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Aeromechanics Analysis of a Boundary Layer Ingesting FanBoundary layer ingesting propulsion systems have the potential to significantly reduce fuel burn but these systems must overcome the challe nges related to aeromechanics-fan flutter stability and forced response dynamic stresses. High-fidelity computational analysis of the fan a eromechanics is integral to the ongoing effort to design a boundary layer ingesting inlet and fan for fabrication and wind-tunnel test. A t hree-dimensional, time-accurate, Reynolds-averaged Navier Stokes computational fluid dynamics code is used to study aerothermodynamic and a eromechanical behavior of the fan in response to both clean and distorted inflows. The computational aeromechanics analyses performed in th is study show an intermediate design iteration of the fan to be flutter-free at the design conditions analyzed with both clean and distorte d in-flows. Dynamic stresses from forced response have been calculated for the design rotational speed. Additional work is ongoing to expan d the analyses to off-design conditions, and for on-resonance conditions.
Document ID
20130009482
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Bakhle, Milind A.
(NASA Glenn Research Center Cleveland, OH, United States)
Reddy, T. S. R.
(Toledo Univ. Toledo, OH, United States)
Herrick, Gregory P.
(NASA Glenn Research Center Cleveland, OH, United States)
Shabbir, Aamir
(United Technologies Research Center East Hartford, CT, United States)
Florea, Razvan V.
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 27, 2013
Publication Date
January 1, 2013
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-18442
AIAA Paper 2012-3995
NASA/TM-2013-217730
Meeting Information
Meeting: 48th Joint Propulsion Conference and Exhibit
Location: Atlanta, GA
Country: United States
Start Date: July 30, 2012
End Date: August 1, 2012
Sponsors: American Society for Electrical Engineers, Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers
Funding Number(s)
WBS: WBS 561581.02.08.03.47.03.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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