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High-temperature measuring section for fuel gas turbine combustor test

A technology for gas turbines and combustion chambers, which is applied in the field of high-temperature measurement sections for combustion chamber tests, can solve the problems of high cost and easy damage, and achieve the effects of low cost, low degree of damage, and short processing cycle

Inactive Publication Date: 2013-10-23
HARBIN TURBINE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention aims to solve the technical problems of high cost and easy damage of the existing gas turbine combustor test high temperature measuring section, and provides a high temperature measuring section for gas turbine combustor test

Method used

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  • High-temperature measuring section for fuel gas turbine combustor test
  • High-temperature measuring section for fuel gas turbine combustor test
  • High-temperature measuring section for fuel gas turbine combustor test

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Experimental program
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specific Embodiment approach 1

[0015] Specific implementation mode one: combine Figure 1 ~ Figure 4 In this embodiment, the high-temperature measurement section for gas turbine combustor test includes an outer cover shell 1, a front flange 2, a rear flange 3 and a high-temperature gas passage 4, and the front end of the outer cover shell 1 is provided with a front flange 2, so The rear end of the housing shell 1 is provided with a rear flange 3, and a high-temperature gas channel 4 is opened between the front flange 2 and the rear flange 3. It is characterized in that the high-temperature measurement section for the gas turbine combustion chamber test also includes a central heat-resistant The pouring material 5 , the central heat-resistant pouring material 5 is fixed and filled on the inner surface of the housing shell 1 by inverted T-shaped nails 11 .

[0016] When the high-temperature measurement section for gas turbine combustor test of the present invention is in use, the exhaust gas (flue gas) of the...

specific Embodiment approach 2

[0023] Embodiment 2: The difference between this embodiment and Embodiment 1 is that the high-temperature measurement section for the gas turbine combustor test also includes a lifting lug 6, a temperature measurement probe interface 7, a flue gas measuring instrument interface 8, and a cooling water interface 9 , the lifting lugs 6 are arranged on both sides of the outer cover shell 1, the static pressure sensor interface 10-1 is arranged directly below the lifting lugs 6, and the temperature measurement probe interface 7 is set on the upper end of the outer cover shell 1 close to the high-temperature gas At the channel entrance 4-1, the cooling water interface 9 is set at the upper end of the outer cover shell 1 close to the high-temperature gas channel outlet 4-2, and there are two ports between the temperature measurement probe interface 7 and the cooling water interface 9 A total pressure sensor interface 10-2, and the flue gas measuring instrument interface 8 is arranged ...

specific Embodiment approach 3

[0024] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the outer casing 1 , the front flange 3 and the rear flange 4 are made of ordinary low alloy steel. Others are the same as in the first or second embodiment.

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Abstract

The invention relates to a high-temperature measuring section for a fuel gas turbine combustor test, and aims to solve the technical problems of high price and easy damage of the existing high-temperature measuring section for the fuel turbine combustor test. The high-temperature measuring section comprises a shield shell, a front flange, a rear flange and a high-temperature fuel gas channel; and the shield shell is provided with the front flange at the front end and is provided with the rear flange at the rear end. The high-temperature measuring section for the fuel gas turbine combustor test is characterized by further comprising a central heat-resistant pouring material, and the central pouring material is fixedly filled in the inner face of the shield shell by an inversed T-shaped nail. The high-temperature measuring section is applied to the field of high-temperature measuring.

Description

technical field [0001] The invention relates to a high temperature measuring section for a combustion chamber test. Background technique [0002] At present, the commonly used measurement section in the combustion chamber test is the water-cooled superalloy measurement section. The disadvantages of the water-cooled superalloy measurement section: the use of high-temperature alloys is expensive; the use of water-cooled jackets has complex structures and long processing cycles; due to the difficulty of water flow in the water jacket , uneven heat transfer and modal boiling are prone to occur, and the cooling water makes the temperature of the measurement section change drastically, which often causes cracks in the components, resulting in water leakage, damage to the measurement section, and potential safety hazards. Contents of the invention [0003] The invention aims to solve the technical problems of high cost and easy damage of the existing gas turbine combustion chambe...

Claims

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Application Information

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IPC IPC(8): G01M15/02
Inventor 张秋鸿张宏涛冯永志王岳王辉赵俊明张文军孙中伟王思远陈洪港于宗明张巍李海涛吴鑫楠王玲
Owner HARBIN TURBINE
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