AN ANALYSIS OF NUCLEAR-ROCKET NOZZLE COOLING
Technical Report
·
OSTI ID:4071412
A rocket regenerative-cooling analysis was conducted over a range of reacter power of 46 to 1600 Mw. Although the propellant (hydrogen) is characterized by a large heatsink capacity, an analysis of the local heat-flux capability of the coolant at the nozzle throat indicated that, for conventional values of system pressure drop and limiting wall temperature, the cooling capability was inadequate. Several techniques for improving the cooling margin were discussed, e.g., high pressure drop, high wall temperature, refractory wall coatings, thin highly conductive walls, and film cooling. (auth)
- Research Organization:
- National Aeronautics and Space Administration. Lewis Research Center, Cleveland
- NSA Number:
- NSA-15-005149
- OSTI ID:
- 4071412
- Report Number(s):
- NASA-TN-D-482
- Country of Publication:
- United States
- Language:
- English
Similar Records
ANALYSIS, FEASIBILITY, AND WALL-TEMPERATURE DISTRIBUTION OF A RADIATION- COOLED NUCLEAR-ROCKET NOZZLE
Engine-cycle analysis for a particle-bed reactor nuclear rocket. Final report, May-Jul 90
Numerical study of nozzle wall cooling for nuclear thermal rockets
Technical Report
·
Sun Dec 31 23:00:00 EST 1961
·
OSTI ID:4804708
Engine-cycle analysis for a particle-bed reactor nuclear rocket. Final report, May-Jul 90
Technical Report
·
Thu Feb 28 23:00:00 EST 1991
·
OSTI ID:5484664
Numerical study of nozzle wall cooling for nuclear thermal rockets
Conference
·
Tue Jun 01 00:00:00 EDT 1993
·
OSTI ID:5898965