Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber

Abstract

The invention relates to a main combustion stage tangential oil supply premix and pre-evaporation combustion chamber. The combustion chamber is in a single-ring chamber structure and is designed by adopting the conceptual design of staging combustion, and all the used amount of gas for combustion is supplied by the precombustion stage and the main combustion stage. The combustion chamber mainly comprises a flow-dividing type diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle, the precombustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall. The precombustion stage utilizes a low-speed flow returning zone generated by swirl air entering the combustion chamber by a precombustion stage swirler component; the fuel needed by the main combustion stage is ejected by the tangential main combustion stage nozzle, is atomized under the air flow effect generated by entering of atomized air of the main combustion stage nozzle into a pipe, then flows into a premix and pre-evaporation ring pipe for evaporation, and is further blended with air; and even oil-gas mixed gas formed at the outlet of the premix and pre-evaporation ring pipe enters a flame tube and combusts under the pilot combustion of the precombustion stage flame. The combustion chamber has simple structure, and can effectively reduce the discharge of pollution simultaneously while guaranteeing that an aeroengine is in normal working state.

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 CAEP6 (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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