Investigation of the Aerodynamic Performance of a Transonic Axial-flow Turbine with Variable Nozzle

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概要

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• A single-stage transonic turbine was tested over a wide range of pressure ratios. The exit Mach number of nozzle and blade are supersonic at the design pressure ratio of 4.16. The measured performance was compared with the results calculated by a mean-line prediction method, using two kinds of loss systems. One is Ainley & Mathieson's system improved by Dunham & Came (AMDC), and the other is Craig & Cox's system (C&C). It was found that airflow characteristics and loss systems play an important role in estimating the performance of a transonic turbine, especially when nozzle and rotor row are choked alternately.

• 一般社団法人日本機械学会の論文

著者

• Takagi Toshiyuki

  Research & Development Division Process Plant & Machinery Headquarters Mitsui Engineering &a

関連論文

• Investigation of the Aerodynamic Performance of a Transonic Axial-flow Turbine with Variable Nozzle
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