Continuous adjoint aerodynamic optimization design for multi-stage gas turbine with cooling air
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
Copyright © 2017, Emerald Publishing Limited