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A low-emission combustor head with an axial swirl pre-diaphragm plate matching blade injection structure in the main combustion stage

A technology of axial swirling and swirling blades, applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve problems such as fuel atomization and pollution emissions, and achieve full combustion, reduce pollutant emissions, and premixing effects Good results

Active Publication Date: 2020-04-24
BEIHANG UNIV
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is: Aiming at the problems of fuel atomization and pollution emission in the main combustion stage of the central staged combustion chamber, a low-emission combustion chamber in which the main combustion stage adopts an axial swirl pre-membrane plate to match the blade injection structure is proposed head

Method used

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  • A low-emission combustor head with an axial swirl pre-diaphragm plate matching blade injection structure in the main combustion stage
  • A low-emission combustor head with an axial swirl pre-diaphragm plate matching blade injection structure in the main combustion stage
  • A low-emission combustor head with an axial swirl pre-diaphragm plate matching blade injection structure in the main combustion stage

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Embodiment Construction

[0032] Describe the present invention in detail below in conjunction with accompanying drawing and specific embodiment:

[0033] Such as figure 1 As shown, it is a kind of main combustion stage described in the embodiment of the present invention that adopts the head of the low-emission combustion chamber with the axial swirl pre-membrane plate matching the vane injection structure, and adopts the organization combustion of the central classification method, mainly composed of the main combustion chamber Stage swirl blade 01, main combustion stage axial swirl pre-diaphragm blade 02, main combustion stage sleeve 03, main combustion stage channel 04, main combustion stage inner ring 05, interstage section with venturi tube 06, Pre-combustion stage swirler vane 07, pre-combustion stage nozzle outer ring 08, pre-combustion stage nozzle 09, main combustion stage oil circuit pipe 10, main combustion stage oil circuit ring chamber 11. Interstage section 06 has a venturi tube. Among...

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Abstract

The invention discloses a low-emission combustion chamber head with a main combustion stage adopting an axial rotational flow pre-membrane plate matching with blade injection structure. According to the combustion chamber head, the head adopts a center grading design and consists of a main combustion stage and a pre-combustion stage; the main combustion stage is provided an axial rotational flow pre-membrane structure, the main functions of a main combustion stage swirler is that air is enable to generate rotational flow, moreover, fuel oil is injected into the air through small holes in blades, and the fuel oil is atomized and mixed in the swirling air; axial rotational flow pre-membrane blades are aligned with fuel oil injection holes in the swirler blades, and are used for carrying outpre-membrane atomization on the fuel oil, the atomization effect of main combustion stage fuel oil is improved, and therefore the relatively high low-emission performance is achieved; and the pre-combustion stage adopts diffusion flame to stabilized the flame, the main combustion stage adopts the structure in the chamber head to perform fuel oil atomization premixed combustion, so that the low-emission performance of the combustion chamber is further improved.

Description

technical field [0001] The invention relates to the technical field of a swirl burner, in particular to a low-emission combustion chamber head whose main combustion stage adopts an axial swirl pre-diaphragm plate matching blade injection structure. Background technique [0002] Aeroengines are known as the bright pearl of the crown of modern industry. Its design and manufacturing level can best represent the overall industrial level of a country. Aeroengines are divided into military and civilian use according to their uses. Military aero engines use high-temperature-rising combustors for thrust-to-weight ratios, while civil engines use low-emission combustors for efficiency and environmental protection. With the development of the civil aviation industry and the improvement of environmental protection awareness, more stringent requirements will be placed on the pollution emissions of advanced gas turbine combustors in the future. [0003] The center-staged combustion chamb...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38
CPCF23R3/38
Inventor 王建臣韩猛王志超林宇震张弛
Owner BEIHANG UNIV
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