Integrated optical circuit device for monitoring temperature of turbine blades of aero-engine

Abstract

The invention provides an integrated optical circuit device for monitoring the temperature of turbine blades of an aero-engine. An integrated optical circuit system is used for measuring the surface temperature of turbine blades, and comprises a three-band temperature measurement optical path, a gas spectrum analyzing optical path, a data acquisition and processing system and a master controller. The infrared radiation emitted by a tested blade is divided into two parts after passing through the optical circuit system. The first part is received by a photoelectric detector after entering the three-band temperature measurement optical path, is processed by a filter circuit and an amplifying circuit and then is analyzed by the data acquisition and processing system. The second part of the infrared radiation enters the gas optical spectrum analyzing optical path. The gas absorption peak is analyzed. A switching controller switches optical filter wheels in the temperature measurement optical path. The integrated optical circuit device provides a gas spectrum analysis function, analyzes the gas absorption spectrum, switches the band used for temperature measurement as required, can avoid the gas absorption peak, reduces measurement errors, and switches filter lens according to use occasions, and provides single-band, dual-band, and three-band temperature measurement functions.

Description

technical field [0001] The invention relates to an optical path system, in particular to an optical path system for temperature measurement, more specifically to an optical path system for monitoring the surface temperature of an aeroengine turbine blade. Background technique [0002] With the development of aero-engines in the direction of high thrust-to-weight ratio, high bypass ratio, and high turbine inlet temperature, the power requirements for the engine are increasing. The turbine inlet temperature of the engine has grown from 1477°C for the third-generation engine with a thrust-to-weight ratio of 8.0 to 1704°C for the fourth-generation engine with a thrust-to-weight ratio of 10.0. At present, the temperature of turbine blades that can be monitored by foreign turbine blade temperature measurement products can only reach 1400°C, which cannot meet the temperature monitoring requirements of high thrust-to-weight ratio engines, making it more difficult to measure the temp...

AI Technical Summary

Problems solved by technology

[0004] The main technical problem to be solved by the present invention is to propose an integrated optical path system for temperature monitoring of aeroengine turbine blades

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