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Local heat-transfer measurements on a large scale-model turbine blade airfoil using a composite of a heater element and liquid crystalsLocal heat transfer coefficients were experimentally mapped along the midchord of a five-time-size turbine blade airfoil in a static cascade operated at room temperature over a range of Reynolds numbers. The test surface consisted of a composite of commercially available materials: a mylar sheet with a layer of cholesteric liquid crystals, that change color with temperature, and a heater sheet made of a carbon-impregnated paper, that produces uniform heat flux. After the initial selection and calibration of the composite sheet, accurate, quantitative, and continuous heat transfer coefficients were mapped over the airfoil surface. The local heat transfer coefficients are presented for Reynolds numbers from 2.8 x 10 to the 5th power to 7.6 x 10 to the 5th power. Comparisons are made with analytical values of heat transfer coefficients obtained from the STANS boundary layer code. Also, a leading edge separation bubble was revealed by thermal and flow visualization.
Document ID
19860028323
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hippensteele, S. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Russell, L. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Torres, F. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1985
Publication Information
Publication: ASME, Transactions, Journal of Engineering for Gas Turbines and Power
Volume: 107
ISSN: 0022-0825
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 85-GT-59
Accession Number
86A13061
Distribution Limits
Public
Copyright
Other

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