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Combustion and Performance Analyses of Coaxial Element Injectors with Liquid Oxygen/Liquid Methane PropellantsLiquid rocket engines using oxygen and methane propellants are being considered by the National Aeronautics and Space Administration (NASA) for in-space vehicles. This propellant combination has not been previously used in a flight-qualified engine system, so limited test data and analysis results are available at this stage of early development. NASA has funded several hardware-oriented activities with oxygen and methane propellants over the past several years with the Propulsion and Cryogenic Advanced Development (PCAD) project, under the Exploration Technology Development Program. As part of this effort, the NASA Marshall Space Flight Center has conducted combustion, performance, and combustion stability analyses of several of the configurations. This paper summarizes the analyses of combustion and performance as a follow-up to a paper published in the 2008 JANNAF/LPS meeting. Combustion stability analyses are presented in a separate paper. The current paper includes test and analysis results of coaxial element injectors using liquid oxygen and liquid methane or gaseous methane propellants. Several thrust chamber configurations have been modeled, including thrust chambers with multi-element swirl coax element injectors tested at the NASA MSFC, and a uni-element chamber with shear and swirl coax injectors tested at The Pennsylvania State University. Configurations were modeled with two one-dimensional liquid rocket combustion analysis codes, the Rocket Combustor Interaction Design and Analysis (ROCCID), and the Coaxial Injector Combustion Model (CICM). Significant effort was applied to show how these codes can be used to model combustion and performance with oxygen/methane propellants a priori, and what anchoring or calibrating features need to be applied or developed in the future. This paper describes the test hardware configurations, presents the results of all the analyses, and compares the results from the two analytical methods
Document ID
20100021994
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Hulka, J. R.
(Jacobs Technologies Engineering Science Contract Group Houston, TX, United States)
Jones, G. W.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 24, 2013
Publication Date
May 3, 2010
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
M10-0077
Meeting Information
Meeting: 57th JANNAF Propulsion Meeting (JPM)
Location: Colorado Springs, CO
Country: United States
Start Date: May 3, 2010
End Date: May 7, 2010
Sponsors: Department of the Air Force, Department of the Navy, NASA Headquarters, Department of the Army
Funding Number(s)
CONTRACT_GRANT: NNM05AB50C
Distribution Limits
Public
Copyright
Other

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