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High-temperature, high-pressure optical port for rocket engine applicationsThis paper discusses the design, fabrication, and test of a window assembly for instrumentation of liquid-fueled rocket engine hot gas systems. The window was designed to allow optical measurements of hot gas in the SSME fuel preburner and appears to be the first window designed for application in a rocket engine hot gas system. Such a window could allow the use of a number of remote optical measurement technologies including: Raman temperature and species concentration measurement, Raleigh temperature measurements, flame emission monitoring, flow mapping, laser-induced florescence, and hardware imaging during engine operation. The window assembly has been successfully tested to 8,000 psi at 1000 F and over 11,000 psi at room temperature. A computer stress analysis shows the window will withstand high temperature and cryogenic thermal shock.
Document ID
19930066149
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Delcher, Ray
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Nemeth, ED
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Powers, W. T.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Engineering (General)
Report/Patent Number
AIAA PAPER 93-2377
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: ASME, AIAA, SAE, ASEE
Accession Number
93A50146
Distribution Limits
Public
Copyright
Other

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