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：US20160281517A1

公开(公告)日：2016-09-29

申请号：US14669902

申请日：2015-03-26

Applicant: Solar Turbines Incorporated

Inventor： Yong Weon Kim ,  Garrett P. Prins

IPC: F01D9/04 ,  F01D25/12

CPC classification number: F01D9/065 ,  F01D5/189 ,  F05D2230/21 ,  F05D2240/121

Abstract: A nozzle segment for a turbine nozzle of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall spaced apart from the upper endwall, a pressure portion, and a suction portion. The pressure portion extends between the upper endwall and the lower endwall adjacent a first side of the nozzle segment. The suction portion is spaced apart from the pressure portion and extends between the upper endwall and the lower endwall adjacent a second side of the nozzle segment. The second side is opposite the first side.

Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮喷嘴的喷嘴段。 喷嘴段包括上端壁，与上端壁间隔开的下端壁，压力部分和抽吸部分。 压力部分在上端壁和下端壁之间相邻于喷嘴段的第一侧延伸。 抽吸部分与压力部分间隔开并且在上端壁和下端壁之间延伸，邻近喷嘴段的第二侧。 第二面与第一面相对。

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。