NDLI: Status on the verification of combustion stability for the j-2x engine thrust chamber assembly

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Status on the verification of combustion stability for the j-2x engine thrust chamber assembly

Content Provider	NASA Technical Reports Server (NTRS)
Author	Kenny, R. Jeremy Dodd, Fred Casiano, Matthew Hinerman, Tim Barnett, Greg Martin, Tom Hulka, Jim
Copyright Year	2013
Description	Development is underway of the J -2X engine, a liquid oxygen/liquid hydrogen rocket engine for use on the Space Launch System. The Engine E10001 began hot fire testing in June 2011 and testing will continue with subsequent engines. The J -2X engine main combustion chamber contains both acoustic cavities and baffles. These stability aids are intended to dampen the acoustics in the main combustion chamber. Verification of the engine thrust chamber stability is determined primarily by examining experimental data using a dynamic stability rating technique; however, additional requirements were included to guard against any spontaneous instability or rough combustion. Startup and shutdown chug oscillations are also characterized for this engine. This paper details the stability requirements and verification including low and high frequency dynamics, a discussion on sensor selection and sensor port dynamics, and the process developed to assess combustion stability. A status on the stability results is also provided and discussed.
File Size	78689
Page Count	1
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20130014078
Archival Resource Key	ark:/13960/t86h9jt19
Language	English
Publisher Date	2013-04-29
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Liquid Oxygen Dynamic Stability Oscillations Rocket Engines Thrust Chambers Acoustics Hydrogen Oxygen Engines Combustion Chambers Spacecraft Launching Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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