Premixing and pre-evaporating combustion chamber

Abstract

The invention discloses a premixing and pre-evaporating combustion chamber, which has a single annular chamber structure and adopts a conceptual design of fractional combustion. In the combustion chamber, the total combustion gas volume is supplied by a pre-combustion fraction and a main combustion fraction, the pre-combustion fraction adopts a swirl-flow stable diffusion flame combustion organization mode and the main combustion fraction adopts a premixing and pre-evaporating combustion organization mode. The combustion chamber mainly comprises a shunting diffuser, a combustion chamber outer casing, a combustion chamber inner casing, a fuel oil nozzle, the pre-combustion fraction, the main combustion fraction, a combustion liner outer wall and a combustion liner inner wall. The pre-combustion fraction stabilizes flame by using a low-speed refluxing zone generated by swirl air entering the combustion chamber from a pre-combustion fraction swirler; and after being sprayed out by a main combustion fraction nozzle, the fuel oil needed by the main combustion fraction first form an oil-gas mixed gas through atomization under the action of an air flow in a prefilming air ring in the main combustion fraction nozzle and then flows to the premixing and pre-evaporating fraction to be evaporated and further blended with the air, so a uniform oil-gas mixed gas jet flow is formed at the position of the outlet of the premixing and pre-evaporating fraction and enters the combustion liner to be ignited by flame in the pre-combustion fraction to combust. The combustion chamber is simple in structure and can effectively reduce pollutant discharge while ensuring an aeroengine works normally.

Description

technical field [0001] The invention relates to an aviation gas turbine combustor adopting a premixed pre-evaporative combustion organization mode. The combustor adopting the premixed pre-evaporative combustion organization mode has a simple structure, and can reduce combustion pollution emissions while ensuring efficient and stable operation of the combustor . Background technique [0002] The basic performance and structural distribution of modern aero-engine combustors have reached a fairly high level, but for modern aero-engine combustors, there are still a lot of problems and challenges. The development of new materials, new processes, new structures, and new concepts Application is the source to ensure its continuous progress. [0003] The main development trend of modern aero-engine combustors is low-pollution combustion. Aeroengine combustors must meet increasingly stringent aeroengine pollution emission standards. The currently adopted CAEP4 (Committee on Aviatio...

AI Technical Summary

Problems solved by technology

In the low power state, the equivalent ratio of the combustion zone is very low, which is far lower than the above-mentioned equivalence ratio range required for low-pollution combustion. At this time, although NOx emissions are low, CO and UHC emissions are high

In addition, because the conventional combustion chamber generally adopts the diffusion combustion method, the local equivalence ratio is very uneven, so for the conventional combustion chamber, it cannot meet the low pollution requirements in the entire engine operating range

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