IGTC-5 A Consideration of Blade Loading Criteria for Radial Inflow Turbines(Session A-2 AERODYNAMICS II (Radial Flow))

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概要

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• The optimal blade loading conditins for a radial turbine rotor were experimentally and theoretically anaiyzed. Differences in turbine efficiency were measured for six types of rotors with different blade loading. Further, relative velocity distribution on the suction side of the rotor blade, as obtained from flow analysis, was used to determine momentum thickness and shape factor of the boundary layer. The cor-respondence was then noted between these values and differences in turbine efficiency. The boundary layer along the blade suction side, at the mean flow surface between the shroud and hub, is representative of the rotor's mean flow. The shorter the blade is, the thinner the momentum thickness at the rotor exit is, resulting in less pressure loss. Too high blade loading at the shroud surface, on the contray, results in lowered efficiency. This is seen to be due to increased loss caused by separation of the boundary layer in the vicinity of the shroud.

• 公益社団法人日本ガスタービン学会の論文

著者

• Takamura T.

  Engine & Powertrain Research Laboratory Central Engineering Laboratories Nissan Motor Co. Ltd.

• Itoh T.

  Engine & Powertrain Research Laboratory, Central Engineering Laboratories, Nissan Motor Co., Ltd.

関連論文

• IGTC-5 A Consideration of Blade Loading Criteria for Radial Inflow Turbines(Session A-2 AERODYNAMICS II (Radial Flow))
• IGTC-61 A CONSIDERATION CONCERNING STALL AND SURGE LIMITATIONS WITHIN CENTRIFUGAL COMPRESSORS-PART II(Session B-6 Aerodynamics IV (Radial Flow))

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