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BLADE ROW FOR AN UNSTEADY AXIAL FLOW GAS TURBINE STAGE
BLADE ROW FOR AN UNSTEADY AXIAL FLOW GAS TURBINE STAGE
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机译：叶片行用于非定常的轴向燃气轮机级
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摘要
The current invention is directed to a blade row (50) for an axial flow gas turbine stage (100), comprising a plurality of blades (68) positioned in an annular array around an blade row axis (52), wherein a radial direction (56) runs perpendicular to said blade row axis (52), said plurality of blades (68) each radially extending from an inner diameter (62) to an outer diameter (64), wherein an annulus height (65, 66) of each blade (58) is defined between said inner diameter (62) and said outer diameter (64), wherein each blade (58) has a leading edge (86) and a trailing edge (88), said leading edge (86) of each blade (58) of the plurality of blades (68) being positioned in an inlet plane (90), and said trailing edge (88) of each blade (58) of the plurality of blades (68) being positioned in an outlet plane (92). Further, said inner diameter (62) and/or said outer diameter (64) of each blade (58) has a kink (72) so that said annulus height (65, 66) of each blade (58) increases between said inlet plane (90) and said outlet plane (92).
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