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NASA High Temperature Alloy Development – GRX-810Problem: Conventional materials and processing techniques limit the design of combustor domes used in jet turbine engines.

Proposed Solution: Develop a high ductility, high temperature material for an additively manufactured (AM) combustor fuel nozzle and dome for supersonic aircraft (>1093°C (2000°F) operating temperature).
Document ID
20230009039
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
T Smith ORCID(Glenn Research Center Cleveland, Ohio, United States)
C Kantzos (Glenn Research Center Cleveland, Ohio, United States)
T Gabb (Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
June 14, 2023
Publication Date
June 26, 2023
Subject Category
Metals and Metallic Materials
Meeting Information
Meeting: Turbomachinery Technical Conference & Exposition
Location: Boston, MA
Country: US
Start Date: June 26, 2023
End Date: June 30, 2023
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
WBS: 109492.02.03.09.02.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Peer Committee

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