公开(公告)号：US10399189B2

公开(公告)日：2019-09-03

申请号：US15289801

申请日：2016-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Eric A. Hudson ,  Alan C. Barron ,  Edwin Otero

IPC: B23P15/02 ,  F01D5/00 ,  F01D5/14

Abstract: A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.

公开(公告)号：US20190010810A1

公开(公告)日：2019-01-10

申请号：US16126482

申请日：2018-09-10

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Jaimie Schweitzer ,  Jonathan Perry Sandoval ,  Edwin Otero ,  Kyle C. Lana ,  Scott D. Virkler

IPC: F01D5/22 ,  F01D5/30 ,  F01D11/00

Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

公开(公告)号：US09963991B2

公开(公告)日：2018-05-08

申请号：US14852819

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John W. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Edwin Otero ,  Alan W. Stoner

IPC: F01D11/08 ,  F01D11/00 ,  F01D11/02 ,  F16J15/3288 ,  F16J15/44 ,  F01D5/02 ,  F01D25/28 ,  F16J15/3268

CPC classification number: F01D11/08 ,  F01D5/02 ,  F01D11/001 ,  F01D11/025 ,  F01D25/28 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3268 ,  F16J15/3288 ,  F16J15/442

Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.

公开(公告)号：US09726023B2

公开(公告)日：2017-08-08

申请号：US14605366

申请日：2015-01-26

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Edwin Otero ,  Daniel A. Snyder ,  Jaimie Taraskevich ,  Di Wu

IPC: F01D5/18 ,  F01D5/14 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D5/187 ,  F01D5/147 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/22141 ,  Y02T50/676

Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

公开(公告)号：US20160222796A1

公开(公告)日：2016-08-04

申请号：US15022640

申请日：2014-09-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Edwin Otero

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/189 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2300/606

Abstract: A blade includes a platform and a monolithic airfoil extending from the platform to a tip. The airfoil includes a first wall extending from a leading edge to a trailing edge, a second wall extending from the leading edge to the trailing edge and joined to the first wall at the leading edge, and at least one rib extending from the first wall to the second wall. The at least one rib and the first and second walls define a cavity. The blade also includes a baffle positioned within the cavity. The baffle has walls that are separate and distinct from and not attached to the at least one rib and the first and second walls of the airfoil. A method for forming a blade includes forming a platform and forming an airfoil and a baffle within the airfoil on a layer-by-layer basis using additive manufacturing.

Abstract translation: 叶片包括平台和从平台延伸到尖端的整体翼型件。 翼型件包括从前缘延伸到后缘的第一壁，从前缘延伸到后缘并在前缘处连接到第一壁的第二壁以及从第一壁延伸到至少一个肋 第二个墙。 所述至少一个肋和所述第一壁和所述第二壁限定空腔。 叶片还包括位于腔内的挡板。 挡板具有与所述翼型件的至少一个肋部以及翼型件的第一和第二壁分开并且不连接的壁。 用于形成叶片的方法包括使用添加剂制造在层叠的基础上形成平台并在翼型内形成翼型和挡板。

公开(公告)号：US20160130963A1

公开(公告)日：2016-05-12

申请号：US14830636

申请日：2015-08-19

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  Edwin Otero ,  John E. Paul

IPC: F01D11/00 ,  F02C7/28 ,  F16J15/44 ,  F02C3/04

CPC classification number: F01D11/001 ,  F01D11/025 ,  F05D2240/55 ,  F05D2260/38 ,  F05D2260/96 ,  F16J15/44

Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.

Abstract translation: 本公开总体上涉及一种具有由至少两个梁支撑的鞋的静水超前低泄漏密封件。 防振梁隔离件设置成与两个相邻的梁接触并且可操作以减轻外部感应的梁的振动响应。

公开(公告)号：US10443450B2

公开(公告)日：2019-10-15

申请号：US14921533

申请日：2015-10-23

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Alan W. Stoner ,  Edwin Otero

IPC: F01D25/28 ,  F16J15/16 ,  F01D5/22 ,  F01D5/24 ,  F01D5/26 ,  F01D5/28 ,  F01D9/02 ,  F01D9/04 ,  F01D11/00 ,  F01D11/12 ,  F01D25/24

Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

公开(公告)号：US10436051B2

公开(公告)日：2019-10-08

申请号：US14921503

申请日：2015-10-23

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Alan W. Stoner ,  Edwin Otero

IPC: F01D11/00 ,  F16J15/16 ,  F01D9/04 ,  F01D11/02 ,  F01D11/12

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

公开(公告)号：US20180099362A1

公开(公告)日：2018-04-12

申请号：US15289801

申请日：2016-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Eric A. Hudson ,  Alan C. Barron ,  Edwin Otero

IPC: B23P15/02 ,  F01D5/14

CPC classification number: B23P15/02 ,  F01D5/005 ,  F01D5/141 ,  F05D2220/32 ,  F05D2230/10 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49337

Abstract: A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.

公开(公告)号：US20160201477A1

公开(公告)日：2016-07-14

申请号：US14914084

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Edwin Otero ,  Kyle C. Lana

IPC: F01D5/18 ,  F01D25/12 ,  F01D11/08 ,  F01D25/30 ,  F23R3/00 ,  F01D9/04

Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.

Abstract translation: 燃气涡轮发动机部件包括间隔开的壁，其提供沿第一方向延伸的冷却通道。 交叉肋连接壁并沿第一方向延伸。 交叉肋具有沿与第一方向横切的第二方向延伸的孔。 至少一个基座的一排连接壁并沿第一方向延伸。 行和交叉肋在第二方向上彼此重叠。