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Continuous adjoint aerodynamic optimization design for multi-stage gas turbine with cooling air

Lei Chen ( Heavy Engineering Research Association , Auckland, New Zealand)
Jiang Chen (School of Energy and Power, Beihang University , Beijing, China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 2 May 2017

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Abstract

Purpose

This paper aims to conduct the optimization of the multi-stage gas turbine with the effect of the cooling air injection based on the adjoint method.

Design/methodology/approach

Continuous adjoint method is combined with the S2 surface code.

Findings

The optimization of the stagger angles, stacking lines and the passage can improve the attack angles and restrain the development of the boundary, reducing the secondary flow loss caused by the cooling air injection.

Practical implications

The aerodynamic performance of the gas turbine can be improved via the optimization of blade and passage based on the adjoint method.

Originality/value

The results of the first study on the adjoint method applied to the S2 surface through flow calculation including the cooling air effect are presented.

Keywords

Acknowledgements

The authors would like to acknowledge the support from the National Natural Science Foundation of China (No.51576007).

Citation

Chen, L. and Chen, J. (2017), "Continuous adjoint aerodynamic optimization design for multi-stage gas turbine with cooling air", Aircraft Engineering and Aerospace Technology, Vol. 89 No. 3, pp. 444-456. https://doi.org/10.1108/AEAT-05-2014-0058

Publisher

:

Emerald Publishing Limited

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