Premix and pre-evaporation combustion chamber

Abstract

The invention discloses a tangential premix and pre-evaporation combustion chamber. The combustion chamber has a single-ring cavity structure; and through a design by adopting a concept of staged combustion, combustion gas is totally supplied by a pre-combustion stage and a main combustion stage, wherein the pre-combustion stage adopts a steady-rotational flow diffusion flame combustion organization mode; and the main combustion stage adopts a premix and pre-evaporation combustion organization mode. The combustion chamber mainly comprises a flow-dividing diffuser, an outer casing of the combustion chamber, an inner casing of the combustion chamber, a fuel nozzle, the pre-combustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall, wherein the pre-combustion stage stabilizes the flame by a low-speed return area generated by rotational flow air entering the combustion chamber from a pre-combustion stage swirler assembly; and the fuel needed by the main combustion stage is ejected from a nozzle of the main combustion stage, is atomized to form oil-gas mixed gas under the airflow action of a prefilming air ring of the nozzle of the main combustion stage, flows into a premix and pre-evaporation section to be evaporated, is further doped with the air to form a uniform oil-gas mixed air jet at an opening of the premix and pre-evaporation section to enter the flame tube, and is combusted under the ignition of a pre-combustion stage flame. The tangential premix and pre-evaporation combustion chamber has the advantages of simple structure and capacities of guaranteeing the normal working state of an aircraft engine and effectively reducing pollution discharge simultaneously.

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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