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Large-Scale Boundary Layer Ingesting Propulsor Research_NASA's Advanced Air Transport Technology (AATT) project is investigating boundary layer ingesting (BLI) propulsors for advanced subsonic commercial vehicle concepts to enable the reduction of fuel burn. A multidisciplinary team of researchers from NASA, United Technologies Research Center (UTRC), Virginia Polytechnic University, and the Air Force Arnold Engineering Development Complex developed and tested an embedded BLI inlet and distortion-tolerant fan (BLI2DTF) system in the NASA Glenn Research Center (GRC) 8-foot by 6-foot (8x6) transonic wind tunnel. The test demonstrated the component performance goals necessary for an overall fuel burn reduction of 3 to 5 percent on a large hybrid wing body (HWB) aircraft. Special test equipment, including a raised floor with flow effectors and a bleed system, was developed for use in the 8x6 to produce the appropriate incoming boundary layer representative of an HWB application. Detailed measurements were made to determine the inlet total pressure loss and distortion, fan stage efficiency, and aeromechanic performance including blade vibration stress and displacement response. Results from this test were used as input to a vehicle-level system study performed by the AATT project to assess the impact of BLI on an alternative advanced concept aircraft referred to as the NASA D8 (ND8), which is somewhat similar to the HWB in its integration of the propulsor. This paper will provide an overview of the project timeline, special test equipment needed in the wind tunnel to develop the appropriate incoming boundary layer, and the difficulties in designing a propulsor for the test. The paper will conclude with some representative aerodynamic and aeromechanic data from the test itself and conclude with how this data was used in the ND8 system study.
Document ID
20190032273
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Celestina, Mark L. (NASA Glenn Research Center Cleveland, OH, United States)
Long-Davis, Mary J. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
October 25, 2019
Publication Date
September 22, 2019
Subject Category
Aerodynamics
Report/Patent Number
GRC-E-DAA-TN73213
Meeting Information
Meeting: International Society for Air Breathing Engines (ISABE) Conference
Location: Canberra
Country: Australia
Start Date: September 22, 2019
End Date: September 27, 2019
Sponsors: International Society for Air Breathing Engines (ISABE)
Funding Number(s)
WBS: 081876.02.03.50.06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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