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Inverse Design of A Proper Number, Shapes, Sizes, and Locations of Coolant Flow PassagesDuring the past several years we have developed an inverse method that allows a thermal cooling system designer to determine proper sizes, shapes, and locations of coolant passages (holes) in, say, an internally cooled turbine blade, a scram jet strut, a rocket chamber wall, etc. Using this method the designer can enforce a desired heat flux distribution on the hot outer surface of the object, while simultaneously enforcing desired temperature distributions on the same hot outer surface as well as on the cooled interior surfaces of each of the coolant passages. This constitutes an over-specified problem which is solved by allowing the number, sizes, locations and shapes of the holes to adjust iteratively until the final internally cooled configuration satisfies the over-specified surface thermal conditions and the governing equation for the steady temperature field. The problem is solved by minimizing an error function expressing the difference between the specified and the computed hot surface heat fluxes. The temperature field analysis was performed using our highly accurate boundary integral element code with linearly varying temperature along straight surface panels. Examples of the inverse design applied to internally cooled turbine blades and scram jet struts (coated and non-coated) having circular and non-circular coolant flow passages will be shown.
Document ID
19920023054
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
George S. Dulikravich
(Pennsylvania State University State College, Pennsylvania, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Publication Information
Subject Category
Fluid Mechanics And Heat Transfer
Meeting Information
Meeting: Proceedings of a workshop held at NASA George C. Marshall Space Flight Center
Location: Huntsville, AL
Country: US
Start Date: April 28, 1992
End Date: April 30, 1992
Sponsors: National Aeronautics and Space Administration
Accession Number
92N32298
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
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