An integrated optical device for temperature monitoring of aeroengine turbine blades

Abstract

The present invention provides an integrated optical path device for monitoring the temperature of turbine blades of aeroengines. The integrated optical path system is used to measure the surface temperature of turbine blades, including a three-band temperature measurement optical path, a gas spectrum analysis optical path, a data acquisition and processing system and main controller. The infrared radiation emitted by the measured blade is divided into two parts after passing through the optical path system: the first part enters the three-band temperature measurement optical path and is received by the photoelectric detector, and is analyzed by the data acquisition and processing system after being processed by the filter circuit and the amplifier circuit; the second part Infrared radiation enters the optical path of gas spectrum analysis to analyze the absorption peak of gas, and the switching controller switches the switching of the filter wheel in the temperature measurement optical path. This set of inventions can provide gas spectrum analysis function, and according to the absorption spectrum of the analyzed gas, switch the band used for temperature measurement as needed, avoid the absorption peak of the gas, reduce measurement errors, and switch the filter lens according to the application occasion, Provide single-band, dual-band, 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, which solves the problem of large measurement errors caused by the single optical path structure and function used in the current radiation temperature measurement technology

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