Record Details

Boundary Layer Ingesting Inlet / Distortion-Tolerant Fan (BLI2DTF) Propulsion for Highly Efficient Subsonic Cruise Aircraft
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Author and Affiliation:
Arend, David(NASA Glenn Research Center, Cleveland, OH United States);
Hirt, Stefanie(NASA Glenn Research Center, Cleveland, OH United States);
Bakhle, Milind(NASA Glenn Research Center, Cleveland, OH United States);
Wolter, John(NASA Glenn Research Center, Cleveland, OH United States);
Cousins, William(United Technologies Research Center, East Hartford, CT, United States);
Tillman, Greg(United Technologies Research Center, East Hartford, CT, United States);
Voytovych, Dmytro(United Technologies Research Center, East Hartford, CT, United States);
Sharma, Om(United Technologies Research Center, East Hartford, CT, United States);
Obrien, Walter(Virginia Polytechnic Inst. and State Univ., Blacksburg, VA, United States);
Ferrar, Anthony(Virginia Polytechnic Inst. and State Univ., Blacksburg, VA, United States);
Sirbaugh, James(Arnold Engineering Development Center, Arnold AFS, TN, United States)
Abstract: Significant progress has been made in the research and development of boundary layer ingesting (BLI) propulsors which studies and high fidelity analyses have predicted will have a four percent reduction in fuel burned for large transport class subsonic cruise aircraft. Funded by NASAs Advanced Air Transport Technology (AATT) Project, this work has necessarily comprised the efforts of inlets, turbomachinery, aeromechanics, nozzles, propulsion airframe integration and acoustics technical disciplines. A high level aircraft propulsion systems study has been completed and validated against other independent studies that identified significant performance benefit potential of this technology. Based on the results of the systems study, a Multi-disciplinary Design, Analysis and Optimization (MDAO) approach has been employed to design a coupled BLI Inlet Distortion-Tolerant Fan stage propulsor to determine whether the predicted performance benefits are achievable. High-fidelity, fully coupled integrated inlet fan computational fluid mechanics and aeromechanics analyses have been completed to identify, research and advance the enabling technologies required to design such a propulsor and thereby test the potential of this concept and its technologies. Such a propulsor has been designed and nearly completely fabricated in preparations for its evaluation through wind tunnel tests. Photographs are included showing the hardware that has been designed and is being installed into NASAs 8x6 Wind Tunnel in preparation for tests which are scheduled to occur in late fiscal 2016.
Publication Date: Aug 02, 2016
Document ID:
20170004391
(Acquired May 18, 2017)
Subject Category: AIRCRAFT PROPULSION AND POWER; AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number: GRC-E-DAA-TN34563
Document Type: Oral/Visual Presentation
Meeting Information: SAE S-16 Committee Meeting; 2-4 Aug. 2016; Snowmass, CO; United States
Meeting Sponsor: Society of Automotive Engineers, Inc.; Warrendale, PA, United States
Contract/Grant/Task Num: NNC07CB59C; WBS 031876.02.03.06.01.02
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH United States
Organization Source: NASA Glenn Research Center; Cleveland, OH United States
Description: 13p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: AIR TRANSPORTATION; BOUNDARY LAYERS; DISTORTION; FABRICATION; FAN BLADES; INLET FLOW; PROPULSION SYSTEM PERFORMANCE; SUBSONIC AIRCRAFT; TECHNOLOGY UTILIZATION; TURBOFANS; WIND TUNNEL TESTS; DESIGN ANALYSIS; PROPULSIVE EFFICIENCY; RESEARCH AND DEVELOPMENT; TECHNOLOGY ASSESSMENT; THRUST CONTROL; TRANSPORT AIRCRAFT; TURBOFAN ENGINES
Other Descriptors: PROPULSION; BOUNDARY LAYER; TURBOMACHINERY
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