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Oliver Sjögren, Tomas Grönstedt, Anders Lundbladh and Carlos Xisto
In modern turbofan engines, the bypass section of the fan stage alone provides the majority of the total thrust required in cruise, and the size of the fan has a considerable effect on the overall engine weight and nacelle drag. Thrust requirements in di...
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Xin Zhao, Philip Van Hoorn, Hua-Dong Yao and James Alderman
The inflow distortion to the fan introduced by the ingestion of the fuselage boundary layer is the most critical challenge in realizing the benefits of boundary later ingesting (BLI) concepts. Minimizing the level of distortion while maintaining the desi...
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Hamidreza Abedi, Carlos Xisto, Isak Jonsson, Tomas Grönstedt and Andrew Rolt
The investigation of the various heat management concepts using LH2 requires the development of a modeling environment coupling the cryogenic hydrogen fuel system with turbofan performance. This paper presents a numerical framework to model hydrogen-fuel...
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Jan Wislicenus and Nihad E. Daidzic
One of the most difficult steps in estimating the cruise performance characteristics of high-subsonic transport-category turbofan-powered airplanes is the estimation of the transonic wave drag. Modern jet airplanes cruise most efficiently in the vicinity...
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Giorgio Palma, Lorenzo Burghignoli, Francesco Centracchio and Umberto Iemma
Modern turbofans with high bypass ratios, low blade passage frequencies and short nacelles require continuous development of acoustic linings to achieve the noise reductions expected by the international aviation authorities. Metamaterials and metafluids...
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Rainer Schnell, Xin Zhao, Efthymios Rallis, Mavroudis Kavvalos, Smruti Sahoo, Markus Schnoes and Konstantinos Kyprianidis
In this paper, a turbo-electric propulsion system was analyzed, and its performance was assessed. The aircraft considered here was a single-aisle, medium-range configuration targeting a capacity of 150 Pax. The propulsion concept comprised two boosted ge...
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James Large and Apostolos Pesyridis
In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the ...
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