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A turbojet simulator for Mach numbers up to 2.0.A turbojet simulator has been designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and temperature. Overall aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
Document ID
19720041998
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Steffen, F. W.
Satmary, E. A.
Vanco, M. R.
Nosek, S. M. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 6, 2013
Publication Date
March 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
ASME PAPER 72-GT-89
Report Number: ASME PAPER 72-GT-89
Meeting Information
Meeting: American Society of Mechanical Engineers, Gas Turbine and Fluids Engineering Conference and Products Show
Location: San Francisco, CA
Start Date: March 26, 1972
End Date: March 30, 1972
Sponsors: American Society of Mechanical Engineers
Accession Number
72A25664
Distribution Limits
Public
Copyright
Other

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