Vapor core nuclear reactor rocker engine for space propulsion

Edward T. Dugan, Yoichi Watanabe, Stephen Kuras, Nils J. Diaz, James A. McClanahan

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Neutronic, thermal hydraulic and thermal mechanical studies have been performed on an innovative vapor core nuclear reactor concept for space for space propulsion. The Nuclear Vapor Thermal Reactor (NVTR) Rocket Engine uses modified-NERVA geometry and systems with the solid fuel replaced by uranium tetrafluoride vapor. The NVTR is an intermediate term gas core thermal rocket engine with specific impulse in the range of 1000-1200 seconds; a thrust of 75,000 lbs for a hydrogen flow rate of 30 kg per second; average core exit temperatures of 3100 °K to 3400 °K; reactor thermal powers of 1400 to 1800 MW; and thrust-to-weight ratios of 5-to-1.

Original languageEnglish (US)
Title of host publicationProceedings of the Intersociety Energy Conversion Engineering Conference
PublisherPubl by SAE
Pages605-610
Number of pages6
ISBN (Print)0780313887
StatePublished - Dec 1 1993
EventProceedings of the 28th Intersociety Energy Conversion Engineering Conference - Atlanta, GA, USA
Duration: Aug 8 1993Aug 13 1993

Publication series

NameProceedings of the Intersociety Energy Conversion Engineering Conference
Volume1
ISSN (Print)0146-955X

Other

OtherProceedings of the 28th Intersociety Energy Conversion Engineering Conference
CityAtlanta, GA, USA
Period8/8/938/13/93

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