Igniter position adjustment mechanism for gas turbine combustor test
A gas turbine and regulating mechanism technology, applied in gas turbine engine testing, jet engine testing, engine testing, etc., can solve the problems of frequent disassembly and assembly of igniters, complicated steps, igniter damage, etc., to improve the ignition success rate, optimize Ignition position, the effect of enhancing ignition performance
Active Publication Date: 2022-05-10
HANGZHOU TURBINE POWER GRP
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Problems solved by technology
[0005] The purpose of the embodiment of the present invention is to provide an igniter position adjustment mechanism for gas turbine combustion chamber test, which aims to solve the problem that the existing ignition position test requires frequent disassembly and assembly of the igniter, complicated steps, and easy damage to the igniter
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[0025] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.
[0026] The specific implementation of the present invention will be described in detail below in conjunction with specific embodiments.
[0027] Such as figure 1 As shown, it is a schematic structural diagram of an igniter position adjustment mechanism for a gas turbine combustor test provided by an embodiment of the present invention, including an igniter 2, and the igniter position adjustment mechanism for a gas turbine combustor test also includes an igniter assembly base 8. The first axial adjustment screw 5, the igniter position locking screw 9, the sealing cover 4 and the igniter mounting se...
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The invention is suitable for the technical field of combustion chamber testing equipment, and in particular relates to an igniter position adjustment mechanism for gas turbine combustion chamber testing. The embodiment of the present invention provides an igniter position adjustment mechanism for gas turbine combustion chamber test, which changes the traditional test method of fixing the igniter position in the gas turbine combustion chamber test, and drives the igniter by pushing the igniter mounting seat through the first axial adjustment screw Move along the axial direction to complete the precise adjustment in the axial direction, and drive the igniter to move up and down relative to the igniter mounting seat through the thread to complete the precise adjustment in the radial direction, thus realizing the igniter axis in the gas turbine combustor test The adjustment of the radial and radial positions optimizes the ignition position, improves the success rate of ignition, and enhances the ignition performance of the combustion chamber.
Description
technical field [0001] The invention belongs to the technical field of combustion chamber testing equipment, in particular to an igniter position adjustment mechanism for gas turbine combustion chamber testing. Background technique [0002] In the combustion chamber of a gas turbine, the ignition performance directly affects the working safety and reliability of the entire gas turbine. The ignition position directly affects the ignition success rate and is an important parameter affecting the ignition performance, which in turn affects the aerodynamic layout and structural design of the entire combustion chamber. With the enhancement of environmental awareness, the formulated emission standards require industrial gas turbines to reduce emissions of nitrogen oxides (NOx), carbon monoxide (CO) and unburned hydrocarbons (UHC), so lean-burn premixing technology is widely used in the gas turbine combustor. For the lean-burn premixing technology, under normal circumstances, the ...
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IPC IPC(8): G01M15/02G01M15/14
CPCG01M15/02G01M15/14
Inventor 衡思江傅燕妮蓝吉兵李祎曼孟惠任占洋隋永枫王良臧鹏张宇明
Owner HANGZHOU TURBINE POWER GRP