Thermal Load Test Method and Numerical Calculation for Ceramic Matrix Composite Turbine Guide Vane
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Thermal Load Test Method and Numerical Calculation for Ceramic Matrix Composite Turbine Guide Vane Xiuli Shen 1 & Yifei Qiao 1 & Shaojing Dong 1 Longdong Gong 2
1
& Xin Liu &
Received: 15 May 2018 / Accepted: 12 July 2018 # Springer Nature B.V. 2018
Abstract With the improvement of inlet temperature of aero-engine turbine, continuous fiber reinforced ceramic matrix composite (CFCC) has become an important material for turbine guide vane. In this paper, the testing method of steady state thermal load and cyclic thermal load were explored under typical working environment of turbine guide vane. The temperature field was established through the high-frequency induction heating and was measured by thermocouples and an infrared thermometer. The DIC strain gauge was used to measure the strain. This method overcomes the difficulties in the temperature field establishment, temperature and strain measurements of the ceramic matrix composites. The material mapping method has been applied to calculate the macroscopic stress and strain. It has been observed that the maximum strain error was 11.8% compared with the steady state thermal load experiment result. On this basis, the stress and strain of the thermal fatigue load were analyzed. In addition, a fatigue test was carried out on the standard test pieces, which had the same manufacturing process with the turbine vane. The obtained results through this paper show that the life of the vane was more than 8.34 × 106 under the thermal fatigue load. The experimental and numerical calculation methods proposed in this study provide the experimental and theoretical basis for further research. Keywords Continuous fiber reinforcedceramic matrix composite (CFCC) . Turbine guidevane . Thermal load . Thermal fatigue . Material mapping method
* Shaojing Dong [email protected]
1
School of Energy and Power Engineering, Beihang University, Beijing 100191, China
2
Navigation and Control Technology Research Institute of China Ordnance Industries, Beijing 100089, China
Appl Compos Mater
1 Introduction With the improvement in the thrust-weight ratio of aero-engine, there is an increase in the inlet temperature of turbine. Where, for a thrust-weight ratio of 12~15, the inlet temperature of turbine is designed to be in the range of 1802~2002 °C, whereas for a thrust-weight ratio of 15~20, the inlet temperature of turbine reaches 1977~2077 °C [1]. Considering blade cooling and thermal barrier coating, high-pressure turbine guide vanes need to resist temperatures exceeding 1300 °C [2]. The SiCf/SiC continuous fiber reinforced ceramic matrix composites (CFCC) possess a lower density, demonstrating a higher resistance to temperature (can be used for long periods of time at a temperature as high as 1252 °C [3]), and a lower thermal expansion. Besides providing a higher efficiency, CFCC components could reduce the emission of pollution. A gas turbine when it is redesigned based on the CFCC components will reduce the fuel consumption up to 13%, and 75% of NOx, CO and UHC emissions [4]. As a re
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