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

A technology of combustion chamber and main combustion stage, applied in combustion chamber, continuous combustion chamber, combustion method, etc., to achieve the effects of high combustion efficiency, easy assembly, and reduced pollution emissions

Active Publication Date: 2011-04-27
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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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,

Method used

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

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[0032] figure 1 It is a schematic diagram of the engine structure, including a low-pressure compressor 1, a high-pressure compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5. When the engine is working, the air is compressed by the low-pressure compressor 1 and then enters the high-pressure compressor 2. The high-pressure air then enters the combustion chamber 3 to complete the combustion with fuel. The high-temperature and high-pressure gas formed after combustion enters the high-pressure turbine 4 and the low-pressure turbine 5, and passes The turbine does work to drive the high-pressure compressor 2 and the low-pressure compressor 1 respectively.

[0033] Such as figure 2 As shown, the combustion chamber 3 adopts a single-ring cavity structure, and the combustion outdoor casing 6 and the combustion chamber casing 7 constitute the outer contour of the combustion chamber, and are connected to the front and rear high pressure compressor 2 ...

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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

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Claims

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Application Information

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Owner BEIHANG UNIV
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