Local heat-transfer measurements on a large scale-model turbine blade airfoil using a composite of a heater element and liquid crystals
Local heat-transfer coefficients were experimentally mapped along the midchord of a five-times-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, which change color with temperature, and a heater sheet made of a carbon-impregnated paper, which 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/sup 5/ to 7.6 X 10/sup 5/. Comparisons are made with analytical values of heat-transfer coefficients obtained from the STAN5 boundary layer code. Also, a leading-edge separation bubble was revealed by thermal and flow visualization.
- Research Organization:
- National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH
- OSTI ID:
- 5987610
- Journal Information:
- J. Eng. Gas Turbines Power; (United States), Vol. 107:4
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
42 ENGINEERING
AIRFOILS
HEAT TRANSFER
SURFACES
THERMAL ANALYSIS
TURBINE BLADES
BOUNDARY LAYERS
BUBBLE GROWTH
CARBON
LIQUID CRYSTALS
PAPER
REYNOLDS NUMBER
SHEETS
TEMPERATURE MEASUREMENT
THERMODYNAMICS
CRYSTALS
ELEMENTS
ENERGY TRANSFER
FLUIDS
LAYERS
LIQUIDS
NONMETALS
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420400 - Engineering- Heat Transfer & Fluid Flow