公开(公告)号：US09314838B2

公开(公告)日：2016-04-19

申请号：US13631043

申请日：2012-09-28

Applicant: Solar Turbines Incorporated

Inventor： Stephen Edward Pointon ,  Andrew Meier ,  Nnawuihe Asonye Okpara ,  Daniel Martinez

IPC: B22C9/10 ,  F01D5/18 ,  B22C7/02 ,  B22C9/04

CPC classification number: B22C9/10 ,  B22C7/02 ,  B22C9/04 ,  B22C9/043 ,  B22C9/108 ,  F01D5/187 ,  F05D2230/21 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/22141 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.

Abstract translation: 一种制造用于燃气涡轮发动机的冷却涡轮叶片的方法。 该方法包括形成内刀片图案，内刀片图案包括内翼片和多个内翼片冷却翅片。 该方法还包括形成内刀片芯，从内刀片芯中去除内刀片图案，形成外刀片图案，形成铸造壳体，从铸造壳体移除外刀片图案，以及将冷却的涡轮叶片铸造在 铸壳。 该方法还包括从铸冷却的涡轮机叶片移除铸造壳体，以及从铸造冷却的涡轮机叶片移除内部叶片芯部。

公开(公告)号：US20140271206A1

公开(公告)日：2014-09-18

申请号：US13797090

申请日：2013-03-12

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Angelo Vincent Marasco ,  Daniel Martinez ,  Garrett P. Prins

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D5/22

Abstract: A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.

Abstract translation: 燃气涡轮发动机涡轮盘组件包括涡轮盘，涡轮叶片和销密封件。 每个涡轮机叶片包括具有延伸到平台的压力侧的压力侧密封槽和延伸到平台的吸入侧的吸力侧密封槽的平台。 压力侧密封槽和吸力侧密封槽相对于涡轮盘的轴线在径向方向上分别成三度到十度。 销密封件包括圆柱形并且位于由相邻涡轮叶片的压力侧密封槽和吸力侧密封槽形成的密封槽内。

公开(公告)号：US20140271205A1

公开(公告)日：2014-09-18

申请号：US13796765

申请日：2013-03-12

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Angelo Vincent Marasco ,  Daniel Martinez ,  Garrett P. Prins

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D5/22

Abstract: A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.

Abstract translation: 燃气涡轮发动机涡轮盘组件包括涡轮盘，涡轮叶片和销密封件。 每个涡轮机叶片包括具有延伸到平台的压力侧的压力侧密封槽和延伸到平台的吸入侧的吸力侧密封槽的平台。 压力侧密封槽和吸力侧密封槽相对于涡轮盘的轴线在径向方向上分别成三度到十度。 销密封件包括圆柱形并且位于由相邻涡轮叶片的压力侧密封槽和吸力侧密封槽形成的密封槽内。

公开(公告)号：US20140093387A1

公开(公告)日：2014-04-03

申请号：US13631043

申请日：2012-09-28

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Stephen Edward Pointon ,  Andrew Meier ,  Nnawuihe Asonye Okpara ,  Daniel Martinez

IPC: B23P15/02 ,  F01D5/18

CPC classification number: B22C9/10 ,  B22C7/02 ,  B22C9/04 ,  B22C9/043 ,  B22C9/108 ,  F01D5/187 ,  F05D2230/21 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/22141 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.

Abstract translation: 一种制造用于燃气涡轮发动机的冷却涡轮叶片的方法。 该方法包括形成内刀片图案，内刀片图案包括内翼片和多个内翼片冷却翅片。 该方法还包括形成内刀片芯，从内刀片芯中去除内刀片图案，形成外刀片图案，形成铸造壳体，从铸造壳体移除外刀片图案，以及将冷却的涡轮叶片铸造在 铸壳。 该方法还包括从铸冷却的涡轮机叶片移除铸造壳体，以及从铸造冷却的涡轮机叶片移除内部叶片芯部。

公开(公告)号：US20140093386A1

公开(公告)日：2014-04-03

申请号：US13631258

申请日：2012-09-28

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Stephen Edward Pointon ,  Andrew Meier ,  Nnawuihe Asonye Okpara ,  Daniel Martinez ,  Jiang Luo

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/20 ,  F05D2260/2214

Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of inner spar cooling fins extending from the inner spar to the skin, and a plurality of trailing edge cooling fins extending from the pressure side of the skin to the lift side of the skin aft of the inner spar.

Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 机翼还包括一个“皮肤”，其包括尖端壁，内部翼梁，从内部翼梁延伸到皮肤的多个内部翼梁冷却翅片，以及从皮肤的压力侧延伸的多个后缘冷却翅片 到内部翼梁的皮肤后部的提升面。