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公开(公告)号：US10132193B2
公开(公告)日：2018-11-20
申请号：US14911287
申请日：2014-08-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Michael S. Stevens
Abstract: A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.
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公开(公告)号：US20180252165A1
公开(公告)日：2018-09-06
申请号：US15688251
申请日：2017-08-28
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Todd M. LaPierre , Richard K. Hayford
IPC: F02C7/36 , F02C3/107 , F02K3/06 , F16H1/46 , F16H57/025 , F16H57/028
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.
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公开(公告)号：US10036271B2
公开(公告)日：2018-07-31
申请号：US14994208
申请日：2016-01-13
Applicant: United Technologies Corporation
Inventor： Kevin J. Ryan , Terence P. Tyler, Jr. , Ken F. Blaney
CPC classification number: F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/11 , F05D2250/231 , F05D2250/232 , F05D2250/74 , F05D2260/202 , Y02T50/673 , 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.
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公开(公告)号：US20180119560A1
公开(公告)日：2018-05-03
申请号：US15339581
申请日：2016-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jose R. Paulino , Ken F. Blaney , Terence P. Tyler, JR. , Daniel S. Rogers , Anthony B. Swift , Thomas E. Clark
CPC classification number: F01D11/10 , F01D9/02 , F01D11/003 , F01D11/14 , F01D25/14 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/55 , Y02T50/672 , Y02T50/675
Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.
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公开(公告)号：US09752451B2
公开(公告)日：2017-09-05
申请号：US13719584
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Paul M. Lutjen
CPC classification number: F01D11/24
Abstract: An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment.
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Patent Agency Ranking
公开(公告)号：US09745898B2
公开(公告)日：2017-08-29
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: F16H57/025 , F02C7/36 , F02K3/06 , F02C3/107 , F16H1/46 , F16H57/028
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.
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27.发明申请公开(公告)号：US20160369644A1
公开(公告)日：2016-12-22
申请号：US14903836
申请日：2014-05-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Christppher M. Jarochym
Abstract: An active clearance control system for a gas turbine engine includes an annular piston with a multiple of piston lift lugs. A method of active blade tip clearance control for a gas turbine engine includes translating axial movement of an annular piston to radial movement of a multiple of blade outer air seal segments.
Abstract translation: 用于燃气涡轮发动机的主动间隙控制系统包括具有多个活塞提升凸耳的环形活塞。 用于燃气涡轮发动机的主动叶片顶端间隙控制的方法包括将环形活塞的轴向运动平移到多个叶片外部空气密封段的径向移动。
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公开(公告)号：US20160312644A1
公开(公告)日：2016-10-27
申请号：US15105220
申请日：2014-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Richard K. Hayford , Christopher M. Jarochym
Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
Abstract translation: 用于燃气涡轮发动机的示例性主动间隙控制系统包括致动器和限定被配置为接收致动器的孔的壳体壁部分。 致动器构造成移动空气密封段，并且致动器可通过壳体壁部分的径向外侧插入孔内的安装位置。
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29.发明申请GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM WITH AIR SEAL SEGMENT INTERFACE 审中-公开气体涡轮发动机快速响应空气密封部分接口的间隙控制系统公开(公告)号：US20160053626A1
公开(公告)日：2016-02-25
申请号：US14780838
申请日：2014-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Paul M. Lutjen , Brian R. Pelletier
IPC: F01D11/20
CPC classification number: F01D11/20 , F01D11/22 , F04D29/164 , F04D29/526
Abstract: An active clearance control system of a gas turbine engine includes an air seal segment with a bridge hook having a lugged aperture.
Abstract translation: 燃气涡轮发动机的主动间隙控制系统包括具有带钩状孔的桥钩的空气密封段。
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公开(公告)号：US10968772B2
公开(公告)日：2021-04-06
申请号：US16042096
申请日：2018-07-23
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.
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