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Advanced aircraft engine materials trendsRecent activities of the Lewis Research Center are reviewed which are directed toward developing materials for rotating hot section components for aircraft gas turbines. Turbine blade materials activities are directed at increasing metal temperatures approximately 100 C compared to current directionally solidified alloys by use of oxide dispersion strengthening or tungsten alloy wire reinforcement of nickel or iron base superalloys. The application of thermal barrier coatings offers a promise of increasing gas temperatures an additional 100 C with current cooling technology. For turbine disk alloys, activities are directed toward reducing the cost of turbine disks by 50 percent through near net shape fabrication of prealloyed powders as well as towards improved performance. In addition, advanced alloy concepts and fabrication methods for dual alloy disks are being studied as having potential for improving the life of future high performance disks and reducing the amount of strategic materials required in these components.
Document ID
19810018721
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dreshfield, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Gray, H. R. (NASA Lewis Research Center Cleveland, OH, United States)
Levine, S. R. (NASA Lewis Research Center Cleveland, OH, United States)
Signorelli, R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Metallic Materials
Report/Patent Number
NASA-TM-82626
E-879
Meeting Information
Meeting: Ann. Intern. Gas Turbine Conf.
Location: Houston, TX
Country: United States
Start Date: March 8, 1981
End Date: March 12, 1981
Sponsors: ASME
Accession Number
81N27259
Funding Number(s)
PROJECT: RTOP 505-33-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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