NASA NTRS · 20230009039
NASA High Temperature Alloy Development – GRX-810
Abstract
Problem: 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).
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T Smith, C Kantzos, T Gabb. 2023-06-26. NASA High Temperature Alloy Development – GRX-810. https://ntrs.nasa.gov/citations/20230009039
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