Accession Number:

ADA370851

Title:

Performance of a Ducted Micro-Turbojet Engine

Descriptive Note:

Thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

• Hobson, Garth V.
• Shreeve, Raymond P.

Report Date:

1999-09-01

Pagination or Media Count:

92.0

Abstract:

A turbo-ramjet engine configuration has possible applications in missiles or Uninhabited Aerial Vehicles UAVs. 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 J450s 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.

Descriptors:

• *GAS TURBINE ROTORS
• AIRCRAFT
• TEST EQUIPMENT
• SHORT RANGE(TIME)
• BASE LINES
• LENGTH
• CONFIGURATIONS
• DUCTS
• PRESSURE
• FUEL CONSUMPTION
• CONVERGENCE
• NOZZLES
• COVERINGS
• THRUST
• ENTRAINMENT
• STATIC TESTS
• SECONDARY FLOW

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE