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Computational Study of Compact Ejector-Enhanced Resonant Pulse CombustorsPrevious studies of Ejector-Enhanced Resonant Pulse Combustors considered configurations that were relatively long, making them difficult to incorporate in practical gas turbine engines. In the present study, more compact configurations are analyzed, focusing on the system pressure gain. The study shows that it is possible to reduce the length of both the pulse combustor and ejector components without compromising the device's performance. In fact, it is found that in several of the compact configurations analyzed, the system pressure gain actually increased, reaching pressure gain levels above 5%, significantly higher than those obtained in previous studies. The Rayleigh efficiency, which has been used in the past to characterize the performance of pulse combustors, is computed for several of the Ejector-Enhanced Resonant Pulse Combustor configurations. The Rayleigh efficiency is seen to correlate with both average combustor pressure and system pressure gain for a given configuration, however, it could not be used to compare different configurations.
Document ID
20180005326
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Yungster, Shaye
(Ohio Aerospace Inst. Cleveland, OH, United States)
Paxson, Daniel E.
(NASA Glenn Research Center Cleveland, OH, United States)
Perkins, Hugh D.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 17, 2018
Publication Date
July 7, 2018
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN57291
Meeting Information
Meeting: AIAA Propulsion and Energy Conference
Location: Cincinnati, OH
Country: United States
Start Date: July 7, 2018
End Date: July 13, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNC13BA10B
WBS: WBS 109492.02.03.02.30
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Compact
Computational Study
Pulse Combustors
Ejector-Enhanced
Resonant
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