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Measurement of Heat Flux and Pressure in a Turbine Stage 81GT88
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analysis angle application approximately ASME assumed axial blade boundary layer calculated cascade coefficient combustor component compressor computed configuration constant cooling cycle determined developed direction distribution downstream edge effect efficiency emissions energy engine equation equivalence exit experimental factor Figure flow fluid fuel function gas turbine given heat higher included increase indicated inlet intensity limit load locations loss Mach mass maximum mean measured mechanical method mode normal nozzle obtained operating particle passage percent performance predicted presented pressure primary Products radial range ratio reduced reference region relative rotating rotor secondary separation shock shown in Fig shows side solution speed stage stator steam stress suction surface Table temperature thermal thickness trailing transfer turbulence variation velocity wake wall zone