Matrix Solution of Compressible Flow on S1 Surface Through a Turbomachine Blade Row With Splitter Vanes or Tandem Blades

The basic aerothermodynamic equations of turbomachine flow expressed with respect to nonorthogonal curvilinear coordinates and corresponding nonorthogonal velocity components are used to solve the compressible flow S1 surface in a turbomachine blade row with splitter vanes or tandem blades. The equa...

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Published in:Journal of engineering for gas turbines and power 1984-04, Vol.106 (2), p.449-454
Main Authors: Wu, Chung-Hua, Wang, Baoguo
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Language:English
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container_title Journal of engineering for gas turbines and power
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Wang, Baoguo
description The basic aerothermodynamic equations of turbomachine flow expressed with respect to nonorthogonal curvilinear coordinates and corresponding nonorthogonal velocity components are used to solve the compressible flow S1 surface in a turbomachine blade row with splitter vanes or tandem blades. The equation of stream function is solved by matrix technique, and the mass flow ratio and outlet flow angle are determined by applying the Kutta-Joukowsky condition to the trailing edges of the main blade and the splitter vane. Typical examples are given to illustrate the effectiveness of the present method.
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Eng. Gas Turbines Power</stitle><date>1984-04-01</date><risdate>1984</risdate><volume>106</volume><issue>2</issue><spage>449</spage><epage>454</epage><pages>449-454</pages><issn>0742-4795</issn><eissn>1528-8919</eissn><abstract>The basic aerothermodynamic equations of turbomachine flow expressed with respect to nonorthogonal curvilinear coordinates and corresponding nonorthogonal velocity components are used to solve the compressible flow S1 surface in a turbomachine blade row with splitter vanes or tandem blades. The equation of stream function is solved by matrix technique, and the mass flow ratio and outlet flow angle are determined by applying the Kutta-Joukowsky condition to the trailing edges of the main blade and the splitter vane. Typical examples are given to illustrate the effectiveness of the present method.</abstract><pub>ASME</pub><doi>10.1115/1.3239587</doi><tpages>6</tpages></addata></record>
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ispartof Journal of engineering for gas turbines and power, 1984-04, Vol.106 (2), p.449-454
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title Matrix Solution of Compressible Flow on S1 Surface Through a Turbomachine Blade Row With Splitter Vanes or Tandem Blades
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