公开(公告)号：US20160208620A1

公开(公告)日：2016-07-21

申请号：US14915455

申请日：2014-08-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles Thistle ,  Lane Thornton

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.

Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直的部分和横向于负载方向的弯曲的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。

公开(公告)号：US10822959B2

公开(公告)日：2020-11-03

申请号：US15623787

申请日：2017-06-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Evan P. Molony ,  Carey Clum ,  Dominic J. Mongillo ,  Charles Thistle

IPC: F01D5/18 ,  B22C9/24 ,  F01D5/20 ,  B22C13/08 ,  B22C9/10 ,  B22D29/00 ,  F04D29/38 ,  F04D29/58

Abstract: A casting core may include a core body and a tip comb extending from a tip region of the core body. The tip comb may be integrally formed with the core body. The tip comb may comprise a first casting pedestal and a second casting pedestal. The first casting pedestal and the second casting pedestal may define an aperture having a tapered geometry.

公开(公告)号：US20200217208A1

公开(公告)日：2020-07-09

申请号：US16239949

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： James Tilsley Auxier ,  Jeffrey T. Morton ,  Matthew S. Gleiner ,  Parth Jariwala ,  Charles Thistle ,  Megan J. Kwolek

IPC: F01D5/18 ,  F01D25/12

Abstract: A component for a gas turbine engine includes a body portion that extends between a leading edge and a trailing edge of the component. The trailing edge includes a flared region and a non-flared region. At least one discharge slot is disposed at least partially within the flared region of the component.

公开(公告)号：US10533430B2

公开(公告)日：2020-01-14

申请号：US15362779

申请日：2016-11-28

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Mohamed Hassan

IPC: F01D5/26 ,  F01D5/22 ,  F01D5/16 ,  F01D11/00 ,  F01D25/06 ,  F01D5/02 ,  F01D5/30 ,  F04D29/08 ,  F04D29/32

Abstract: A blade for a gas turbine engine. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper seal received in the cavity, the damper seal having a main body portion that extends along a major axis of the damper seal between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion each extend towards the root when the damper seal is located in the cavity and wherein the damper seal has a variable thickness along at least a portion of a minor axis of the damper seal that extends between opposite peripheral edges of the main body portion.

公开(公告)号：US10077665B2

公开(公告)日：2018-09-18

申请号：US15009328

申请日：2016-01-28

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Mohamed Hassan

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/02 ,  F01D5/18

CPC classification number: F01D5/147 ,  F01D5/02 ,  F01D5/081 ,  F01D5/18 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/177 ,  Y02T50/676

Abstract: The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a base, a first side, and a second side, a rail extending from the base of the load beam between the first side and the second side, a tooth running parallel to the longitudinal axis disposed on the first side of the load beam. The rail may comprise at least one of, a convex sidewall having a convex curvature, a concave sidewall having a concave curvature, or a vertical sidewall extending perpendicular to the base. The rail may comprise a sidewall comprising a sidewall step wherein the sidewall has a step cut into a portion of the rail. The rail may comprise a tapered sidewall wherein the tapered sidewall extends at an angle to the base.

公开(公告)号：US20180187559A1

公开(公告)日：2018-07-05

申请号：US15397519

申请日：2017-01-03

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Mohamed Hassan

IPC: F01D5/26 ,  F01D5/30 ,  F04D29/34 ,  F04D29/66

Abstract: A blade for a gas turbine engine is disclosed herein. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint located at a peripheral edge of the platform, wherein the damper restraint is a raised feature extending along at least a portion of the peripheral edge of the platform.

公开(公告)号：US20170218776A1

公开(公告)日：2017-08-03

申请号：US15009366

申请日：2016-01-28

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Mohamed Hassan

IPC: F01D5/14 ,  F01D5/30 ,  F01D5/18

CPC classification number: F01D5/147 ,  F01D5/081 ,  F01D5/082 ,  F01D5/18 ,  F01D5/3007 ,  F01D5/3038 ,  F01D5/323 ,  F01D5/326 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/411 ,  F05D2230/53 ,  F05D2230/90 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2250/141 ,  F05D2250/712 ,  F05D2260/20 ,  F05D2260/941 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/605 ,  F05D2300/607 ,  Y02T50/676

Abstract: The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

公开(公告)号：US20160326909A1

公开(公告)日：2016-11-10

申请号：US15111517

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles Thistle ,  Lane Thornton

IPC: F01D25/12 ,  F01D11/08 ,  F02C7/12 ,  F01D5/18 ,  F02C3/10 ,  F02K3/06

CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F01D11/24 ,  F02C3/10 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/121 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

Abstract: A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.

Abstract translation: 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉，使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁，并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。