Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe

Abstract

The invention provides a premixing pre-vaporization combustion chamber for a main combustible stage of a discrete pipe. The combustion chamber is in a single annulus structure, and consists of a combustion chamber outer case, a combustion chamber inner case, a flame tube outer wall, a flame tube inner wall and a combustion chamber head, wherein combusting air completely enters a flame tube from the combustion chamber head, a staged combustion scheme, namely a pre-combustible stage and the main combustible stage, is adopted; a swirl cup is adopted in the pre-combustible stage which is of a diffusion combustion organization mode; a premixing pre-vaporization device is adopted in the main combustible stage, a main combustible stage nozzle supplies fuel axially, the fuel is vaporized in the premixing pre-vaporization device and blended with air, the uniformly mixed combustible gas enters the combustion chamber to participate in combustion, namely a premixing combustion organization mode. The pre-combustible stage controls the range of stable work of the combustion chamber, and provides a stable ignition source for the main combustible stage; and the main combustible stage controls main pollution emission of the combustion chamber, and lower pollution emission of the combustion chamber is realized by controlling the equivalence ratio of premixed gas of the main combustible stage. The premixing pre-vaporization device has a simple structure, and can realize that the pollution emission of an aircraft engine combustion chamber can be reduced on the basis of not influencing the combustion stability.

Description

technical field [0001] The invention relates to a low-pollution combustor of an aviation gas turbine utilizing premixed pre-evaporative combustion technology. The staged combustion mode is adopted, the main combustion stage adopts the premixed combustion method, and multiple premixed pre-evaporation sections are evenly arranged around the pre-combustion stage in the circumferential direction to form the main combustion stage, and the head of each premixed pre-evaporation section is axially supplied fuel. The invention can reduce pollution emissions and ensure efficient and stable operation of the combustion chamber. Background technique [0002] The basic performance and structural distribution of modern aero-engine combustors have reached a fairly high level, but there are still a lot of problems and challenges for modern aero-engine combustors. The development and application of new materials, new processes, new structures, and new concepts It is the source to ensure its...

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art, and use the premixed pre-evaporation combustion technology to provide a premixed pre-evaporation combustor of the main combustion stage of the discrete tube. The oil and gas distribution in the combustion zone of the combustor is even, Guarantee the engine under small working conditions (the typical operating conditions of aero-engines include ground idle, approach, high-altitude cruise, climb, and take-off, and the total oil and gas in the combustion chamber is lower than normal in the ground idle and approach states, which are considered to be small operating conditions) While working stably, it can also maintain low pollution emissions under large working conditions (the total oil-gas ratio in the combustion chamber is generally high when cruising at high altitude, climbing, and taking off, which is considered to be a large working condition)

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