EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE

Qiao Wenxiao; Xiong Changbing

Volume 5 Issue 3

Jul. 1990

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Qiao Wenxiao, Xiong Changbing. EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE[J]. Journal of Aerospace Power, 1990, 5(3): 227-228,285.

Citation:

Qiao Wenxiao, Xiong Changbing. EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE[J]. Journal of Aerospace Power, 1990, 5(3): 227-228,285.

Qiao Wenxiao, Xiong Changbing. EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE[J]. Journal of Aerospace Power, 1990, 5(3): 227-228,285.

Citation:

Qiao Wenxiao, Xiong Changbing. EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE[J]. Journal of Aerospace Power, 1990, 5(3): 227-228,285.

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EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE

Qiao Wenxiao¹,
Xiong Changbing²

1.
China Flight Test Establishment
2.
Beijing University of Aeronautics and Astronautics

Received Date: 1989-10-01
Publish Date: 1990-07-28

Abstract

Abstract

A method to determine the size of notch on first stage blade of compressor with a stress concentrated factor (K t) of three is briefly introduced,which is required for foreign object damage (FOD)testing of aeroengines.It is based on 8-node and 20-node finite element appoaches respectively.The 8-node super-parameter element approach is used to calculate the stress distribution of a whole blade without and with notch,and the 20-node 3D iso-parameter finite element programm is applied to computation of local stress distribution around a notch of blade.The practical testing techniques and test results are also presented.