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Engine high pressure turbine blade surface temperature measuring device

A technology of measuring device and high-pressure turbine, applied in measuring device, thermometer, measuring heat, etc., can solve the problems of unbearable measuring means, high temperature of turbine blades of aero-engine, large error, etc., to avoid heat accumulation and improve production efficiency , to avoid the effect of repeated driving

Active Publication Date: 2015-04-01
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0002] The temperature of the turbine blades of the working aero-engine is high, generally around 1500-2000 degrees. This temperature index plays a major role in the process of testing the engine's working performance. Usually, the measurement method cannot withstand such a high temperature. Now the temperature at this place is measured by calculation. method, indirect measurement, the error is large, and it is impossible to evaluate the specific value of the error

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Embodiment Construction

[0014] The present invention is specifically described below in conjunction with accompanying drawing, as figure 1 , figure 2 As shown, the present invention includes a mounting flange 4, and the measuring device is installed on the casing in front of the engine turbine through the mounting flange 4; the mounting flange 4 fixes the "U" type liquid cooling device 2, and the "U" type A "U"-shaped gas cooling device 3 is arranged in the liquid cooling device 2, and a through hole 5 is arranged in the "U"-shaped gas cooling device 3, and a photoelectric probe 1 is arranged in the through hole 5;

[0015] In order to further cool the photoelectric probe 1 and prevent heat accumulation in the through hole 5, the mounting flange 4 is provided with a bell mouth 6, and the bell mouth 6 is connected to the through hole 5;

[0016] The wall thickness of the outer side 21 of the liquid cooling device 2 is greater than that of the inner side 22;

[0017] In order to prevent the front en...

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Abstract

The invention discloses an engine high pressure turbine blade surface temperature measuring device. The engine high pressure turbine blade surface temperature measuring device comprises a mounting flange, wherein the measuring device is mounted on a casing of an engine turbine, the mounting flange fixes a U-shaped liquid cooling device, the U-shaped liquid cooling device is internally provided with a U-shaped gas cooling device, the U-shaped gas cooling device is internally provided with a through hole, and the through hole is internally provided with a probe. The engine high pressure turbine blade surface temperature measuring device realize cooling of the photoelectric probe through three modes of water cooling, gas cooling and wind cooling and guarantees work temperature of the photoelectric probe, so temperature of a turbine blade can be accurately measured, a problem in monitoring temperature of the engine turbine blade in vehicle tests is solved, data support is provided for solving engine faults, production efficiency is improved, and driving repetition caused by certain faults can be avoided.

Description

Technical field: [0001] The invention relates to a measuring device, in particular to a temperature measuring device, more specifically to a measuring device for the surface temperature of an engine turbine blade. technical background: [0002] The temperature of the turbine blades of the working aero-engine is high, generally around 1500-2000 degrees. This temperature index plays a major role in the process of testing the engine's working performance. Usually, the measurement method cannot withstand such a high temperature. Now the temperature at this place is measured by calculation. The method of indirect measurement has a large error, and it is impossible to evaluate the specific value of the error. Contents of the invention [0003] In order to solve the above-mentioned technical problems, the purpose of the present invention is to measure the temperature of the surface of the turbine blades of the engine in real time and monitor the working state of the engine by arr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01K1/14G01K1/143
Inventor 杨福刚常诚黄祁茂崔博王立志朱哲
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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