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

Continuous adjoint aerodynamic optimization design for multi-stage gas turbine with cooling air PurposeThis 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/approachContinuous adjoint method is combined with the S2 surface code.FindingsThe 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 implicationsThe aerodynamic performance of the gas turbine can be improved via the optimization of blade and passage based on the adjoint method.Originality/valueThe results of the first study on the adjoint method applied to the S2 surface through flow calculation including the cooling air effect are presented. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology: An International Journal Emerald Publishing

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

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
1748-8842
DOI
10.1108/AEAT-05-2014-0058
Publisher site
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Abstract

PurposeThis 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/approachContinuous adjoint method is combined with the S2 surface code.FindingsThe 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 implicationsThe aerodynamic performance of the gas turbine can be improved via the optimization of blade and passage based on the adjoint method.Originality/valueThe results of the first study on the adjoint method applied to the S2 surface through flow calculation including the cooling air effect are presented.

Journal

Aircraft Engineering and Aerospace Technology: An International Journal – Emerald Publishing

Published: May 2, 2017

References

  • 3D simulation of wind turbine rotors at full scale. part I: geometry modeling and aerodynamics
  • Numerical optimization of compressor blade profile based on the control theory
  • Algorithm developments for discrete adjoint methods
  • An introduction to the adjoint approach to design flow
  • Genetic algorithm-based platform optimization for floating offshore wind turbines
  • Finite difference formulations
  • Aerodynamic design via control theory
  • Optimum aerodynamic design using CFD and control theory
  • Aerodynamic shape optimization of complex aircraft configurations via an adjoint formulation
  • Re-engineering the design process through computation
  • Aerodynamic shape optimization using the adjoint method
  • Multi-stage turbomachinery blades optimization design using adjoint method and thin shear-layer N-S equation
  • Aerodynamic design of turbine blades by using adjoint-based method and N-S equation
  • Inverse problem in aerodynamic shape design of turbomachinery blades
  • Turbine blade row optimization through endwall contouring by an adjoint method
  • Secondary flow reduction by blade redesign and endwall contouring using an adjoint optimization method