An integrated multidisciplinary design optimization procedure for cooled gas turbine blades
Author:
Affiliation:
1. Arizona State Univ., Tempe
2. Arizona State Univ., Mesa
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2000-1664
Reference54 articles.
1. Wing design code using three-dimensional Euler equations and optimization
2. Film Cooling
3. Weigand, B., and Harasgama, S. P. "Computations of a Film Cooled Turbine Rotor Blade With Non-Uniform Inlet Temperature Distribution Using a Three-Dimensional Viscous Procedure, " ASME 94-GT-15.
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1. A high temperature turbine blade heat transfer multilevel design platform;Numerical Heat Transfer, Part A: Applications;2020-10-28
2. Integrated aerodynamic design and analysis of turbine blades;Advances in Engineering Software;2014-02
3. Application of Design Optimization to Turbomachinery Design;9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization;2002-09-04
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