Low-emission combustion chamber with double-layer axial hydrocyclone adopted at precombustion stage

Abstract

The invention discloses a low-emission combustion chamber with a double-layer axial hydrocyclone at a precombustion stage. The combustion chamber is of a single annular cavity structure and structurally comprises a pressure expander, a combustion chamber exterior casing, a combustion chamber interior casing, a flame tube and a combustion chamber head; all combustion-used air enters the flame tube through the combustion chamber head, a staged combustion scheme is adopted, and the combustion is divided into into the precombustion stage and a primary combustion stage; a premixed combustion mode is adopted at the primary combustion stage, and a diffusive combustion mode serves as the main mode of the precombustion stage; the double-layer axial hydrocyclone is adopted at the precombustion stage, two blasts of rotational flow can maintain individual flowing through a partition plate, and momentum loss due to the fact that the two blasts of rotational flow make contact with each other too early is avoided; the two blasts of rotational flow are utilized for reinforcing fuel oil atomization and mixing, meanwhile, reasonable recirculating zone distribution is generated, efficient and stable combustion under small working conditions is guaranteed, and meanwhile pollutant emission is lowered; the combustion chamber is simple in structure at the precombustion stage and easy to machine and install, combustion chamber emission under small working conditions can be lowered, and thereby the low emission performance of a total landing and taking-off cycle of the combustion chamber is improved.

Description

technical field [0001] The invention relates to a low-emission combustion chamber, in particular to a low-emission combustion chamber in which a pre-combustion stage adopts double-layer axial swirlers. Background technique [0002] An aero engine is a highly complex and sophisticated thermomechanical engine that provides the power required for aircraft to fly. As the heart of the aircraft, it is known as the "Flower of Industry", which directly affects the performance, reliability and economy of the aircraft. Aeroengines can be simply classified into civil aeroengines and military aeroengines according to their usage. Compared with military aeroengines, civil aeroengines have stricter requirements in terms of low fuel consumption, low emissions, and low noise. Among them, low emissions mainly need to be achieved by optimizing the design of the combustion chamber. [0003] The main pollutant emissions of modern civil aviation engines include: nitrogen oxides (NOx), carbon ...

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is: aiming at the problem that the fuel atomization of the existing low-emission combustor is poor in small working conditions, and the combustion efficiency and low emission are difficult to balance, the staged combustion mode is adopted, and the main combustion stage adopts premixed combustion , the pre-combustion stage adopts a double-layer axial swirler to strengthen the atomization and mixing of fuel under small working conditions, so as to ensure stable combustion, improve the combustion performance of the combustion chamber under small working conditions, and reduce pollution emission

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