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- W2333954023 abstract "Two key studies have suggested that lowering a rotor’s blade count is beneficial to a rotor’s performance. However, reducing the number of blades of conventional design can compromise the rotor’s flow-field, and thus lower the pressure ratio. To try to address this challenge, this paper examines the potential performance of an alternate blade style, conceptualized to significantly reduce the number of blades needed in a high flow compression system. The blade design is being evaluated in the first turbomachinery stage of a turbofan engine, or as a turbofan rotor. A steady-state and rigid body analysis has been conducted using ANSYS CFD tools. The flow characteristics and static thrust generated by the new blade model system were greater than for an equivalent existing turbofan system in preliminary simulations. The simulation results indicate that further research on this concept could pave the way for quieter, safer, and more efficient aircraft engines." @default.
- W2333954023 created "2016-06-24" @default.
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- W2333954023 date "2016-01-02" @default.
- W2333954023 modified "2023-09-24" @default.
- W2333954023 title "Evaluation of New Blade Concept for Turbofan Engines" @default.
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- W2333954023 doi "https://doi.org/10.2514/6.2016-0652" @default.
- W2333954023 hasPublicationYear "2016" @default.
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