Heat transfer prediction on transonic turbine blades |
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| Institution: | 1. National Key Laboratory of Science and Technology on Aero-Engine & Aero-Thermodynamics, Beihang University, Beijing 100191, China;2. Department of Aircraft Airworthiness Certification, Civil Aviation Management Institute of China, Beijing 100102, China,;1. School of Materials Science and Engineering, Changwon National University, Changwon, Gyeongnam 51140, Republic of Korea;2. High Temperature Materials Research Group, Korea Institute of Materials Science, Changwon, Gyeongnam 51140, Republic of Korea;3. School of Materials and Metallurgy, University of Science and Technology Liaoning, No. 185 High-Tech District, Anshan, Liaoning 114051, China;4. Department of Mechanical and Energy Engineering, Indiana University-Purdue University Indianapolis, Indianapolis, IN 46202, USA;1. Center for Advanced Turbomachinery and Energy Research, University of Central Florida, Orlando, FL 32816, USA;2. Florida Center for Advanced Aero-Propulsion, Florida State University, Tallahassee, FL 32310, USA;3. National Aerospace Laboratories, Council of Scientific and Industrial Research, Bangalore 560017, India |
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| Abstract: | The design and optimization of turbine blades submitted to high-temperature flows require the prediction of aerodynamic and thermal flow characteristics. A computation method for aerothermal viscous flows has been developed. The method is based on a compressible boundary layer approach. Tests were performed on turbine blade configurations. These tests include most difficulties that can be encountered in reality: laminar-turbulent transition, separation bubbles, strong accelerations, shock waves. Predictions of the wall heat transfer prove to be satisfactory. |
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