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  • 1
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    Heat transfer in rocket combustion chambers (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Complexities of liquid rocket engine heat transfer which involve the injector faceplate and film cooled walls are being investigated by computational analysis. A conjugate heat transfer analysis was used to describe localized heating phenomena associated with particular injector configurations and film coolant flows. These components were analyzed, and the analyses verified when appropriate test data were available. The component analyses are being synthesized into an overall flowfield/heat transfer model. A Navier-Stokes flow solver, the FDNS code, was used to make the analyses. Particular attention was given to the representation of the thermodynamic properties of the fluid streams. Unit flow models of specific coaxial injector elements have been developed and are being used to describe the flame structure near the injector faceplate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Pennsylvania State Univ., NASA Propulsion Engineering Research Center, Volume 2; p 111-114
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Computational analysis of the SSME fuel preburner flow (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computational fluid dynamics model which simulates the steady state operation of the SSME fuel preburner is developed. Specifically, the model will be used to quantify the flow factors which cause local hot spots in the fuel preburner in order to recommend experiments whereby the control of undesirable flow features can be demonstrated. The results of a two year effort to model the preburner are presented. In this effort, investigating the fuel preburner flowfield, the appropriate transport equations were numerically solved for both an axisymmetric and a three-dimensional configuration. Continuum's VAST (Variational Solution of the Transport equations) code, in conjunction with the CM-1000 Engineering Analysis Workstation and the NASA/Ames CYBER 205, was used to perform the required calculations. It is concluded that the preburner operational anomalies are not due to steady state phenomena and must, therefore, be related to transient operational procedures.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-178803 , NAS 1.26:178803 , CI-FR-0084
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    SSME main combustion chamber and nozzle flowfield analysis (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation is presented of the computational fluid dynamics (CFD) tools which would accurately analyze main combustion chamber and nozzle flow. The importance of combustion phenomena and local variations in mixture ratio are fully appreciated; however, the computational aspects of the gas dynamics involved were the sole issues addressed. The CFD analyses made are first compared with conventional nozzle analyses to determine the accuracy for steady flows, and then transient analyses are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-178893 , NAS 1.26:178893 , CI-FR-0085
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Radiation/convection coupling in rocket motor and plume analysis (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for describing radiation/convection coupling to a flow field analysis was developed for rocket motors and plumes. The three commonly used propellant systems (H2/O2, RP-1/O2, and solid propellants) radiate primarily as: molecular emitters, non-scattering small particles (soot), and scattering larger particles (Al2O3), respectively. For the required solution, the divergence of the radiation heat flux was included in the energy equation, and the local, volume averaged intensity was determined by a solution to the radiative transfer equation. A rigorous solution to this problem is intractable, therefore, solution methods which use the ordinary and improved differential approximation were developed. This radiation model was being incorporated into the FDNS code, a Navier-Stokes flowfield solver for multiphase, turbulent combusting flows.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-193288 , NAS 1.26:193288 , SECA-FR-93-10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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