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American Institute of Aeronautics and Astronautics

    Undergraduate Team Engine Design Competition

    Undergraduate Team Engine Design Competition

    An Ultra-High Bypass Ratio Turbofan Engine for the Future

    Deadline for LOI pushed to 1 May 2015


    Special Note:

    This Competition is different than other AIAA Design Competitions. The letter of intent is due earlier, and the competition is run in a two step process. Reports will be due in March. A review committee will evaluate all of the submitted proposals, and the top three will be invited to a conference session to make an oral presentation. This oral presentation will be scored and combined with the evaluations from the technical report. The combined scores will determine final 1st - 3rd rankings.


    Additionally, unlike other design competitions, there is NO MONETARY PRIZE for this competition cycle (2014-2015).





    Major engine manufacturers are continually assessing and revising their technical & business plans to ensure that their vision reaches into the next decade.  In the commercial aviation market, replacement engines for new generations of the Boeing 787 and Airbus A380 & A350 airplanes are currently being considered.  Very recently Rolls-Royce revealed its road map for the future(1), whereby it will extend its Trent 1000 and Trent XWB engine programs to address significantly higher bypass ratios, further improvements in propulsive efficiencies at cruise and reduced fuel burn & emissions for long range travel in 2025 and beyond.  This Request for Proposal asks that you also look to 2025 and design a new 3-spool, high bypass ratio turbofan for entry into service around that time for use on twin-engine, wide-body passenger and freight aircraft.  Your primary objective is also reduced fuel burn, as a result of higher propulsive efficiency at cruise conditions.

    A generic model, representative of 3-spool current systems is supplied as a baseline engine.  You should model this engine with your design system to provide a viable basis reference for improvement.  You are then required to retain the core of the baseline design and generate a new LP/IP system that fits around it, using aerodynamic similarity.  A simple but typical, multi-segment, extended mission should be constructed that covers both design-point and off-design engine operations.  Such a mission will also test propulsive efficiencies at cruise and reduced fuel burn specifically and should be “flown” using both engines.  The performance characteristics and total fuel consumption of both engines should be estimated over the mission and stated clearly in the proposal.  The benefits of the new design should be clearly stated.  Special attention should be paid to engine mass, dimensions & integration with the aircraft.  Technical feasibility is critical and operating costs should also be considered. 



    Primary Contact:

    Ian Halliwell


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