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Cooling of gas turbines IX : cooling effects from use of ceramic coatings on water-cooled turbine bladesThe hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the trailing part of such narrow blades, a theoretical study has been made of the cooling effect of a ceramic coating on: (1) the blade-metal temperature when the gas temperature is unchanged, and (2) the gas temperature when the metal temperature is unchanged. Comparison is also made between the changes in the blade or gas temperatures produced by ceramic coatings and the changes produced by moving the cooling passages nearer the trailing edge. This comparison was made to provide a standard for evaluating the gains obtainable with ceramic coatings as compared to those obtainable by constructing the turbine blade in such a manner that water passages could be located very near the trailing edge.
Document ID
19930093970
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Brown, W Byron
Livingood, John N B
Date Acquired
August 16, 2013
Publication Date
October 13, 1948
Report/Patent Number
NACA-RM-E8H03
Accession Number
93R23296
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
HEAT TRANSMISSION - METALS
TURBINES, GAS - COOLING
METALS - TEMPERATURES, HIGH
TURBINES - BLADES - TEMPERATURE
TURBINES - BLADES, TRAILING EDGE
TURBINES - BLADES - COOLING
PROTECTIVE COATINGS, CERAMIC

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