring cavity structure. The combustion chamber adopts a staged combustion manner; the head of the combustion chamber is divided into a pre-combustion stage and the main combustion stage; the pre-combustion stage adopts a diffusion combustion manner, so that when combustion stability is ensured, pollutant discharge under the small working condition is reduced; and the main combustion stage adopts a premixing pre-evaporation combustion manner, so that combustion pollutants can be effectively reduced. According to the invention, the central staged structure is adopted and the pre-combustion stage has a simple structure; the main combustion stage adopts the scheme of combining a multi-point axial double-stage air auxiliary atomizing nozzle and a premixing pre-evaporation section and is positioned and installed by a main combustion stage spray nozzle installation ring; the main combustion stage has a simple structure; fuel is atomized, evaporated and mixed under the action of two strands of rotational flow and interacts with rotational flow air in the premixing pre-evaporation section to form a uniform fuel-gas mixture; and the premixing pre-evaporation low-pollution combustion chamber is beneficial to the pollutant discharge level of the integral landing and take-off cycle of an aircraft engine combustion chamber.

Description

technical field [0001] The invention relates to the technical field of aviation gas turbines, in particular to a premixed pre-evaporation low-pollution combustion chamber of the main combustion stage of a multi-point axial double-stage air-assisted atomizing nozzle. In the center, a combination of diffusion combustion and premixed combustion is adopted to ensure the stability and safety of the combustion chamber and reduce pollution emissions under small working conditions; the main combustion stage is located on the radial periphery of the precombustion stage, and In the way of premixed pre-evaporative combustion, the head of the main combustion stage is axially supplied with fuel at multiple points. The invention is beneficial to reduce the pollution emission of the entire combustion chamber, and ensure the efficient and stable operation of the combustion chamber, thereby reducing the pollution emission level of the entire landing and take-off (LTO) cycle of the aeroengine. ...

AI Technical Summary

Problems solved by technology

[0021] The technical problem to be solved by the present invention is: to overcome the deficiencies of the existing technology, and to provide a multi-point axial double-stage air-assisted atomizing nozzle main combustion stage premixed pre-evaporation low-pollution combustion chamber by using the pre-mixed pre-evaporation combustion technology , the combustion chamber adopts the central staged combustion mode, the pre-combustion stage is in the center, and the combination of diffusion combustion and premixed combustion is adopted to ensure the stability and safety of the combustion chamber and reduce pollution emissions; the main combustion stage adopts dual The combination of stage air-assisted atomizing nozzle and premixed pre-evaporation section has a simple structure and is easy to install, which not only reduces pollution emissions under small working conditions, but also ensures the radial and circumferential uniformity of the main combustion stage fuel. It is beneficial to reduce the pollution emission level of the aero-engine combustion chamber throughout the landing and take-off cycle

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