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公开(公告)号：EP3719259A1
公开(公告)日：2020-10-07
申请号：EP20166491.9
申请日：2020-03-27
Applicant: United Technologies Corporation
Inventor： MCCAFFREY, Michael G. , RIVERO, Pedro , HOUGH, Matthew Andrew
Abstract: A pre-diffuser (100) for a gas turbine engine (20) includes an exit guide vane ring (104) having a multiple of exit guide vanes (108) defined around an engine longitudinal axis (A), a hot fairing structure (102) adjacent to the exit guide vane ring (10) to define a multiple of diffusion passages (120) around the engine longitudinal axis (A), an outer radial interface (190) between a radial outer surface of the hot fairing structure (102) and the exit guide vane ring (104), the outer radial interface (190) being a full hoop structure, and an anti-rotation feature (130) between the hot fairing structure (120) and the exit guide vane ring (104), the anti-rotation feature (130) inboard of the multiple of diffusion passages (120).
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公开(公告)号：EP3712504A1
公开(公告)日：2020-09-23
申请号：EP20153235.5
申请日：2020-01-22
Applicant: United Technologies Corporation
Inventor： HOUGH, Matthew Andrew , TU, John S , HARMON, Stephen C , CROTEAU, Paul F , HANSON, Russell B , RATHGEB, Joshua C
Abstract: A diffuser case assembly for a gas turbine engine includes a fairing (48) disposed circumferentially about a longitudinal axis (24). The fairing (48) defines a plurality of passages (52) circumferentially spaced apart and forming at least a portion of a fluid path (C) between a compressor (40) and a combustor (44) of the gas turbine engine. A diffuser frame (58) includes a plurality of struts (62). Each of the plurality of struts (62) is disposed between a pair of adjacent passages of the plurality of passages (52). The diffuser frame (58) is configured to couple an inner diffuser case (54) to an outer diffuser case (56).
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公开(公告)号：EP2956627B1
公开(公告)日：2018-07-25
申请号：EP14797049.5
申请日：2014-02-07
Applicant: United Technologies Corporation
Inventor： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC classification number: F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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14.发明公开
公开(公告)号：EP2956627A2
公开(公告)日：2015-12-23
申请号：EP14797049.5
申请日：2014-02-07
Applicant: United Technologies Corporation
Inventor： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC classification number: F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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公开(公告)号：EP3052762A2
公开(公告)日：2016-08-10
申请号：EP14861286.4
申请日：2014-09-17
Applicant: United Technologies Corporation
Inventor： BEATTIE, Jeffrey S. , HIMES, Jason D. , HOUGH, Matthew Andrew , CORCORAN, Christopher
CPC classification number: F01D5/081 , F01D5/082 , F01D5/085 , F01D5/12 , F01D5/187 , F01D5/3007 , F01D5/3015 , F05D2220/32 , F05D2240/81 , F05D2260/20
Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.
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Patent Agency Ranking
公开(公告)号：EP3049633A1
公开(公告)日：2016-08-03
申请号：EP14848566.7
申请日：2014-08-14
Applicant: United Technologies Corporation
Inventor： THORNTON, Lane , HOUGH, Matthew Andrew
CPC classification number: F01D5/186 , F01D5/187 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2250/292 , F05D2250/324 , Y02T50/676
Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.
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公开(公告)号：EP3047102A2
公开(公告)日：2016-07-27
申请号：EP14843390.7
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： HOUGH, Matthew Andrew , BEATTIE, Jeffrey S.
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 circumferentially 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.
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公开(公告)号：EP3047102B1
公开(公告)日：2020-05-06
申请号：EP14843390.7
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： HOUGH, Matthew Andrew , BEATTIE, Jeffrey S.
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公开(公告)号：EP3054092A1
公开(公告)日：2016-08-10
申请号：EP16154790.6
申请日：2016-02-09
Applicant: United Technologies Corporation
Inventor： ZACCHERA, Kevin , HOUGH, Matthew Andrew , LEMOINE, Jonathan , TREAT, Christopher , MATEO, Alberto
IPC: F01D5/08
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 96, 102 associated with the bracket. A second orientation feature 104, 106 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。 冷却部件被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，并具有用于将支架固定到燃气涡轮发动机结构的附接接口。 与支架相关联的第一定位特征96,102。 第二取向特征104,106与燃气涡轮发动机结构相关联。 第一和第二定向特征相互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一种安装冷却结构的方法。
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20.发明公开
公开(公告)号：EP3047112A2
公开(公告)日：2016-07-27
申请号：EP14859577.0
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： HOUGH, Matthew Andrew , CORCORAN, Christopher , BEATTIE, Jeffrey S.
CPC classification number: F01D11/006 , F01D5/22 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/75 , F05D2260/22141
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.
Abstract translation: 燃气涡轮发动机包括涡轮部分。 涡轮部分包括可围绕轴线旋转的盘。 多个涡轮叶片安装在圆周周围，多个密封件布置在涡轮叶片与圆周之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。
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