A multidisciplinary optimization procedure for gas turbine blade design has been developed and demonstrated on a generic blade. Two blade models have been considered. In the first model, only external cooling has been considered. In the second model, the blade is cooled both internally and externally. Shape optimization is performed using geometric parameters associated with film cooling and blade external shape. A quasi-three-dimensional Navier-Stokes solver for turbomachinery flows is used to solve for the flow field external to the blade with appropriate modifications to incorporate the effect of film cooling. The internal coolant flow is assumed to be fully developed and the temperature and heat transfer coefficient at the walls of the coolant passages are specified. The temperature distribution within the blade is evaluated by solving the heat diffusion equation using the finite element method. The multiobjective Kreisselmeier-Steinhauser function approach has been used in conjunction with an approximate analysis technique for optimization. The results obtained using both blade models are compared with reference geometry. Considerable reduction in blade temperatures are achieved in both the models.

Original languageEnglish (US)
Title of host publication7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
StatePublished - 1998
Event7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1998 - St. Louis, United States
Duration: Sep 2 1998Sep 4 1998


Other7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1998
Country/TerritoryUnited States
CitySt. Louis

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering


Dive into the research topics of 'Multidisciplinary optimization of gas turbine blade design'. Together they form a unique fingerprint.

Cite this