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Aero-Thermo-Structural Design Optimization of Internally Cooled Turbine BladesA set of robust and computationally affordable inverse shape design and automatic constrained optimization tools have been developed for the improved performance of internally cooled gas turbine blades. The design methods are applicable to the aerodynamics, heat transfer, and thermoelasticity aspects of the turbine blade. Maximum use of the existing proven disciplinary analysis codes is possible with this design approach. Preliminary computational results demonstrate possibilities to design blades with minimized total pressure loss and maximized aerodynamic loading. At the same time, these blades are capable of sustaining significantly higher inlet hot gas temperatures while requiring remarkably lower coolant mass flow rates. These results suggest that it is possible to design internally cooled turbine blades that will cost less to manufacture, will have longer life span, and will perform as good, if not better than, film cooled turbine blades.
Document ID
20000020821
Document Type
Conference Paper
Authors
Dulikravich, G. S. (Pennsylvania State Univ. University Park, PA United States)
Martin, T. J. (Pennsylvania State Univ. University Park, PA United States)
Dennis, B. H. (Pennsylvania State Univ. University Park, PA United States)
Lee, E. (Pennsylvania State Univ. University Park, PA United States)
Han, Z.-X. (Pennsylvania State Univ. University Park, PA United States)
Date Acquired
August 19, 2013
Publication Date
February 1, 1999
Publication Information
Publication: Design Principles and Methods for Aircraft Gas Turbine Engines
Subject Category
Aircraft Propulsion and Power
Funding Number(s)
CONTRACT_GRANT: NAG3-1995
CONTRACT_GRANT: NSF DMI-95-22854
Distribution Limits
Public
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