公开(公告)号：US10927710B2

公开(公告)日：2021-02-23

申请号：US16142515

申请日：2018-09-26

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark ,  Daniel J. Whitney

IPC: F01D25/24 ,  F01D11/08 ,  F01D25/00

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

公开(公告)号：US10920601B2

公开(公告)日：2021-02-16

申请号：US16520874

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Jose R. Paulino ,  Ken F. Blaney

IPC: F01D11/08 ,  B22C9/10 ,  F01D11/24 ,  B22C9/24

Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets. A sacrificial structure for forming internal cooling passages within a blade outer air seal and a method of cooling an interface between a blade outer air seal and a rotating blade array is also disclosed.

公开(公告)号：US10697303B2

公开(公告)日：2020-06-30

申请号：US14785119

申请日：2014-04-22

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Richard K. Hayford

IPC: F01D5/16 ,  B22F3/105 ,  B22F5/04 ,  F01D5/18 ,  F01D9/04 ,  F01D25/06 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  B23K26/342 ,  B23K15/00

Abstract: An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

公开(公告)号：US20200072084A1

公开(公告)日：2020-03-05

申请号：US16122481

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D25/24 ,  F01D11/08 ,  F01D11/00

Abstract: A blade outer air seal assembly contains a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The support structure has a first support member that engages a first axial side of the blade outer air seal. A second support member engages a second axial side of the blade outer air seal. A retaining clip secures the blade outer air seal to the support structure. The retaining clip has a first leg and a second leg that extends in a generally radial direction. The first leg abuts the first axial side and the second leg abuts the first support member.

公开(公告)号：US20200003422A1

公开(公告)日：2020-01-02

申请号：US16566061

申请日：2019-09-10

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Stephen K. Kramer

IPC: F23R3/28 ,  F02C7/236 ,  F02C3/04

Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.

公开(公告)号：US10018068B2

公开(公告)日：2018-07-10

申请号：US14596152

申请日：2015-01-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peter J. Milligan ,  Paul M. Lutjen ,  Ken F. Blaney ,  Thurman C. Dabbs ,  Kevin J. Ryan

IPC: F01D11/24

CPC classification number: F01D11/24 ,  F05D2240/11 ,  F05D2250/74 ,  Y02T50/673

Abstract: A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P′ which is at the center of an arc W′ and co-planer with a machined surface V′.

公开(公告)号：US20170198603A1

公开(公告)日：2017-07-13

申请号：US14994186

申请日：2016-01-13

Applicant: United Technologies Corporation

Inventor： Kevin J. Ryan ,  Terence P. Tyler, JR. ,  Ken F. Blaney

IPC: F01D25/12 ,  F01D11/08 ,  F01D5/12 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08 ,  F01D25/246 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2250/232 ,  F05D2260/202 ,  Y02T50/676

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

公开(公告)号：US20160194979A1

公开(公告)日：2016-07-07

申请号：US14911123

申请日：2014-08-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ken F. Blaney

IPC: F01D25/12 ,  F01D5/12 ,  F01D11/08 ,  F01D5/02

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08 ,  F01D11/10 ,  F01D11/18 ,  F01D11/24 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20

Abstract: A blade outer air seal segment has an inner surface and an outer surface. The outer surface is in communication with a cooling air source. The segment also has a first end having a first surface extending from the inner surface and a first angled surface extending from the first surface, and a second end having a second surface extending from the inner surface and a second angled surface extending from the second surface.

Abstract translation: 叶片外部空气密封段具有内表面和外表面。 外表面与冷却空气源连通。 该段还具有第一端，其具有从内表面延伸的第一表面和从第一表面延伸的第一倾斜表面，以及具有从内表面延伸的第二表面的第二端和从第二表面延伸的第二倾斜表面 。

公开(公告)号：US20160194974A1

公开(公告)日：2016-07-07

申请号：US14910899

申请日：2014-08-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ken F. Blaney ,  Brian R. Pelletier ,  James N. Knapp

IPC: F01D11/08 ,  F01D25/28

CPC classification number: F01D11/08 ,  F01D11/24 ,  F01D21/045 ,  F01D25/246 ,  F01D25/28 ,  F04D29/164 ,  F05D2220/32 ,  F05D2240/11

Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The BOAS further includes at least one radial standoff axially aligned with the at least one attachment hook.

Abstract translation: 本公开涉及一种燃气涡轮发动机，其包括叶片外部空气密封（BOAS），其具有邻近其前缘和后缘中的一个的至少一个附接钩。 所述BOAS还包括与所述至少一个附接钩轴向对准的至少一个径向支座。

公开(公告)号：US20160177841A1

公开(公告)日：2016-06-23

申请号：US14974994

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Todd M. LaPierre ,  Richard K. Hayford

IPC: F02C7/36 ,  F16H57/028 ,  F16H57/025 ,  F16H1/46

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311 ,  F16H1/46 ,  F16H57/025 ,  F16H57/028 ,  Y02T50/671

Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.

Abstract translation: 用于涡轮机的行星齿轮系统包括前行星齿轮组件，其包括多个向前行星齿轮，所述前行星齿轮啮合到设置在动力轴上的前方太阳轮和与前行星齿轮啮合的前齿圈和后行星齿轮组 前行星组件包括与设置在动力轴上的后方太阳齿轮啮合的多个后行星齿轮和与后行星齿轮啮合的后轮齿轮。 该系统还包括设置在前行星齿轮组件和后行星齿轮组件之间的齿轮壳体。 齿轮壳体包括固定支架，其中前行星齿轮和后行星齿轮可旋转地安装到固定支架上，以及从固定支架径向延伸的安装件，其可连接到涡轮机的固定部分。