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Modeling of SSME Fuel Preburner ASIThe Augmented Spark Ignitor (ASI) is a LOX/H2/electrical spark system that functions as an ignition source and sustainer for stable combustion. It is used in the SSME preburner combustor, the SSME main combustion chamber, the J-1 and J-2 engines as well as proposed designs of the Space Transportation Main Engine (STME) main combustor and gas generators. In the SSME it is a long circular cylindrical chamber located along the Main Combustor centerline with a truncated conical dome at the top, which contains two oblique LOX injection ports and two spark plugs offset at 90 degrees. Hydrogen injection is through a number of nearly tangential slots downstream which creates a swirl flow intended to cool the AS1 chamber walls. Past incidents of erosion of the AS1 spark plugs have often led to the need for replacement of these very costly devices. Thus it is desirable to understand the complex reactive flow field within the AS1 both during the initial ignition transient and during the main stage steady state combustion (no sparking).
Document ID
19920023015
Acquisition Source
Marshall Space Flight Center
Document Type
Contribution to a larger work
Authors
P Y Liang
(Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Publication Information
Publication: Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 2
Publisher: National Aeronautics and Space Administration
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion
Location: Huntsville, AL
Country: US
Start Date: April 28, 1992
End Date: April 30, 1992
Sponsors: Marshall Space Flight Center
Accession Number
92N32259
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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