### Abstract

A multidisciplinary optimization procedure, with the integration of aerodynamic and heat transfer criteria, has been developed for the design of gas turbine blades. Two different optimization formulations have been used. In the first formulation, the maximum temperature in the blade section is chosen as the objective function to be minimized. An upper bound constraint is imposed on the blade average temperature and a lower bound constraint is imposed on the blade tangential force coefficient. In the second formulation, the blade average and maximum temperatures are chosen as objective functions. In both formulations, bounds are imposed on the velocity gradients at several points along the surface of the airfoil to eliminate leading edge velocity spikes which deteriorate aerodynamic performance. Shape optimization is performed using the blade external and coolant path geometric parameters as design variables. Aerodynamic analysis is performed using a panel code. Heat transfer analysis is performed using the finite element method. A gradient based procedure in conjunction with an approximate analysis technique is used for optimization. The results obtained using both optimization techniques are compared with a reference geometry. Both techniques yield significant improvements with the multiobjective formulation resulting in slightly superior design.

Original language | English (US) |
---|---|

Pages (from-to) | 21-42 |

Number of pages | 22 |

Journal | Mathematical Problems in Engineering |

Volume | 4 |

Issue number | 1 |

State | Published - 1998 |

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### Keywords

- Aerodynamics
- Heat transfer
- Multidisciplinary
- Optimization
- Turbine blades

### ASJC Scopus subject areas

- Engineering(all)

### Cite this

*Mathematical Problems in Engineering*,

*4*(1), 21-42.

**Shape optimization of turbine blades with the integration of aerodynamics and heat transfer.** / Rajadas, J. N.; Chattopadhyay, A.; Pagaldipti, N.; Zhang, S.

Research output: Contribution to journal › Article

*Mathematical Problems in Engineering*, vol. 4, no. 1, pp. 21-42.

}

TY - JOUR

T1 - Shape optimization of turbine blades with the integration of aerodynamics and heat transfer

AU - Rajadas, J. N.

AU - Chattopadhyay, A.

AU - Pagaldipti, N.

AU - Zhang, S.

PY - 1998

Y1 - 1998

N2 - A multidisciplinary optimization procedure, with the integration of aerodynamic and heat transfer criteria, has been developed for the design of gas turbine blades. Two different optimization formulations have been used. In the first formulation, the maximum temperature in the blade section is chosen as the objective function to be minimized. An upper bound constraint is imposed on the blade average temperature and a lower bound constraint is imposed on the blade tangential force coefficient. In the second formulation, the blade average and maximum temperatures are chosen as objective functions. In both formulations, bounds are imposed on the velocity gradients at several points along the surface of the airfoil to eliminate leading edge velocity spikes which deteriorate aerodynamic performance. Shape optimization is performed using the blade external and coolant path geometric parameters as design variables. Aerodynamic analysis is performed using a panel code. Heat transfer analysis is performed using the finite element method. A gradient based procedure in conjunction with an approximate analysis technique is used for optimization. The results obtained using both optimization techniques are compared with a reference geometry. Both techniques yield significant improvements with the multiobjective formulation resulting in slightly superior design.

AB - A multidisciplinary optimization procedure, with the integration of aerodynamic and heat transfer criteria, has been developed for the design of gas turbine blades. Two different optimization formulations have been used. In the first formulation, the maximum temperature in the blade section is chosen as the objective function to be minimized. An upper bound constraint is imposed on the blade average temperature and a lower bound constraint is imposed on the blade tangential force coefficient. In the second formulation, the blade average and maximum temperatures are chosen as objective functions. In both formulations, bounds are imposed on the velocity gradients at several points along the surface of the airfoil to eliminate leading edge velocity spikes which deteriorate aerodynamic performance. Shape optimization is performed using the blade external and coolant path geometric parameters as design variables. Aerodynamic analysis is performed using a panel code. Heat transfer analysis is performed using the finite element method. A gradient based procedure in conjunction with an approximate analysis technique is used for optimization. The results obtained using both optimization techniques are compared with a reference geometry. Both techniques yield significant improvements with the multiobjective formulation resulting in slightly superior design.

KW - Aerodynamics

KW - Heat transfer

KW - Multidisciplinary

KW - Optimization

KW - Turbine blades

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UR - http://www.scopus.com/inward/citedby.url?scp=0006616656&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:0006616656

VL - 4

SP - 21

EP - 42

JO - Mathematical Problems in Engineering

JF - Mathematical Problems in Engineering

SN - 1024-123X

IS - 1

ER -