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A kind of cleaning method of heavy-duty gas turbine combustor nozzle

A technology for gas turbines and combustion chambers, applied to cleaning methods and appliances, chemical instruments and methods, and cleaning hollow objects, etc., can solve the problems of foreign matter clogging and difficult discharge, and achieve the effects of simple assembly, reasonable structure, and guaranteed nozzle flow path

Active Publication Date: 2022-07-22
HARBIN TURBINE +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention proposes a cleaning method for the nozzle of the combustion chamber of the heavy-duty gas turbine in order to solve the problem that foreign objects are blocked and difficult to be discharged during the production process of the nozzle of the combustion chamber of the existing heavy-duty gas turbine

Method used

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  • A kind of cleaning method of heavy-duty gas turbine combustor nozzle
  • A kind of cleaning method of heavy-duty gas turbine combustor nozzle
  • A kind of cleaning method of heavy-duty gas turbine combustor nozzle

Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0019] Embodiment 1: The cleaning method for a heavy-duty gas turbine combustor nozzle in this embodiment is carried out according to the following steps:

[0020] 1. Backflush the heavy-duty gas turbine combustor nozzle using the combustor nozzle cleaning component:

[0021] The combustion chamber nozzle cleaning assembly is composed of a cylinder block 1, a gas pipe flange 2 and an air pipe flange cover 3; the cylinder block 1 is composed of a cylinder block flange 5, a cylindrical cylinder wall 6 and a water inlet flange 7 One end of the cylinder wall 6 is open, the other end of the cylinder wall 6 is provided with a bottom plate, the water inlet flange 7 is arranged on the outer wall of the open end of the cylinder wall 6, and the water inlet flange 7 is arranged on the center of the bottom plate of the cylinder wall 6 ; The center of the gas pipe flange 2 is a threaded hole, and the threaded hole is provided with a plug 4;

[0022] First, put the cylinder block 1 for cle...

specific Embodiment approach 2

[0030] Embodiment 2: The difference between this embodiment and Embodiment 1 is that the cylinder flange 5, the cylinder wall 6 and the water inlet flange 7 are connected by welding.

specific Embodiment approach 3

[0031] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that an O-ring is provided between the cylinder flange 5 and the flange at the rear end of the nozzle body of the combustion chamber.

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Abstract

A nozzle cleaning method for a heavy-duty gas turbine combustion chamber relates to a nozzle cleaning method. The purpose is to solve the problem that the foreign matter is blocked and difficult to discharge during the production process of the existing heavy-duty gas turbine combustor nozzle. Method: Use the component for cleaning the nozzle of the combustion chamber to reversely flush the nozzle of the combustion chamber of the heavy-duty gas turbine: the component for cleaning the nozzle of the combustion chamber is composed of the cylinder block, the gas pipe flange and the air pipe flange cover; the cylinder block is composed of the cylinder block flange, The cylindrical cylinder wall and the water inlet flange are formed; the center of the gas pipe flange is a threaded hole, and the threaded hole is provided with a plug; blue for forward flushing. The cylinder structure adopted by the invention is simple, and the reverse flushing and forward flushing do not damage the structure of the nozzle, and at the same time solve the problem that the foreign matter in the gas passage of the nozzle cannot be removed in a small position. The present invention is suitable for nozzle cleaning.

Description

technical field [0001] The invention relates to a cleaning method for a heavy-duty gas turbine combustion chamber nozzle. Background technique [0002] The heavy-duty gas turbine uses the continuous flow of gas as the working medium to drive the impeller to rotate at a high speed and convert the energy of the fuel into kinetic energy internal combustion power machinery. The output and efficiency of a gas turbine, as well as pollutant emissions and thermal stability, largely depend on the flow characteristics of the gas turbine combustor nozzle. The nozzle is the core part of the combustion chamber, which is one of the three important body structures of the gas turbine. The flow characteristics of the nozzle are directly related to the flow distribution and pressure drop design of the combustion chamber, which in turn affects the combustion process and cooling effect. Therefore, it is necessary to ensure that the nozzle flow channel is clean. No foreign objects. [0003] Ex...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B08B9/032
CPCB08B9/0321
Inventor 董生权宋建成杨克振张璐赵瑜
Owner HARBIN TURBINE
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