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An anti-backfire type nozzle connection section assembly of a gas turbine combustor

A technology for gas turbines and connecting sections, applied in combustion chambers, combustion types, continuous combustion chambers, etc., can solve problems such as failure to guarantee damage to nozzle hardware due to tempering

Active Publication Date: 2016-09-07
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although this solution can ensure that the nozzle continues to work, it cannot guarantee the damage to the nozzle hardware caused by tempering. At the same time, this effective working method is based on the cost of pollutant emissions and non-design working conditions

Method used

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  • An anti-backfire type nozzle connection section assembly of a gas turbine combustor
  • An anti-backfire type nozzle connection section assembly of a gas turbine combustor
  • An anti-backfire type nozzle connection section assembly of a gas turbine combustor

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Embodiment Construction

[0024] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.

[0025] figure 2 It is a schematic structural diagram of a nozzle connecting section assembly in the prior art. The nozzle connection section assembly includes a fuel nozzle connection section 54 and a fuel nozzle assembly 32, the fuel nozzle assembly 32 includes a swirler 33, a fuel injection device 35 and a nozzle assembly central body 36; the fuel injection device 35 is reasonably installed in the center of the nozzle assembly body 36, and is upstream of the axial position of the central body end 37 of the nozzle assembly; the fuel nozzle connecting section 54 includes a cylindrical channel 61, which is limited by the inner wall 62 of the cylindrical channel; when combustion instability occurs downstream of the fuel nozzle connecting section 54, The flame from the combustion zone flashes back, enters the cylin...

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PUM

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Abstract

The utility model relates to an anti-backfire type nozzle connecting section assembly of a combustion chamber of a gas turbine, which belongs to the structural design of the combustion chamber of the gas turbine. The nozzle connection section assembly includes a fuel nozzle assembly and a fuel nozzle connection section outside the fuel nozzle assembly; the fuel nozzle assembly includes a swirler, a fuel injection device and a nozzle assembly center body; the fuel nozzle connection section includes a cylindrical Channel, converging channel and expanding channel; the axial location of the throat where the converging channel connects with the expanding channel is located downstream of the axial location of the center body end of the nozzle assembly. Since the present invention adopts a special structural form in the fuel nozzle connecting section, especially improves the structure of the inner channel of the fuel nozzle connecting section, when flashback occurs downstream, the upstream fuel nozzle assembly can be effectively protected and prevented from being burned.

Description

technical field [0001] The invention relates to the structural design of a gas turbine, in particular to an anti-backfire type nozzle connection section assembly of a combustion chamber of a gas turbine. Background technique [0002] figure 1 It is a typical combustion chamber structure in the prior art. The gas turbine 10 includes a compressor 12 (partially marked), multiple combustion chambers (only one is marked in the figure) and a turbine (represented by turbine blades 16 in the figure) ). The turbine 16 shares a common axis with the compressor 12 . The air entering from the compressor 12 is pressurized, enters the combustion chamber 14 countercurrently, burns and cools along the way, and finally enters the turbine 16 . [0003] As noted above, the gas turbine 10 includes a plurality of combustors 14 positioned around the gas turbine. Each combustion chamber 14 includes an end cover assembly 30, which includes fuel supply pipes and corresponding valves, etc.; a plur...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23D14/82F23D14/48F23R3/38
Inventor 李珊珊
Owner CHINA UNITED GAS TURBINE TECH CO LTD