Impact of inlet flow angle variation on the performance of a transonic compressor blade using NIPC
Author:
Affiliation:
1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China
2. China Aerodynamics Research and Development Center, Mianyang 621000, China
Funder
National Natural Science Foundation of China
National Science and Technology Major Project of China
Publisher
AIP Publishing
Subject
General Physics and Astronomy
Link
https://aip.scitation.org/doi/pdf/10.1063/5.0074200
Reference28 articles.
1. Performance Deterioration in Industrial Gas Turbines
2. Influences of Manufacturing Tolerances and Surface Roughness of Blades on the Performance of Turbines
3. Impact of Geometric Variability on Axial Compressor Performance
4. Numerical Investigation of the Influence of Real World Blade Profile Variations on the Aerodynamic Performance of Transonic Nozzle Guide Vanes
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