Skip to main content
OSTI.GOVU.S. Department of Energy Office of Scientific and Technical Information
U.S. Department of Energy
Office of Scientific and Technical Information
 

Engine-cycle analysis for a particle-bed reactor nuclear rocket. Final report, May-Jul 90

Technical Report ·
OSTI ID:5484664
This report addresses three candidate engine cycles for a particle bed nuclear rocket; bleed cycle with uncooled carbon - carbon composite nozzle; bleed cycle with regeneratively cooled Aluminum nozzle; expander cycle with regeneratively cooled Aluminum nozzle. The analysis was performed using the SALT System Analysis Language Translator code with the following amendments; particle bed reactor was modeled as a simple heater; a regeneratively cooled nozzle model was added which includes the heating of the coolant due to hot exhaust gases and nuclear heating of nozzle. The conclusion of the analysis were the topping cycle should be pursued for Mars missions and the bleed cycle should be pursued for OTV (Orbital Transfer Vehicle) missions. This study indicates that a regeneratively cooled aluminum nozzle can be sufficiently cooled to allow its use with a PBR rocket engine. This result is based on nozzle heating due to hot exhaust gases at a maximum chamber temperature and nuclear heating effects. The highest temperatures occur at the nozzle throat, where a composite or alloy coating could protect the aluminum. Further investigation of nozzle cooling should include modeling the nozzle with more nodes, and including more accurate dimensions for the nozzle wall thicknesses and coolant flow passages. The study also indicates that an expander cycle with a cooled aluminum nozzle can operate with a high pressure PBR at realistic TPA efficiencies. Further investigation should include the improvements to the regeneratively cooled nozzle model and more accurate performance maps for the TPA components.
Research Organization:
Phillips Lab., Edwards AFB, CA (United States)
OSTI ID:
5484664
Report Number(s):
AD-A-235258/1/XAB; PL-TR--91-3002
Country of Publication:
United States
Language:
English

Similar Records

Carbon-carbon turbopump concept for Space Nuclear Thermal Propulsion
Conference · Tue Jun 01 00:00:00 EDT 1993 · OSTI ID:5817164
High-temperature turbopump assembly for space nuclear thermal propulsion
Conference · Tue Jan 19 23:00:00 EST 1993 · AIP Conference Proceedings (American Institute of Physics); (United States) · OSTI ID:5587958
KINETIC -- a system code for analyzing Nuclear Thermal Propulsion rocket engine transients
Conference · Thu Jul 01 00:00:00 EDT 1993 · OSTI ID:10175257

Related Subjects

21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS
220800* -- Nuclear Reactor Technology-- Propulsion Reactors
ACCURACY
ALLOYS
ALUMINIUM
CARBON
COATINGS
COMPUTER CODES
COOLANTS
COOLING
COOLING SYSTEMS
DIMENSIONS
ELEMENTS
ENERGY SYSTEMS
ENGINES
EXHAUST GASES
FLUIDS
GASEOUS WASTES
GASES
HEATERS
HEATING
HIGH PRESSURE
HIGH TEMPERATURE
MAPS
MATHEMATICAL MODELS
METALS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
NONMETALS
NOZZLES
ORBITS
PROPULSION REACTORS
PROTECTIVE COATINGS
REACTOR COMPONENTS
REACTOR COOLING SYSTEMS
REACTORS
ROCKET ENGINES
S CODES
SPACE VEHICLES
SYSTEMS ANALYSIS
THERMODYNAMIC CYCLES
THICKNESS
TOPPING CYCLES
VEHICLES
VENTS
WALLS
WASTES