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Title: Thermal barrier coating on high temperature industrial gas turbine engines

Technical Report ·
DOI:https://doi.org/10.2172/5274567· OSTI ID:5274567

This study program identified significant benefits from applying thermal barrier coatings to hot section components of high temperature industrial gas turbine engines. The thermal barrier coating used in this study was a yttria-stabilized zirconia material with a NiCrAlY undercoat, and the base engine used to establish improvements was the P and WA FT50A-4 industrial gas turbine engine. The design benefits of thermal barrier coatings include simplified cooling schemes and the use of conventional alloys in the engine hot section. Cooling flow reductions and improved heating rates achieved with thermal barrier coating result in improved performance. Economic benefits include reduced power production costs and reduced fuel consumption. Over the 30,000 hour life of the thermal barrier coated parts, fuel savings equivalent to $5 million are projected and specific power (megawatts/mass of engine airflow) improvements on the order of 13 percent are estimated. A research and evaluation program to develop thermal barrier coating technology is recommended. The program plan culminates in an industrial gas turbine engine demonstration of the potential benefits of thermal barrier coatings.

Research Organization:
United Technologies Corp., South Windsor, Conn. (USA). Power Systems Div.; Pratt and Whitney Aircraft, East Hartford, Conn. (USA)
OSTI ID:
5274567
Report Number(s):
ERDA/NASA-0067/77/1; NASA-CR-135147; PSD-R-109
Country of Publication:
United States
Language:
English