Development of CFD Approaches for Modeling Advanced Concepts of Nuclear Thermal Propulsion Test Facilities

Metadata Updated: November 12, 2020

The current project is going to investigate, implement and begin validating the Computational Fluid Dynamics (CFD) options available for modeling multi-phase reactive flows in a fully coupled multi-physics framework to use in designing and supporting Nuclear Thermal Propulsion (NTP) Test ground test facilities.  NTP is an advanced propulsion alternative to conventional chemical rockets with relatively high thrust and twice the efficiency of the Space Shuttle Main Engine.  Ground testing facilities can validate thrust and efficiencies from testing if capturing and treating the nuclear exhaust satisfy current safety, health and environmental regulations.  A fully-coupled, multi-physics, CFD analysis approach will be required to design such a NTP ground test facility system.  The multi-physics approach will require simultaneous simulations of processes such as transient real-gas hydrogen flow through a supersonic diffuser, Liquid Oxygen/Gaseous Hydrogen (LO2/GH2) combustion at high speeds, and multi-phase condensation and evaporation of water sprays in a reacting flow environment. However, multiphase reactive CFD simulations are not simplistic or straightforward to obtain. In addition, fully coupling these flow simulations with transient thermal analysis of heat exchangers and thermal protection systems significantly increases the complexity. By developing this CFD analysis approach, a better understanding of requirements for NTP ground testing facilities can be better achieved. The project will be developing a CFD approach that can handle the additional complexities needed in a NTP testing facility when modeling the combustion processes in a transient environment for fluid flows that will extend from low subsonic to supersonic during a typical NTP ground test sequence.   Complex combustion processes will eventually need to be modeled in conjunction with down-stream effluent cooling systems such as water sprays and heat exchangers.  The simulation of water spray injection in a transient, time-accurate fashion will require implementation of robust numerical schemes which sufficiently capture the relevant physics of the water spray evaporation in the high-speed combusting flow.  In addition, the simulation of heat exchanger cooling systems will require fully coupling these multi-phase combustion simulations with a transient thermal analysis in a multi-physics analysis framework.  The successful demonstration of accurately and robustly coupling all these analysis into one simulation environment will be a new achievement for NASA.    

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Public: This dataset is intended for public access and use. License: No license information was provided. If this work was prepared by an officer or employee of the United States government as part of that person's official duties it is considered a U.S. Government Work.

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Metadata Created Date November 12, 2020
Metadata Updated Date November 12, 2020

Metadata Source

Harvested from NASA Data.json

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Resource Type Dataset
Metadata Created Date November 12, 2020
Metadata Updated Date November 12, 2020
Publisher Space Technology Mission Directorate
Unique Identifier Unknown
Maintainer
Identifier TECHPORT_14685
Data First Published 2014-09-01
Data Last Modified 2020-01-29
Public Access Level public
Bureau Code 026:00
Metadata Context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
Metadata Catalog ID https://data.nasa.gov/data.json
Schema Version https://project-open-data.cio.gov/v1.1/schema
Catalog Describedby https://project-open-data.cio.gov/v1.1/schema/catalog.json
Homepage URL https://techport.nasa.gov/view/14685
Program Code 026:027
Source Datajson Identifier True
Source Hash d9d1bc3576b125757ccd387f7d4a445df1b5c01d
Source Schema Version 1.1

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