Test system and method for turbine blade integrated thin film temperature sensor

Abstract

The invention provides a test system and method for a turbine blade integrated thin film temperature sensor, which solves the problem that the existing turbine blade integrated thin film temperature sensor cannot adopt an industrial thermocouple temperature measurement calibration mode. The system comprises a heating box, an instantaneous heating unit, an imaging unit, a standard thermocouple, a check meter and a control unit, wherein the instantaneous heating unit comprises a laser, a condensation unit and a rotary table; the condensation unit is located outside the observation opening in the side wall of the heating box and on an emergent light path of the laser; the condensation unit is arranged on the rotary table; the imaging unit is arranged outside the observation opening of the heating box; the number of the standard thermocouples is equal to that of the thin film temperature sensors on the turbine blade to be measured, and the positions are in one-to-one correspondence; the thin film temperature sensor and the standard thermocouple are respectively connected with the check meter; the control unit controls the emergent energy of the laser and is connected with the rotary table; and the control unit compares the temperatures obtained by the thin film temperature sensor and the standard thermocouple, and judges whether the performance of the thin film temperature sensor is qualified or not.

Description

Technical field

[0001] The present invention relates to a sensor testing, and in particular relates to a test system and method for a turbine blade for integrated thin-film temperature sensor. Background technique

[0002] Aviation engines are complex mechanical work at a high temperature and pressure of the high-speed rotation harsh environment, which requires a high material and manufacturing processes. According to the research, aircraft engines, turbine inlet temperature 100 deg.] C per increase, engine thrust may be increased by 20%, 8% thermal efficiency can be improved. In order to pursue higher performance and more energy economical, modern aircraft engine research that will further improve the main turbine inlet temperature. The turbine blade as a main component for converting thermal energy into mechanical energy, which is a key reliability design new engine design. To improve the reliability of the turbine blade, turbine blade surface measurement and analysis required ...

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