Optimisation of a 180° U-shaped bend shape for a turbine blade cooling passage leading to a pressure loss coefficient of approximately 0.6
Author:
Affiliation:
1. Noise Engineering, Rolls-Royce plc, Derby, UK
2. Department of Engineering Science, University of Oxford, UK
3. Pusan National University, Busan, Korea
Abstract
Publisher
SAGE Publications
Subject
Mechanical Engineering,Aerospace Engineering
Link
http://journals.sagepub.com/doi/pdf/10.1177/0954410015611148
Reference15 articles.
1. Optimization of a U-Bend for Minimal Pressure Loss in Internal Cooling Channels—Part I: Numerical Method
2. The computation of flow development through stationary and rotating U-ducts of strong curvature
3. Numerical studies of heat transfer enhancements in laminar separated flows
4. Convective discretization schemes for the turbulence transport equations in flow predictions through sharp u‐bends
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