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Model Engine Performance Measurement From Force Balance InstrumentationA large scale model representative of a low-noise, high bypass ratio turbofan engine was tested for acoustics and performance in the NASA Lewis 9- by 15-Foot Low-Speed Wind Tunnel. This test was part of NASA's continuing Advanced Subsonic Technology Noise Reduction Program. The low tip speed fan, nacelle, and an un-powered core passage (with core inlet guide vanes) were simulated. The fan blades and hub are mounted on a rotating thrust and torque balance. The nacelle, bypass duct stators, and core passage are attached to a six component force balance. The two balance forces, when corrected for internal pressure tares, measure the total thrust-minus-drag of the engine simulator. Corrected for scaling and other effects, it is basically the same force that the engine supports would feel, operating at similar conditions. A control volume is shown and discussed, identifying the various force components of the engine simulator thrust and definitions of net thrust. Several wind tunnel runs with nearly the same hardware installed are compared, to identify the repeatability of the measured thrust-minus-drag. Other wind tunnel runs, with hardware changes that affected fan performance, are compared to the baseline configuration, and the thrust and torque effects are shown. Finally, a thrust comparison between the force balance and nozzle gross thrust methods is shown, and both yield very similar results.
Document ID
19980211443
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Jeracki, Robert J. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1998
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 98-3112
NAS 1.15:208486
E-11263
NASA/TM-1998-208486
Meeting Information
Meeting: Propulsion
Location: Cleveland, OH
Country: United States
Start Date: July 12, 1998
End Date: July 15, 1998
Sponsors: Society of Automotive Engineers, Inc., American Society for Electrical Engineers, American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 538-03-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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