公开(公告)号：US20160160667A1

公开(公告)日：2016-06-09

申请号：US14540730

申请日：2014-11-13

Applicant: General Electric Company

Inventor： Joe Timothy Brown ,  Elizabeth Angelyn Fadde ,  Sivaraman Vedhagiri

IPC: F01D9/02 ,  F02C7/28 ,  F02C3/14 ,  F01D9/04 ,  F02C3/04

CPC classification number: F01D9/023 ,  F01D11/005 ,  F02C7/28 ,  F05D2230/54 ,  F05D2240/128 ,  F05D2240/55

Abstract: A sealing assembly for a turbine engine includes a first stationary component. Also included is a second stationary component, wherein the first stationary component and the second stationary component define a gap therebetween. Further included is a discourager seal in contact with at least one of the first stationary component and the second stationary component, the discourager seal having a lip portion disposed within the gap to reduce a fluid flow through the gap.

Abstract translation: 用于涡轮发动机的密封组件包括第一固定部件。 还包括第二固定部件，其中第一固定部件和第二固定部件之间形成间隙。 进一步包括与第一固定部件和第二固定部件中的至少一个接触的罢工密封件，捣固器密封件具有设置在间隙内的唇部，以减少通过间隙的流体流动。

公开(公告)号：US10352180B2

公开(公告)日：2019-07-16

申请号：US14061095

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Alexander Stein ,  Glen Arthur MacMillan ,  Thomas Brunt ,  Joe Timothy Brown

IPC: F01D9/02 ,  F01D9/04

Abstract: A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

公开(公告)号：US20160131041A1

公开(公告)日：2016-05-12

申请号：US14534934

申请日：2014-11-06

Applicant: General Electric Company

Inventor： Stephen Paul Wassynger ,  Joe Timothy Brown ,  Sivaraman Vedhagiri

IPC: F02C7/20 ,  F02C5/02 ,  F02C3/04

CPC classification number: F01D9/023 ,  Y02T50/675

Abstract: A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a compressor discharge portion, a hot gas path and a first stage nozzle arranged at the hot gas path. A combustor assembly is fluidically connected to the compressor portion. A transition piece has an inlet portion fluidically connected to the combustor assembly and an outlet portion fluidically connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine portion. The seal member extends from a first end to a second, cantilevered end through an intermediate portion including one or more openings that provide a purge fluid flow path from the compressor discharge portion toward the hot gas path.

Abstract translation: 涡轮机包括压缩机部分和可操作地连接到压缩机部分的涡轮机部分。 涡轮部包括设置在热气路径处的压缩机排出部，热气路径和第一级喷嘴。 燃烧器组件流体地连接到压缩机部分。 过渡件具有流体连接到燃烧器组件的入口部分和与涡轮部分流体连接的出口部分。 密封构件相对于涡轮机部分的过渡件和第一级喷嘴中的一个可操作地连接。 密封构件从第一端延伸到第二悬臂端，穿过包括一个或多个开口的中间部分，该开口提供从压缩机排放部朝向热气路径的清洗流体流动路径。

公开(公告)号：US09376927B2

公开(公告)日：2016-06-28

申请号：US14060996

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Alexander Stein ,  Joe Timothy Brown ,  Ravichandran Meenakshisundaram

IPC: F01D5/14 ,  F01D9/04

CPC classification number: F01D9/041 ,  F01D5/141 ,  F05D2240/80 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/673

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.

Abstract translation: 本发明的各种实施例包括涡轮喷嘴和采用这种喷嘴的系统。 各种具体实施例包括涡轮喷嘴，其具有：具有吸力侧的翼型件; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与前缘相对并跨越压力侧和吸力侧的后缘; 以及沿着吸力侧，压力侧，后缘和前缘与翼型件连接的至少一个端壁，所述至少一个端壁包括在端壁与翼型的前缘之间的接合处的非轴对称轮廓。

公开(公告)号：US20150192020A1

公开(公告)日：2015-07-09

申请号：US14150190

申请日：2014-01-08

Applicant: General Electric Company

Inventor： Anshuman Singh ,  Joe Timothy Brown ,  Ravi Meenaksh ,  Ibrahim Sezer

IPC: F01D5/18

CPC classification number: F01D11/24 ,  F01D5/187 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial outer side, and a plurality of side surfaces. The radial outer side includes a recessed portion. A trench is formed in the recessed portion, and a cooling passage extends between the trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member. The at least one mounting member includes an internal cavity. A trench element is formed in the internal cavity, and a cooling passage element extends between the trench element and an external surface of the nozzle.

Abstract translation: 涡轮机包括压缩机部分，可操作地连接到压缩机部分的涡轮机部分和安装在压缩机部分和涡轮机部分之一中的护罩。 护罩包括径向外侧和多个侧表面。 径向外侧包括凹部。 在凹部中形成沟槽，并且冷却通道在沟槽和多个侧表面中的至少一个之间延伸。 在压缩机部分和涡轮部分中的一个中布置有翼型部件。 机翼部件包括具有至少一个安装部件的翼型部分。 所述至少一个安装构件包括内部空腔。 沟槽元件形成在内腔中，冷却通道元件在沟槽元件和喷嘴的外表面之间延伸。

公开(公告)号：US20150110618A1

公开(公告)日：2015-04-23

申请号：US14060996

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Alexander Stein ,  Joe Timothy Brown ,  Ravichandran Meenakshisundaram

IPC: F01D9/04 ,  F01D5/14

CPC classification number: F01D9/041 ,  F01D5/141 ,  F05D2240/80 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/673

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.

Abstract translation: 本发明的各种实施例包括涡轮喷嘴和采用这种喷嘴的系统。 各种具体实施例包括涡轮喷嘴，其具有：具有吸力侧的翼型件; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与前缘相对并跨越压力侧和吸力侧的后缘; 以及沿着吸力侧，压力侧，后缘和前缘与翼型件连接的至少一个端壁，所述至少一个端壁包括在端壁与翼型的前缘之间的接合处的非轴对称轮廓。