Performance of a ducted micro-turbojet engine

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Author
Andreou, Loukas.
Date
1999-09Advisor
Hobson, Garth V.
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A turbo-ramjet engine configuration has possible applications in missiles or Uninhabited Aerial Vehicle's (UAV's). In order to study possible configurations, a Sophia J450 turbojet engine was used, with varying shroud configurations, to compare static thrust and specific fuel consumption measured in a test rig. A baseline shroud, which covered the engine, was tested with three ducts lengths aft of the J450's exhaust. Bach duct length was tested with and without the final convergent nozzle. An elliptic intake for the shroud was also manufactured and tested on two of the configurations. Shroud pressures were also recorded to determine the amount of entrainment of secondary flow into the shroud. The short shroud was found to produce the best performance of the three configurations tested.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
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