Forced Response Analysis of Compressor Blades under Unsteady Inlet Distortion-Reference-Cited by-同舟云学术

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Forced Response Analysis of Compressor Blades under Unsteady Inlet Distortion

Published:2013-06-22 Issue: Volume: Page:
ISSN:
Container-title:31st AIAA Applied Aerodynamics Conference
language:
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Author:

Zhang Zhang¹,Hou Anping¹,Tuo Wei²,Xia Aiguo²,Zhou Sheng¹

Affiliation:

1. Beihang University

2. Beijing Aeronautical Technology Research Center

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2013-2409

Reference15 articles.

1. Aeroelasticity Research for Turbomachine Applications

2. Aerodynamic Effects on Blade Vibratory Stress Variations

3. Hamed A, Numbers K. "Inlet Distortion Consideration for High Cycle Fatigue in Gas Turbine Engine",AIAA97-36488.

4. Robert M W, Peter S K, James K etal. "Assessing Fan and Compressor Blade HCF Sensitivity to Non-uniformInletFlows",ASMEGT2004-54264.

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1. Experimental study of a controlled variable double-baffle distortion generator engine test rig;Chinese Journal of Aeronautics;2018-09

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