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    Turbine blade internal cooling configuration
    3.
    发明申请
    Turbine blade internal cooling configuration 有权
    涡轮叶片内部冷却配置

    公开(公告)号：US20090285684A1

    公开(公告)日：2009-11-19

    申请号：US12152372

    申请日：2008-05-14

    申请人： Sandra S. Pinero ,  Edward F. Pietraszkiewicz ,  Bryan P. Dube ,  Stephen J. Yee ,  Ryan Shepard Levy ,  Mohamed Hassan ,  Domenico Valerio ,  Scott D. Hartmann

    发明人： Sandra S. Pinero ,  Edward F. Pietraszkiewicz ,  Bryan P. Dube ,  Stephen J. Yee ,  Ryan Shepard Levy ,  Mohamed Hassan ,  Domenico Valerio ,  Scott D. Hartmann

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2250/30 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    摘要： A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.

    摘要翻译： 冷却的翼型件包括从基座到翼型件的尖端径向延伸的凹形压力壁，在前缘和与前缘轴向间隔开的后缘连接到凹形压力壁的凸形抽吸壁，以及多个冷却 在凹压壁和凸吸入壁之间形成的通道，并且构造成从翼型的底部接收冷却液供给。 冷却通道包括从基部朝向顶端径向延伸的前缘通道，从底部朝向顶端径向延伸并与多个后缘孔流动连通的后缘通道，其适于将冷却流体排出到外部 翼型件，包括多个通道的蛇形冷却回路，以及从蛇形冷却回路中的多个通道的前缘通道和前进通道之间的从底部朝向顶端径向延伸的专用上通通道。

    Turbine blade internal cooling configuration
    4.
    发明授权
    Turbine blade internal cooling configuration 有权
    涡轮叶片内部冷却配置

    公开(公告)号：US08172533B2

    公开(公告)日：2012-05-08

    申请号：US12152372

    申请日：2008-05-14

    申请人： Sandra S. Pinero ,  Edward F. Pietraszkiewicz ,  Bryan P. Dube ,  Stephen J. Yee ,  Ryan Shepard Levy ,  Mohamed Hassan ,  Domenico Valerio ,  Scott D. Hartmann

    发明人： Sandra S. Pinero ,  Edward F. Pietraszkiewicz ,  Bryan P. Dube ,  Stephen J. Yee ,  Ryan Shepard Levy ,  Mohamed Hassan ,  Domenico Valerio ,  Scott D. Hartmann

    IPC分类号： F01D5/08 ,  F01D5/18

    CPC分类号： F01D5/187 ,  F05D2250/30 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    摘要： A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.

    摘要翻译： 冷却的翼型件包括从基座到翼型件的尖端径向延伸的凹形压力壁，在前缘和与前缘轴向间隔开的后缘连接到凹形压力壁的凸形抽吸壁，以及多个冷却 在凹压壁和凸吸入壁之间形成的通道，并且构造成从翼型的底部接收冷却液供给。 冷却通道包括从基部朝向顶端径向延伸的前缘通道，从底部朝向顶端径向延伸并与多个后缘孔流动连通的后缘通道，其适于将冷却流体排出到外部 翼型件，包括多个通道的蛇形冷却回路，以及从蛇形冷却回路中的多个通道的前缘通道和前进通道之间的从底部朝向顶端径向延伸的专用上通通道。