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1 Introduction 1.1 Problem area The request for proposal is a joint AIAA Foundation and ASME/IGTI student design competition where a new turbofan engine for a conceptual supersonic business jet aircraft expected to enter service in 2025 is requested. It will be able to travel from North America to Europe and back again within one business day. It can cruise at Mach 1.15 over land without creating a sonic boom on the ground. Over water, it can cruise at Mach 1.5. Transonic cruise at Mach 0.98 should offer similar cost per distance to subsonic private jets. [1] Today’s aircraft industry is very competitive. The commercial success of an aircraft highly depends on its ability to provide light weight, low noise, competitive fuel consumption, and in the end lower operating costs and passenger fares. A contributing factor to achieve this is the engine design. Furthermore, due to the increase of the environmental concerns over the impact of the growing civil aviation, the emission legislations set by the International Civil Aviation Organization (ICAO) are becoming more stringent. The airlines need to continuously reduce their operating costs, which combined with stringent emission legislations introduces new challenges for the aero-engine industry: new engines need to be developed for low operating costs as well as reduced environmental impact. A reduction of fuel consumption, which is directly proportional to CO2 emissions, can be achieved primarily by increasing component efficiencies, increasing OPR and TIT reducing SFN and engine size and weight. A number of novel engine concepts addressing these issues have been proposed over the years, some of which will be presented briefly in chapter two of this thesis. Implementations of such concepts however, involve a great financial risk for the manufacturers [2]. In this thesis, a more conventional cycle is considered. Engine development is a multidisciplinary process covering thermodynamics, aerodynamics and solid mechanics, where the requirements of one discipline may very well contradict the requirements of another, and trade-offs between performance, size, weight, and costs continuously need to be made. Engine specifications are provided in the RFP, including thrust requirements, maximum dimensions etc. A generic model of a baseline engine is also provided. The new engine is expected to have improved fuel consumption and overall performance, thus increasing the chances of commercial success for the aircraft. The new engine has been given the designation MJ – Haran S14. 1.2 Aim and objectives There is one primary objective and one secondary objective for this thesis. The primary is to carry out a preliminary design for an engine complying with the requirements specified in the RFP. This can be broken down in the following steps: 1. Model the baseline engine and perform a thermodynamic study of the cycle performance. 2. Optimize the engine cycle for low fuel consumption, and high cycle overall efficiency. 3. Carry out preliminary sizing, efficiency calculations and aerodynamic design for the main engine components. 4. Create a schematic design of the engine including dimensions. 12PDF Image | Conceptual Design of a Supersonic Jet Engine
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