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International Symposium on Heat Transfer in Turbomachinery
August, 24-28, 1992 , Marathon, Greece

DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb


ISBN Print: 1-56700-016-9

ISBN Print: 978-1-56700-016-0

Determination of the Proper Number, Locations, Sizes and Shapes of Superelliptic Coolant Flow Passages in Turbine Blades

pages 31-42
DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb.30
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ABSTRACT

During the past several years we have developed an inverse design method that allows a thermal cooling system designer to determine the minimum proper number, and correct sizes, shapes, and locations of coolant passages (holes) in an internally cooled configuration. The methodology has been successfuly demonstrated on two-dimensional coated and non-coated turbine blade airfoils, scram jet combustor struts, etc. Using this method the designer can enforce the desired temperature and the desired heat flux distribution on the hot outer surface of the blade, while simultaneously enforcing the desired temperature distributions on the cooled interior surfaces of each of the coolant passages by automatically relocating, resizing, reshaping and reorienting the initially guessed holes. Hole shapes were allowed to vary according to an inclined Lame family of shapes. The designer only needs to guess the number, sizes, shapes, locations and orientations of the holes. Afterwards, the design process does not require any intervention on the part of the designer since it uses an automatic constrained optimization algorithm to minimize the difference between the specified and intermittently computed outer hot surface heat fluxes. Local minimas in the optimization process were successfully avoided by changing the formulation for the objective function whenever the local minimas were detected. All unnecessary holes were automatically eliminated, while honoring the specified minimal distances between the neighboring holes.

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