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.
Boundary Layer Ingesting Inlet / Distortion-Tolerant Fan (BLI2DTF) Propulsion for Highly Efficient Subsonic Cruise Aircraft
2016
13 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Air transportation , Boundary layers , Wind tunnel tests , Distortion , Fabrication , Fan blades , Inlet flow , Propulsion system performance , Subsonic aircraft , Technology utilization , Turbofans , Design analysis , Propulsive efficiency , Research and development , Technology assessment , Thrust control , Transport aircraft , Turbofan engines
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