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Bleed Cycle Propellant Pumping in a Gas-Core Nuclear Rocket Engine SystemThe performance of ideal and real staged primary propellant pumps and bleed-powered turbines was calculated for gas-core nuclear rocket engines over a range of operating pressures from 500 to 5000 atm. This study showed that for a required engine operating pressure of 1000 atm the pump work was about 0.8 hp/(lb/sec), the specific impulse penalty resulting from the turbine propellant bleed flow as about 10 percent; and the heat required to preheat the propellant was about 7.8 MW/(lb/sec). For a specific impulse above 2400 sec, there is an excess of energy available in the moderator due to the gamma and neutron heating that occurs there. Possible alternative pumping cycles are the Rankine or Brayton cycles.
Document ID
19720010401
Document Type
Technical Memorandum (TM)
Authors
Kascak, Albert F. (NASA Lewis Research Center Cleveland, OH, United States)
Easley, Annie J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
E-6639
NASA-TM-X-2517
Funding Number(s)
PROJECT: RTOP 112-28
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Gas-core
Pumping
Propellant
Nuclear rocket
Bleed cycle

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NameType 19720010401.pdf STI