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    Turbine blade internal cooling configuration
    3.
    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。

    Cooling arrangement for turbine components
    4.
    发明授权
    Cooling arrangement for turbine components 有权
    涡轮机组件的冷却装置

    公开(公告)号：US08105031B2

    公开(公告)日：2012-01-31

    申请号：US11971932

    申请日：2008-01-10

    申请人： Ricardo Trindade ,  Bryan P. Dube ,  William Abdel-Messeh

    发明人： Ricardo Trindade ,  Bryan P. Dube ,  William Abdel-Messeh

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  Y02T50/676

    摘要： A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component.

    摘要翻译： 涡轮机部件包括在涡轮机中部和涡轮机尾端之间延伸的后冷却回路。 后冷却回路包括靠近后端的后端部分，靠近涡轮机中部的第一内部部分和流体连接在后端部分和第一内部部分之间的第一中间部分。 涡轮机部件的向前冷却回路在涡轮机中部和涡轮机前端之间延伸。 前向冷却回路包括靠近前端的前端部分，靠近涡轮机中部的第二内部部分和流体连接在前端部分和第二内部部分之间的多个第二中间部分。 前端部分，第二中间部分，第一中间部分和后端部分均包括多个用于促进涡轮部件冷却的冷却剂排放口。

    Rotor blade for a rotary machine
    6.
    发明授权
    Rotor blade for a rotary machine 有权
    旋转机用转子叶片

    公开(公告)号：US07134838B2

    公开(公告)日：2006-11-14

    申请号：US10770322

    申请日：2004-01-31

    申请人： Bryan P. Dube ,  Eric D. Gray

    发明人： Bryan P. Dube ,  Eric D. Gray

    IPC分类号： F01D11/08

    CPC分类号： F01D5/225 ,  F01D5/147 ,  Y02T50/671 ,  Y10S416/02

    摘要： A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing the shroud with a depression in the shroud and a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the tip shroud has a depression generally outwardly of the airfoil and generally following the curve of the pressure and suction sides of the airfoil from the leading edge region to the trailing edge region.

    摘要翻译： 公开了一种具有用于尖端护罩的机翼和梁结构的转子叶片。 开发了各种构造细节，用于为护罩提供护罩中的凹陷和从翼型的吸力侧和压力侧延伸的过渡区域，以提供护罩的流动通道表面。 在一个详细的实施例中，尖端护罩具有通常在翼面外侧的凹陷，并且通常沿着翼型的压力和吸力侧面从前缘区域到后缘区域的曲线。

    Turbine blade internal cooling configuration
    8.
    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。

    COOLING ARRANGEMENT FOR TURBINE COMPONENTS
    9.
    发明申请
    COOLING ARRANGEMENT FOR TURBINE COMPONENTS 有权
    涡轮组件冷却装置

    公开(公告)号：US20090180861A1

    公开(公告)日：2009-07-16

    申请号：US11971932

    申请日：2008-01-10

    申请人： Ricardo Trindade ,  Bryan P. Dube ,  William Abdel-Messeh

    发明人： Ricardo Trindade ,  Bryan P. Dube ,  William Abdel-Messeh

    IPC分类号： F02C7/12

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  Y02T50/676

    摘要： A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component.

    摘要翻译： 涡轮机部件包括在涡轮机中部和涡轮机尾端之间延伸的后冷却回路。 后冷却回路包括靠近后端的后端部分，靠近涡轮机中部的第一内部部分和流体连接在后端部分和第一内部部分之间的第一中间部分。 涡轮机部件的向前冷却回路在涡轮机中部和涡轮机前端之间延伸。 前向冷却回路包括靠近前端的前端部分，靠近涡轮机中部的第二内部部分和流体连接在前端部分和第二内部部分之间的多个第二中间部分。 前端部分，第二中间部分，第一中间部分和后端部分均包括多个用于促进涡轮部件冷却的冷却剂排放口。

    Rotor blade for a rotary machine
    10.
    发明授权
    Rotor blade for a rotary machine 有权
    旋转机用转子叶片

    公开(公告)号：US07396205B2

    公开(公告)日：2008-07-08

    申请号：US10770331

    申请日：2004-01-31

    申请人： Bryan P. Dube ,  Eric D. Gray

    发明人： Bryan P. Dube ,  Eric D. Gray

    IPC分类号： F01D11/08

    CPC分类号： F01D11/08 ,  F01D5/143 ,  F01D5/147 ,  F01D5/225 ,  F05D2250/232 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/94 ,  F05D2260/941 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/02

    摘要： A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the transition zone over substantially all of its extent between the leading edge region and the trailing edge region is contoured to extend to the sides of the wings to provide a spanwise taper that extends to the side of the wing.

    摘要翻译： 公开了一种具有用于尖端护罩的机翼和梁结构的转子叶片。 开发了各种构造细节，用于提供从翼型的吸力侧和压力侧延伸的过渡区域，以提供护罩的流动通道表面。 在一个详细的实施例中，在前缘区域和后缘区域之间的基本上其全部范围上的过渡区域被轮廓化以延伸到翼的侧面，以提供延伸到机翼侧面的翼展方向的锥形。