Meeting future goals for aircraft and air traffic system performance will require new airframes with more highly integrated propulsion. Previous studies have evaluated hybrid wing body (HWB) configurations with various numbers of engines and with increasing degrees of propulsion-airframe integration. A recently published configuration with 12 small engines partially embedded in a HWB aircraft, reviewed herein, serves as the airframe baseline for the new concept aircraft that is the subject of this paper. To achieve high cruise efficiency, a high lift-to-drag ratio HWB was adopted as the baseline airframe along with boundary layer ingestion inlets and distributed thrust nozzles to fill in the wakes generated by the vehicle. The distributed powered-lift propulsion concept for the baseline vehicle used a simple, high-lift-capable internally blown flap or jet flap system with a number of small high bypass ratio turbofan engines in the airframe. In that concept, the engine flow path from the inlet to the nozzle is direct and does not involve complicated internal ducts through the airframe to redistribute the engine flow. In addition, partially embedded engines, distributed along the upper surface of the HWB airframe, provide noise reduction through airframe shielding and promote jet flow mixing with the ambient airflow. To improve performance and to reduce noise and environmental impact even further, a drastic change in the propulsion system is proposed in this paper. The new concept adopts the previous baseline cruise-efficient short take-off and landing (CESTOL) airframe but employs a number of superconducting motors to drive the distributed fans rather than using many small conventional engines. The power to drive these electric fans is generated by two remotely located gas-turbine-driven superconducting generators. This arrangement allows many small partially embedded fans while retaining the superior efficiency of large core engines, which are physically separated but connected through electric power lines to the fans. This paper presents a brief description of the earlier CESTOL vehicle concept and the newly proposed electrically driven fan concept vehicle, using the previous CESTOL vehicle as a baseline.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Distributed Turboelectric Propulsion for Hybrid Wing Body Aircraft


    Contributors:

    Conference:

    2008 International Powered Lift Conference Royal Aeronautical Society ; 2008 ; London, United Kingdom


    Publication date :

    2008-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Distributed Turboelectric Propulsion for Hybrid Wing Body Aircraft

    Kim, H. | British Library Conference Proceedings | 2008


    Turboelectric Distributed Propulsion in a Hybrid Wing Body Aircraft

    Felder, James L. / Brown, Gerald V. / DaeKim, Hyun et al. | NTRS | 2011


    Turboelectric Distributed Propulsion in a Hybrid Wing Body Aircraft

    Brown, G.V. / Chu, J. / Felder, J.L. et al. | British Library Conference Proceedings | 2011


    Turboelectric Distributed Propulsion System Modelling for Hybrid-Wing-Body Aircraft

    Liu, Chengyuan / Doulgeris, Georgios / Laskaridis, Panagiotis et al. | AIAA | 2012


    Turboelectric Distributed Propulsion Engine Cycle Analysis for Hybrid-Wing-Body Aircraft

    Felder, James L. / Kim, Hyun Dae / Brown, Gerald V. | NTRS | 2009