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7.5 atmospheres air-cooled ceramic thermal-barrier coating ceramic-coated and uncoated ceramic-coated vane coated vanes coating on MAR coating thickness conductivities between test contribute significant errors COOLED ENGINE COMPONENTS cooling effectiveness corrected metal temperature correction factor correction technique dimensionless groups engine and test engine conditions engine gas conditions equations 12 error in metal extrapolated to engine gas and coolant Gas turbines engines gas-side hardware heat-transfer coefficient INSULATING CERAMIC COATINGS ity and expense kinematic layer of ceramic Lewis Research Center Mach number maintained between test material thermal conductivity metal temperature distributions metal wall metal-ceramic interface NASA Nusselt number similarity partial derivative Performing Organization Prandtl number pressure of 1980 PROCEDURES TO COOLED reduced temperatures Reynolds number shown in figure similarity-derived test temperature and pressure temperatures at engine test and engine test conditions test data taken test gas temperature thermal performance thermal similarities turbofan typical uncoated turbine vane uncoated vanes vanes of MAR wall temperature parameter