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An experimental investigation of high-aspect-ratio cooling passagesAn experimental investigation was conducted to evaluate the effectiveness of using high-aspect-ratio cooling passenges to improve the life and reduce the colant pressure drop in high-pressure rocket thrust chambers. A plug-nozzle rocket-engine test apparatus was used to test two cylindrical chambers with low-aspect-ratio cooling passages and one with high-aspect-ratio cooling passages. The chambers were cyclically tested and data were taken over a wide range of coolant mass flows. The results showed that for the same coolant pressure drop, the hot-gas-side wall temperature of the high-aspect-ratio chamber was 30 percent lower than the baseline low-aspect-ratio chamber, resulting in no fatigue damage to the wall. The coolant pressure drop for the high-aspect-ratio chamber was reduced in increments to one-half that of the baseline chamber, by reducing the coolant mass flow, and still resulted in a reduction in the hot-gas-side wall temperature when compared to the low-aspect-ratio chambers.
Document ID
19920016715
Document Type
Conference Paper
Authors
Carlile, Julie A.
(NASA Lewis Research Center Cleveland, OH, United States)
Quentmeyer, Richard J.
(Sverdrup Technology, Inc., Brook Park OH., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 92-3154
NASA-TM-105679
NAS 1.15:105679
E-6991
Meeting Information
Meeting: Joint Propulsion Conference
Location: Nashville, TN
Country: United States
Start Date: July 6, 1992
End Date: July 8, 1992
Sponsors: SAE, ASME, ASEE, AIAA
Accession Number
92N25958
Funding Number(s)
PROJECT: RTOP 590-21-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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