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Materials and structural aspects of advanced gas-turbine helicopter enginesAdvances in materials, coatings, turbine cooling technology, structural and design concepts, and component-life prediction of helicopter gas-turbine-engine components are presented. Stationary parts including the inlet particle separator, the front frame, rotor tip seals, vanes and combustors and rotating components - compressor blades, disks, and turbine blades - are discussed. Advanced composite materials are considered for the front frame and compressor blades, prealloyed powder superalloys will increase strength and reduce costs of disks, the oxide dispersion strengthened alloys will have 100C higher use temperature in combustors and vanes than conventional superalloys, ceramics will provide the highest use temperature of 1400C for stator vanes and 1370C for turbine blades, and directionally solidified eutectics will afford up to 50C temperature advantage at turbine blade operating conditions. Coatings for surface protection at higher surface temperatures and design trends in turbine cooling technology are discussed. New analytical methods of life prediction such as strain gage partitioning for high temperature prediction, fatigue life, computerized prediction of oxidation resistance, and advanced techniques for estimating coating life are described.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Freche, J. C.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Acurio, J.
(U.S. Army, Propulsion Laboratory, Cleveland Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1979
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: Association Aeronautique et Astronautique de France, International Congress in Aeronautics
Location: Paris
Country: France
Start Date: June 6, 1979
End Date: June 8, 1979
Sponsors: Association Aeronautique et Astronautique de France
Accession Number
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