For a gas turbine blade working in a narrow space, the accuracy of blade temperature measurements is greatly impacted by environmental irradiation. A reflection model is established by using discrete irregular surfaces to calculate the angle factor between the blade surface and the hot adjacent parts. The model is based on the rotational angles and positions of the blades, and can correct for measurement error caused by background radiation when the blade is located at different rotational positions. This method reduces the impact of reflected radiation on the basis of the turbine’s known geometry and the physical properties of the material. The experimental results show that when the blade temperature is 911.2±5 K and the vane temperature ranges from 1011.3 to 1065.8 K, the error decreases from 4.21 to 0.75%.
To achieve the highest possible turbine inlet temperature requires to accurately measuring the turbine blade temperature.
If the temperature of blade frequent beyond the design limits, it will seriously reduce the service life. The problem for the
accuracy of the temperature measurement includes the value of the target surface emissivity is unknown and the
emissivity model is variability and the thermal radiation of the high temperature environment. In this paper, the
multi-spectral pyrometer is designed provided mainly for range 500-1000℃, and present a model corrected in terms of
the error due to the reflected radiation only base on the turbine geometry and the physical properties of the material.
Under different working conditions, the method can reduce the measurement error from the reflect radiation of vanes,
make measurement closer to the actual temperature of the blade and calculating the corresponding model through genetic
algorithm. The experiment shows that this method has higher accuracy measurements.
Conference Committee Involvement (1)
Photonic Applications for Aviation, Aerospace, Commercial, and Harsh Environments V
19 August 2014 | San Diego, California, United States