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Method for cleaning nozzle of combustion chamber of heavy duty gas turbine

A technology for gas turbines and combustion chambers, which is applied to cleaning methods and appliances, chemical instruments and methods, and cleaning hollow objects, etc. It 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: 2021-03-30
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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  • Method for cleaning nozzle of combustion chamber of heavy duty gas turbine
  • Method for cleaning nozzle of combustion chamber of heavy duty gas turbine
  • Method for cleaning nozzle of combustion chamber of heavy duty gas turbine

Examples

Experimental program
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specific Embodiment approach 1

[0019] Specific embodiment one: In this embodiment, the method for cleaning the nozzle of the combustion chamber of the heavy-duty gas turbine is carried out according to the following steps:

[0020] 1. Backwashing the combustor nozzles of heavy-duty gas turbines with components for cleaning the combustor nozzles:

[0021] The assembly for cleaning the nozzle of the combustion chamber is composed of a cylinder body 1, a gas pipe flange 2 and an air pipe flange cover 3; the cylinder body 1 is composed of a cylinder body 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 at the center of the bottom plate of the cylinder wall 6 ; The center of the gas pipe flange 2 is a threaded hole, and a plugging screw 4 is arranged in...

specific Embodiment approach 2

[0030] Embodiment 2: This embodiment differs from Embodiment 1 in that: the cylinder body flange 5 , cylinder wall 6 and water inlet flange 7 are connected by welding.

specific Embodiment approach 3

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

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Abstract

The invention discloses a method for cleaning a nozzle of a combustion chamber of a heavy duty gas turbine and relates to a nozzle cleaning method, and aims to solve the problem that foreign matters block the nozzle and are hardly discharged in a production process of an existing nozzle of the combustion chamber of the heavy duty gas turbine. The method comprises the following steps of: flushing the nozzle of the combustion chamber of the heavy duty gas turbine reversely by using an assembly for cleaning the nozzle of the combustion chamber: the assembly for cleaning the nozzle of the combustion chamber is composed of a cylinder, a gas pipe flange and an air pipe flange cover; the cylinder is composed of a cylinder flange, a cylindrical cylinder wall and a water inlet flange; a center of the gas pipe flange is a threaded hole and a plugging screw is arranged in the threaded hole; and detaching the cylinder after being flushed reversely, and connecting a high pressure water pipe to theflange pipe flange for forward flushing. The cylinder is simple in structure, and the problem that the foreign matters in a nozzle gas channel clamped small positions cannot be eliminated is solved while the nozzle structure is not damaged by reverse flushing and forward flushing. The method is suitable for cleaning the nozzle.

Description

technical field [0001] The invention relates to a method for cleaning a nozzle of a combustion chamber of a heavy-duty gas turbine. Background technique [0002] The heavy-duty gas turbine uses continuously flowing gas as the working medium to drive the impeller to rotate at high speed, and convert the energy of the fuel into kinetic energy for internal combustion power machinery. The output and efficiency of gas turbines, as well as pollutant emissions and thermal stability largely depend on the flow characteristics of the gas turbine combustor nozzles. The nozzle is the core part of the combustion chamber, one of the three important main 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 organization process and cooling effect. Therefore, it is necessary to ensure that the nozzle flow path is clean No foreign matter...

Claims

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Application Information

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Patent Type & Authority Applications(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