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公开(公告)号：US11136995B2
公开(公告)日：2021-10-05
申请号：US16376445
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Pedro Rivero , Matthew Andrew Hough
Abstract: A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a hot fairing structure adjacent to the exit guide vane ring to define a multiple of diffusion passages around the engine longitudinal axis; an outer radial interface between a radial outer surface of the hot fairing structure and the exit guide vane ring, the outer radial interface being a full hoop structure; and an anti-rotation feature between the hot fairing structure and the exit guide vane ring, the anti-rotation features inboard of the multiple of diffusion passages.
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公开(公告)号：US10301958B2
公开(公告)日：2019-05-28
申请号：US15021945
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
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公开(公告)号：US20160230666A1
公开(公告)日：2016-08-11
申请号：US14617109
申请日：2015-02-09
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Matthew Andrew Hough , Jonathan Lemoine , Christopher Treat , Alberto A. Mateo
CPC classification number: F02C7/20 , F01D5/081 , F02C7/12 , F05D2230/64 , F05D2260/14 , F05D2260/30 , F05D2260/36 , Y02T50/676
Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.
Abstract translation: 用于燃气涡轮发动机的冷却结构包括限定冷却腔的燃气涡轮发动机结构。 冷却部件构造成将冷却流沿所需方向引导到冷却腔中。 支架支撑冷却部件并且具有附接接口以将支架固定到燃气涡轮发动机结构。 与支架相关联的第一个定向功能。 第二定向特征与燃气涡轮发动机结构相关联。 第一和第二取向特征彼此配合以确保冷却部件仅相对于燃气涡轮发动机结构安装在一个方位上。 还公开了一种燃气涡轮发动机和安装冷却结构的方法。
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公开(公告)号：US11371704B2
公开(公告)日：2022-06-28
申请号：US16376448
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Matthew Andrew Hough , Pedro Rivero
Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.
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公开(公告)号：US10794207B2
公开(公告)日：2020-10-06
申请号：US15022025
申请日：2014-09-11
Applicant: United Technologies Corporation
Inventor： Matthew Andrew Hough
Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.
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Patent Agency Ranking
公开(公告)号：US10563525B2
公开(公告)日：2020-02-18
申请号：US15038536
申请日：2014-11-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.
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公开(公告)号：US20190316475A1
公开(公告)日：2019-10-17
申请号：US16427870
申请日：2019-05-31
Applicant: United Technologies Corporation
Inventor： Matthew Andrew Hough , Jeffrey S. Beattie
IPC: F01D5/18
Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed.
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公开(公告)号：US10364682B2
公开(公告)日：2019-07-30
申请号：US15021991
申请日：2014-08-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Jeffrey S. Beattie
IPC: F01D5/18
Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.
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公开(公告)号：US20160230581A1
公开(公告)日：2016-08-11
申请号：US15022025
申请日：2014-09-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough
CPC classification number: F01D11/006 , F01D5/081 , F01D5/187 , F01D5/225 , F01D5/3007 , F01D9/041 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2240/81 , F05D2250/323
Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.
Abstract translation: 燃气涡轮发动机部件阵列包括各自具有平台的第一和第二部件。 平台彼此相邻布置并提供间隙。 密封件周向地布置在第一和第二部件之间并且与平台接合以阻碍间隙。 在密封件中设置有冷却孔，并且与间隙流体连通。 冷却孔朝向间隙具有增加的锥度。
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公开(公告)号：US20160222808A1
公开(公告)日：2016-08-04
申请号：US15021944
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Jeffrey Beattie
CPC classification number: F01D11/006 , F01D5/081 , F01D5/3015 , F01D11/003 , F01D11/005 , F01D11/008 , F01D11/02 , F01D25/12 , F05D2240/127 , F05D2240/55 , F05D2260/20 , F05D2260/2212
Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumcumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.
Abstract translation: 燃气涡轮发动机包括具有可绕轴线旋转的盘的涡轮部分。 盘具有周向间隔开的叶片安装特征和在叶片安装特征之间周向延伸的径向外边缘表面。 涡轮叶片围绕盘安装在叶片安装特征中。 密封件邻近径向外边缘表面布置在盘的径向外侧，使得在密封件和径向外边缘表面之间存在相应的通道。 径向外边缘表面包括延伸到相应通道中的径向延伸的突起。
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