Carbide-based fuel assembly for thermal propulsion applications
Carbide-based fuel assembly includes outer structural member of ceramic matrix composite material (e.g., SiC—SiC composite), insulation layer of porous refractory ceramic material (e.g., zirconium carbide with open-cell foam structure or fibrous zirconium carbide), and interior structural member of refractory ceramic-graphite composite material (e.g., zirconium carbide-graphite or niobium carbide-graphite). Spacer structures between various layers provide a defined and controlled spacing relationship. A fuel element bundle positioned between support meshes includes a plurality of distributively arranged fuel elements or a solid, unitary fuel element with coolant channels, each having a fuel composition including high assay, low enriched uranium (HALEU). Fuel assemblies are distributively arranged in a moderator block and the upper end of the outer structural member is attached to a metallic inlet tube for hydrogen propellant and the lower end of the outer structural member is interfaced with a support plate, forming a nuclear thermal propulsion reactor.
- Research Organization:
- Idaho National Laboratory (INL), Idaho Falls, ID (United States); BWXT Advanced Technologies LLC, Lynchburg, VA (United States); BWXT Nuclear Energy, Inc., Charlotte, NC (United States)
- Sponsoring Organization:
- USDOE; National Aeronautics and Space Administration (NASA)
- DOE Contract Number:
- AC07-05ID14517; 00212687; 20135; 80MSFC17C0006
- Assignee:
- BWXT Advanced Technologies LLC (Lynchburg, VA); BWXT Nuclear Energy, Inc. (Charlotte, NC)
- Patent Number(s):
- 11,710,578
- Application Number:
- 17/399,881
- OSTI ID:
- 2222015
- Resource Relation:
- Patent File Date: 08/11/2021
- Country of Publication:
- United States
- Language:
- English
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