Performance of a ducted micro-turbojet engine
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Authors
Andreou, Loukas.
Subjects
Advisors
Hobson, Garth V.
Date of Issue
1999-09
Date
September, 1999
Publisher
Monterey, California: Naval Postgraduate School
Language
en_US
Abstract
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.
Type
Thesis
Description
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NPS Report Number
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Funding
Format
x, 81 p.;28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Approved for public release; distribution is unlimited.
Approved for public release; distribution is unlimited.
Rights
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.