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Time Averaged Pressure Measurement in Fundamentally Unsteady Pressure Gain Combustion SystemsExperimental results and analysis are presented on a technique for obtaining time averaged pressure in the harsh and highly unsteady environment of a pressure gain combustor. The technique utilizes a long, narrow, stand-off tube leading from the measurement point to a pressure transducer. The tube damps the fluctuations (which may result from strong shocks and/or detonations) and thermally isolates the transducer. The damping must be sufficient to ensure that net gasdynamic work exchange does not occur on the fluid in the stand-off tube, and it must be linear to insure that the time-averaged pressure at the transducer end is the same as that at the combustor end. The paper presents experimental and analytical results from two rigs which indicate that, using certain stand-off tube dimensions, these criteria are met. Physical rational for the tube dimensions (i.e., guidelines) are also presented.
Document ID
20220007415
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Daniel E Paxson
(Glenn Research Center Cleveland, Ohio, United States)
John L Hoke
(Innovative Scientific Solutions Inc. )
Date Acquired
May 12, 2022
Publication Date
January 1, 2013
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-20044
NASA/TM-2013-217826
Meeting Information
Meeting: 45th Combustion/33rd Airbreathing Propulsion/33rd Exhaust Plume and Signatures/27th Propulsion Hazards Joint Subcommittee Meeting
Location: Monterey, CA
Country: US
Start Date: December 3, 2012
End Date: December 7, 2012
Sponsors: United States Department of the Army, United States Department of the Air Force, United States Department of the Navy, National Aeronautics and Space Administration
Funding Number(s)
WBS: 109492.02.03.05.04
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Technical Review
NASA Peer Committee
Keywords
detonation
combustion
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