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2 Literature review A large number of research papers have been published regarding the aero engine industry over the years. In this chapter, a few of these regarding important aspects of the engine design process will be discussed. 2.1 Reducing fuel consumption Today one major concern in the industry is producing engines with better fuel economy, partially to reduce the operating costs for the airlines leading to lower fares for paying passengers, but also to address today’s environmental concerns. A few approaches to achieve this has been proposed. A summary of some of the current research being done in the search for more fuel efficient engines is provided in [2]. The author starts by discussing the limitations of increasing OPR and TIT in order to increase thermal efficiency and reduce SFC, which has been the trend for conventional cores over the past decades. Increasing OPR further than current designs is limited by HPC delivery temperature at take-off. Increasing TIT is limited by the maximum HPT rotor temperatures at take-off and top of climb. The increase of cooling flows for this reason is also a limited strategy since this represent losses in the cycle and will eventually lead to a loss in thermal efficiency. In [3] the authors investigate the benefits of introducing Intercooled and intercooled recuperated cores. An intercooled core can be designed for a significantly higher overall pressure ratio, with reduced cooling requirements, providing a higher thermal efficiency than could be practically achieved with a conventional core. In an intercooled recuperated core a high thermal efficiency can be achieved at a low overall pressure ratio. The use of a variable geometry auxiliary nozzle for the intercooled engine, and a variable geometry LPT for the intercooled recuperated engine is also evaluated, showing further benefits. The use of recuperation is also investigated in [4], where a recuperated engine for a UAV is compared to a conventional design. The novel engine is expected to maintain the same weight as the conventional engine and extend the mission endurance by 15%. In [5], a geared open rotor configuration engine is compared to an ultra-high bypass geared turbofan engine, with focus on minimizing fuel consumption and hence engine emissions. The open rotor concept is not a new idea, it was evaluated in the 80’s in several flight tests, but most of them never got past that phase and lately the concept has resurfaced. In an open rotor configuration the propulsive efficiency may be increased without increasing nacelle drag, and losses due to transfer efficiency are comparable to those of a turbofan. The results show that the open rotor engine is heavier but the reduced SFC and nacelle drag makes up for this and a mission fuel burn improvement of approximately 15% compared to the turbofan is presented. In [2] the author concludes by highlighting the fact that even though research of more efficient engine concepts exists, the aero engine design industry is primarily driven by economic considerations. Introducing these novel concepts to the market involves an economical and technological risk, and whether the potential reduction in fuel consumption outweighs these risks remains to be seen. 14PDF Image | Conceptual Design of a Supersonic Jet Engine
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