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The Aerodynamic Performance of an Over-The-Rotor Liner with Circumferential Grooves on a High Bypass Ratio Turbofan RotorWhile liners have been utilized throughout turbofan ducts to attenuate fan noise, additional attenuation is obtainable by placing an acoustic liner over-the-rotor. Previous experiments have shown significant fan performance losses when acoustic liners are installed over-the-rotor. The fan blades induce an oscillating flow in the acoustic liners which results in a performance loss near the blade tip. An over-the-rotor liner was designed with circumferential grooves between the fan blade tips and the acoustic liner to reduce the oscillating flow in the acoustic liner. An experiment was conducted in the W-8 Single-Stage Axial Compressor Facility at NASA Glenn Research Center on a 1.5 pressure ratio fan to evaluate the impact of this over-the-rotor treatment design on fan aerodynamic performance. The addition of a circumferentially grooved over-the-rotor design between the fan blades and the acoustic liner reduced the performance loss, in terms of fan adiabatic efficiency, to less than 1% which is within the repeatability of this experiment.
Document ID
20150009952
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Bozak, Rick
(NASA Glenn Research Center Cleveland, OH, United States)
Hughes, Christopher
(NASA Glenn Research Center Cleveland, OH, United States)
Buckley, James
(Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
June 5, 2015
Publication Date
June 3, 2013
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-18742-1
GT2013-95114
Meeting Information
Meeting: ASME Turbo Exp 2013
Location: San Antonio, TX
Country: United States
Start Date: June 3, 2013
End Date: June 7, 2013
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
WBS: WBS 699959.02.09.03.06
Distribution Limits
Public
Copyright
Other

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