The increasing demand of more economical and environmentally friendly aeroengines leads to the proposal of a new concept – geared turbofan. In this thesis,the characteristics of this kind of engine and relevant considerations ofintegration on a flying wing aircraft were studied.The studies can be divided into four levels: GTF-11 engine modelling andperformance simulation; aircraft performance calculation; nacelle design andaerodynamic performance evaluation; preliminary engine installation.Firstly, a geared concept engine model was constructed using TURBOMATCHsoftware. Based on parametric analysis and SFC target, the main cycleparameters were selected. Then, the maximum take-off thrust was verified andcorrected from 195.56kN to 212kN to meet the requirements of take-off fieldlength and second segment climb. Besides, the engine performance at offdesignpoints was simulated for aircraft performance calculation.Secondly, an aircraft performance model was developed and the performanceof FW-11 was calculated on the basis of GTF-11 simulation results. Then, theeffect of GTF-11 characteristics performance on aircraft performance wasevaluated. A comparison between GTF-11 and conventional turbofan, RB211-524B4, indicated that the aircraft can achieve a 13.1% improvement in fuelefficiency by using the new concept engine.Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series andempirical methods while the nacelle dimensions of conventional turbofanRB211-525B4 were obtained by measure approach. Then, the installation thrustlosses caused by nacelle drags of the two engines were evaluated using ESDU81024a. The results showed that the nacelle drags account for about 4.08%and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively.Finally, the considerations of engine installation on a flying wing aircraft werediscussed and a preliminary disposition of GTF-11 on FW-11 was presented.
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