Vapor core nuclear reactor rocker engine for space propulsion

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

Vapor core nuclear reactor rocker engine for space propulsion

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

Radiation Oncology

Research output: Chapter in Book/Report/Conference proceeding › Conference 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 language	English (US)
Title of host publication	Proceedings of the Intersociety Energy Conversion Engineering Conference
Publisher	Publ by SAE
Pages	605-610
Number of pages	6
ISBN (Print)	0780313887
State	Published - 1993
Event	Proceedings of the 28th Intersociety Energy Conversion Engineering Conference - Atlanta, GA, USA Duration: Aug 8 1993 → Aug 13 1993

Publication series

Name	Proceedings of the Intersociety Energy Conversion Engineering Conference
Volume	1
ISSN (Print)	0146-955X

Other

Other	Proceedings of the 28th Intersociety Energy Conversion Engineering Conference
City	Atlanta, GA, USA
Period	8/8/93 → 8/13/93

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This output contributes to the following UN Sustainable Development Goals (SDGs)

SDG 7 Affordable and Clean Energy

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Vapor core nuclear reactor rocker engine for space propulsion. / Dugan, Edward T.; Watanabe, Yoichi; Kuras, Stephen et al.
Proceedings of the Intersociety Energy Conversion Engineering Conference. Publ by SAE, 1993. p. 605-610 (Proceedings of the Intersociety Energy Conversion Engineering Conference; Vol. 1).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Dugan, ET, Watanabe, Y, Kuras, S, Diaz, NJ & McClanahan, JA 1993, Vapor core nuclear reactor rocker engine for space propulsion. in Proceedings of the Intersociety Energy Conversion Engineering Conference. Proceedings of the Intersociety Energy Conversion Engineering Conference, vol. 1, Publ by SAE, pp. 605-610, Proceedings of the 28th Intersociety Energy Conversion Engineering Conference, Atlanta, GA, USA, 8/8/93.

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title = "Vapor core nuclear reactor rocker engine for space propulsion",

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.",

author = "Dugan, \{Edward T.\} and Yoichi Watanabe and Stephen Kuras and Diaz, \{Nils J.\} and McClanahan, \{James A.\}",

year = "1993",

language = "English (US)",

isbn = "0780313887",

series = "Proceedings of the Intersociety Energy Conversion Engineering Conference",

publisher = "Publ by SAE",

pages = "605--610",

booktitle = "Proceedings of the Intersociety Energy Conversion Engineering Conference",

note = "Proceedings of the 28th Intersociety Energy Conversion Engineering Conference ; Conference date: 08-08-1993 Through 13-08-1993",

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TY - GEN

T1 - Vapor core nuclear reactor rocker engine for space propulsion

AU - Dugan, Edward T.

AU - Watanabe, Yoichi

AU - Kuras, Stephen

AU - Diaz, Nils J.

AU - McClanahan, James A.

PY - 1993

Y1 - 1993

N2 - 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.

AB - 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.

UR - https://www.scopus.com/pages/publications/0027885745

UR - https://www.scopus.com/pages/publications/0027885745#tab=citedBy

M3 - Conference contribution

AN - SCOPUS:0027885745

SN - 0780313887

T3 - Proceedings of the Intersociety Energy Conversion Engineering Conference

SP - 605

EP - 610

BT - Proceedings of the Intersociety Energy Conversion Engineering Conference

PB - Publ by SAE

T2 - Proceedings of the 28th Intersociety Energy Conversion Engineering Conference

Y2 - 8 August 1993 through 13 August 1993

ER -

Vapor core nuclear reactor rocker engine for space propulsion

Abstract

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