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Thrust Augmentation Measurements for a Pulse Detonation Engine Driven EjectorThrust augmentation results of an ongoing study of pulse detonation engine driven ejectors are presented and discussed. The experiments were conducted using a pulse detonation engine (PDE) setup with various ejector configurations. The PDE used in these experiments utilizes ethylene (C2H4) as the fuel, and an equi-molar mixture of oxygen and nitrogen as the oxidizer at an equivalence ratio of one. High fidelity thrust measurements were made using an integrated spring damper system. The baseline thrust of the PDE engine was first measured and agrees with experimental and modeling results found in the literature. Thrust augmentation measurements were then made for constant diameter ejectors. The parameter space for the study included ejector length, PDE tube exit to ejector tube inlet overlap distance, and straight versus rounded ejector inlets. The relationship between the thrust augmentation results and various physical phenomena is described. To further understand the flow dynamics, shadow graph images of the exiting shock wave front from the PDE were also made. For the studied parameter space, the results showed a maximum augmentation of 40%. Further increase in augmentation is possible if the geometry of the ejector is tailored, a topic currently studied by numerous groups in the field.
Document ID
20050239570
Acquisition Source
Headquarters
Document Type
Other
Authors
Pal, S.
(Pennsylvania State Univ. University Park, PA, United States)
Santoro, Robert J.
(Pennsylvania State Univ. University Park, PA, United States)
Shehadeh, R.
Saretto, S.
Lee, S.-Y.
Date Acquired
August 23, 2013
Publication Date
November 1, 2005
Publication Information
Publication: Appendix A. Publications and Presentation Abstracts
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2004-3398
Meeting Information
Meeting: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Fort Lauderdale, FL
Country: United States
Start Date: July 11, 2004
End Date: July 14, 2004
Sponsors: American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers, Society of Automotive Engineers, Inc., American Society for Electrical Engineers
Funding Number(s)
CONTRACT_GRANT: NAG3-2657
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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