Three dimensional thermal analysis of rocket thrust chambers

Naraghi, M H.N.; Armstrong, E S

Title: Three dimensional thermal analysis of rocket thrust chambers

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Abstract

A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant mixture and flow rates, chamber pressure, coolant entrance temperature and pressure, dimensions of the engine, materials and the number of nodes in different parts of the engine. The model allows for temperature variation in three dimensions: axial, radial and circumferential directions and by implementing an iterative scheme, it provides nodal temperature distribution, rates of heat transfer, hot gas and coolant thermal and transport properties.

Authors:: Naraghi, M H.N.; Armstrong, E S

Publication Date:: Wed Jun 01 00:00:00 EDT 1988

Research Org.:: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center

OSTI Identifier:: 5828969

Report Number(s):: N-89-21025; NASA-TM-101973; E-4673; NAS-1.15:101973; CONF-880676-

Resource Type:: Conference

Resource Relation:: Conference: Conference on thermophysics, plasma dynamics and lasers, San Antonio, TX, USA, 27-29 Jun 1988

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING; COMBUSTION CHAMBERS; THERMAL ANALYSIS; NOZZLES; MATHEMATICAL MODELS; HEAT TRANSFER; TEMPERATURE DISTRIBUTION; TEMPERATURE EFFECTS; ENERGY TRANSFER; 420400* - Engineering- Heat Transfer & Fluid Flow; 421000 - Engineering- Combustion Systems

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                    Naraghi, M H.N., and Armstrong, E S. Three dimensional thermal analysis of rocket thrust chambers.  United States: N. p., 1988. 
        Web.

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                    Naraghi, M H.N., & Armstrong, E S. Three dimensional thermal analysis of rocket thrust chambers.  United States.

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                    Naraghi, M H.N., and Armstrong, E S. 1988.  
        "Three dimensional thermal analysis of rocket thrust chambers".  United States.

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@article{osti_5828969,

  title        = {Three dimensional thermal analysis of rocket thrust chambers},

  author       = {Naraghi, M H.N. and Armstrong, E S},

  abstractNote = {A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant mixture and flow rates, chamber pressure, coolant entrance temperature and pressure, dimensions of the engine, materials and the number of nodes in different parts of the engine. The model allows for temperature variation in three dimensions: axial, radial and circumferential directions and by implementing an iterative scheme, it provides nodal temperature distribution, rates of heat transfer, hot gas and coolant thermal and transport properties.},

  doi          = {},

  url          = {https://www.osti.gov/biblio/5828969},
  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Wed Jun 01 00:00:00 EDT 1988},

  month        = {Wed Jun 01 00:00:00 EDT 1988}

}

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