公开(公告)号：US09938835B2

公开(公告)日：2018-04-10

申请号：US14068776

申请日：2013-10-31

Applicant: General Electric Company

Inventor： Andrew Paul Giametta ,  David Richard Johns

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/30

CPC classification number: F01D5/18 ,  F01D5/081 ,  F01D5/187 ,  F01D5/3007 ,  Y02T50/676

Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.

公开(公告)号：US09765699B2

公开(公告)日：2017-09-19

申请号：US14585871

申请日：2014-12-30

Applicant: General Electric Company

Inventor： Kevin Richard Kirtley ,  David Richard Johns ,  Andrew Paul Giametta ,  Richard William Johnson

IPC: F02C7/28 ,  F02C7/18 ,  F01D11/04 ,  F01D5/08 ,  F01D11/00

CPC classification number: F02C7/28 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F02C7/18 ,  F05D2240/127 ,  F05D2240/81

Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.

公开(公告)号：US20160186664A1

公开(公告)日：2016-06-30

申请号：US14585871

申请日：2014-12-30

Applicant: General Electric Company

Inventor： Kevin Richard Kirtley ,  David Richard Johns ,  Andrew Paul Giametta ,  Richard William Johnson

IPC: F02C7/28 ,  F01D11/04 ,  F02C7/18

CPC classification number: F02C7/28 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F02C7/18 ,  F05D2240/127 ,  F05D2240/81

Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.

Abstract translation: 一种具有涡轮机的燃气涡轮发动机，其包括定子叶片和转子叶片，所述转子叶片形成在其间限定的沟槽腔中。 密封件可以包括：从定子叶片朝向转子叶片延伸的定子悬垂线，以便包括悬垂顶面，并且与悬垂顶面相对的是突出的下侧; 转子外侧面从平台边缘径向向内延伸，所述转子外侧面与所述突出面的至少一部分相对于所述沟槽的轴向间隙相对; 从所述转子外侧面朝向所述定子叶片延伸的轴向突出部，以与所述定子突出部轴向重叠; 以及内部冷却通道，其延伸穿过定子悬垂端，穿过该突出部下侧形成的端口。 端口可以​​被配置为将从其排出的冷却剂引向轴向突出部。

公开(公告)号：US20160032752A1

公开(公告)日：2016-02-04

申请号：US14881765

申请日：2015-10-13

Applicant: General Electric Company

Inventor： David Richard Johns ,  Eric David Roush

IPC: F01D11/02 ,  F01D25/24

CPC classification number: F01D11/02 ,  F01D11/08 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/55

Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.

Abstract translation: 密封构造包括壳体和相对于壳体旋转地安装的可旋转构件。 可旋转构件具有限定外周面的至少一个部分，其构造成在导致至少一个部分的径向尺寸增加的操作条件期间接触壳体。 所述至少一个部分具有相对的轴向表面，其中每个相对的轴向表面的尺寸轴向更靠近所述外圆周表面的径向向内的所述相对的轴向表面中的另一个，而不是所述外周边面的最远部分。

公开(公告)号：US09771820B2

公开(公告)日：2017-09-26

申请号：US14585896

申请日：2014-12-30

Applicant: General Electric Company

Inventor： Richard William Johnson ,  Kevin Richard Kirtley ,  David Richard Johns ,  James William Vehr ,  Andrew Paul Giametta

IPC: F01D11/00 ,  F02C7/28 ,  F01D11/04 ,  F01D5/08

CPC classification number: F01D11/006 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F05D2240/81

Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.

公开(公告)号：US09528377B2

公开(公告)日：2016-12-27

申请号：US13972667

申请日：2013-08-21

Applicant: General Electric Company

Inventor： Michael James Fedor ,  David Richard Johns ,  Richard William Johnson

IPC: F01D5/08

CPC classification number: F01D5/081 ,  F01D5/08 ,  F01D5/082 ,  F01D5/085 ,  F01D5/087 ,  F01D5/088 ,  Y02T50/673 ,  Y02T50/676

Abstract: A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening.

Abstract translation: 提供了一种用于冷却联接到燃气涡轮发动机中的转子叶片的叶轮的系统。 联接到转子叶片的柄部的角翼包括至少一个冷却通道，其从与燃气涡轮发动机内轮空间流动连通的至少一个入口开口延伸到至少一个与燃气涡轮发动机外部流动连通的出口 转子/定子腔。 至少一个出口开口位于天使的上表面。 所述至少一个冷却通道接收从所述内轮空间引导的加压冷却空气，使得所述加压冷却空气被引导到所述至少一个入口开口中并从所述至少一个出口开口排出。

公开(公告)号：US20160186665A1

公开(公告)日：2016-06-30

申请号：US14585896

申请日：2014-12-30

Applicant: General Electric Company

Inventor： Richard William Johnson ,  Kevin Richard Kirtley ,  David Richard Johns ,  James William Vehr ,  Andrew Paul Giametta

IPC: F02C7/28 ,  F01D11/00

CPC classification number: F01D11/006 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F05D2240/81

Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.

Abstract translation: 一种燃气涡轮发动机中的涡轮，其包括定子叶片和具有形成在沟槽腔中的密封件的转子叶片。 沟槽可以包括限定在定子叶片和转子叶片的相对的内侧面之间的轴向间隙。 密封件可以包括：从定子叶片朝向转子叶片延伸的定子悬垂线，以便包括外侧边缘和内侧边缘，并且在其间限定悬垂面; 转子外侧面从平台边缘径向向内延伸，所述转子外侧面与所述突出面的至少一部分相对于所述沟槽的轴向间隙相对; 以及从转子外侧面朝向定子叶片延伸的第一轴向突起。 转子叶片的定子悬突和第一轴向凸起可被构造成轴向重叠。

公开(公告)号：US09194247B2

公开(公告)日：2015-11-24

申请号：US13676637

申请日：2012-11-14

Applicant: General Electric Company

Inventor： David Richard Johns ,  Eric David Roush

IPC: F01D5/20 ,  F01D11/02 ,  F01D11/08

CPC classification number: F01D11/02 ,  F01D11/08 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/55

Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.

Abstract translation: 密封构造包括壳体和相对于壳体旋转地安装的可旋转构件。 可旋转构件具有限定外周面的至少一个部分，其构造成在导致至少一个部分的径向尺寸增加的操作条件期间接触壳体。 所述至少一个部分具有相对的轴向表面，其中每个相对的轴向表面的尺寸轴向更靠近所述外圆周表面的径向向内的所述相对的轴向表面中的另一个，而不是所述外周边面的最远部分。

公开(公告)号：US20150118045A1

公开(公告)日：2015-04-30

申请号：US14068776

申请日：2013-10-31

Applicant: General Electric Company

Inventor： Andrew Paul Giametta ,  David Richard Johns

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/081 ,  F01D5/187 ,  F01D5/3007 ,  Y02T50/676

Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.

Abstract translation: 用于提供涡轮转子轮的冷却的系统包括转子轮，该转子轮包括围绕转子轮的外周表面周向间隔开的多个燕尾槽。 每个燕尾槽包括一对相对的上槽脚和一对相对的下槽脚。 该系统还包括至少一个涡轮叶片。 涡轮机叶片包括翼型件，平台和燕尾榫。 燕尾榫包括一对相对的上部燕尾榫和一对相对的下部燕尾榫。 燕尾还包括至少一个纵向延伸穿过的入口孔。 一对上部燕尾榫包括延伸穿过其中并与至少一个入口孔流动连通的第一冷却孔。