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CENTRIFUGAL COMPRESSOR IMPELLER WITH NON-LINEAR BLADE LEADING EDGE AND ASSOCIATED DESIGN METHOD
CENTRIFUGAL COMPRESSOR IMPELLER WITH NON-LINEAR BLADE LEADING EDGE AND ASSOCIATED DESIGN METHOD
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机译:具有非线性叶片前缘的离心压缩机叶轮及其设计方法
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摘要
A centrifugal compressor impeller comprises a gas inlet, a gas outlet, and a disc having a plurality of blades extending therefrom. Each blade has a leading edge at the impeller inlet and a trailing edge at the impeller outlet, a blade base extending along the disc between the leading edge and the trailing edge, a blade tip extending between the leading edge and the trailing edge opposite the disc, a pressure side and a suction side. Each blade has a three-dimensional curvature in at least a portion of the surface, adjacent the leading edge. The leading edge has a curved, non-linear profile in a meridian plane. The blade portion has a double-curvature. Each blade has a first metal angle distribution at the blade base, a second metal angle distribution at the blade tip and at least a third metal angle distribution between the blade base and the blade tip.
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