Combustor Wall Axial Location Effects on First Vane Leading-Edge Cooling
Author:
Affiliation:
1. Osney Thermofluids Laboratory, Department of Engineering Science, Oxford University, Oxford, England OX2 0DP, United Kingdom
2. The Boston Consulting Group GmbH, 40219 Dusseldorf, Germany
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B35388
Reference43 articles.
1. Effect of Velocity and Temperature Distribution at the Hole Exit on Film Cooling of Turbine Blades
2. Discrete-Jet Film Cooling: A Comparison of Computational Results With Experiments
3. A Detailed Analysis of Film-Cooling Physics: Part I—Streamwise Injection With Cylindrical Holes
4. A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane
5. Numerical simulation and aerothermal physics of leading edge film cooling
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1. Endwall Film Cooling Performance for a First-Stage Guide Vane With Upstream Combustor Walls and Inlet Injection;Journal of Thermal Science and Engineering Applications;2018-10-15
2. Combustor Wall Coolant Discharge Effects on Turbine Vane Endwall Curtain Cooling;Journal of Thermophysics and Heat Transfer;2018-10
3. Aerothermal Performance of Shielded Vane Design;Journal of Turbomachinery;2017-07-19
4. Influence of Discharge from Combustor Walls on Curtain Cooling for a First-Stage Turbine Vane Endwall;53rd AIAA/SAE/ASEE Joint Propulsion Conference;2017-07-07
5. Aerothermal Performance of a Nozzle Vane Cascade With a Generic Nonuniform Inlet Flow Condition—Part II: Influence of Purge and Film Cooling Injection;Journal of Turbomachinery;2017-05-09
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