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타이틀	Thermal Hydraulics Design and Analysis Methodology for a Solid-Core Nuclear Thermal Rocket Engine Thrust Chamber
저자	Wang, Ten-See;; Canabal, Francisco;; Chen, Yen-Sen;; Cheng, Gary;; Ito, Yasushi
Keyword	COMPUTATIONAL FLUID DYNAMICS;; DESIGN ANALYSIS;; ENGINE DESIGN;; HEAT TRANSFER;; NUCLEAR ROCKET ENGINES;; PROPULSION;; THERMAL ANALYSIS;; THERMAL ENVIRONMENTS;; THRUST CHAMBERS;; UNSTRUCTURED GRIDS (MATHEMATICS); WORKING FLUIDS
URL	http://hdl.handle.net/2060/20130001802
보고서번호	M12-1927
발행년도	2013
출처	NTRS (NASA Technical Report Server)
ABSTRACT	Nuclear thermal propulsion is a leading candidate for in-space propulsion for human Mars missions. This chapter describes a thermal hydraulics design and analysis methodology developed at the NASA Marshall Space Flight Center, in support of the nuclear thermal propulsion development effort. The objective of this campaign is to bridge the design methods in the Rover/NERVA era, with a modern computational fluid dynamics and heat transfer methodology, to predict thermal, fluid, and hydrogen environments of a hypothetical solid-core, nuclear thermal engine the Small Engine, designed in the 1960s. The computational methodology is based on an unstructured-grid, pressure-based, all speeds, chemically reacting, computational fluid dynamics and heat transfer platform, while formulations of flow and heat transfer through porous and solid media were implemented to describe those of hydrogen flow channels inside the solid24 core. Design analyses of a single flow element and the entire solid-core thrust chamber of the Small Engine were performed and the results are presented herein