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公开(公告)号：US10309253B2
公开(公告)日：2019-06-04
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
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：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：US20190128134A1
公开(公告)日：2019-05-02
申请号：US15798763
申请日：2017-10-31
Applicant: United Technologies Corporation
Inventor： Terence P. Tyler , Thurman Carlo Dabbs , Kevin J. Ryan , Nathan K. Galle
Abstract: A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.
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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′.
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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
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.
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Patent Agency Ranking
公开(公告)号：US20170335706A1
公开(公告)日：2017-11-23
申请号：US15157857
申请日：2016-05-18
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Paul M. Lutjen , Kevin J. Ryan
CPC classification number: F01D11/08 , B22C9/103 , F01D5/06 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2230/21 , F05D2240/11 , F05D2240/35 , F05D2260/232 , Y02T50/675
Abstract: A core assembly for fabricating an air cooled engine component for a gas turbine engine includes an end portion for defining passages within a side of an engine component. The end portion defines a first cross-section. A middle portion is spaced apart from the end portion and defines passages through a middle part of the engine component. The middle portion defines a second cross-section. One of the first cross-section and the second cross-section includes a first height greater than a second height. An air cooled engine component for a gas turbine engine and a gas turbine engine are also disclosed.
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公开(公告)号：US20170198599A1
公开(公告)日：2017-07-13
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：US10145257B2
公开(公告)日：2018-12-04
申请号：US14885278
申请日：2015-10-16
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Paul M. Lutjen , Kevin J. Ryan , Ken F. Blaney
Abstract: According to various embodiments, disclosed is a blade outer air seal assembly for a turbine engine comprising a main body portion that extends generally axially, with respect to a central axis of the turbine engine, from a leading edge portion of the main body to a trailing edge portion of the main body, wherein the leading edge portion includes a leading edge wall having a undercut profile along at least a portion of the leading edge wall, wherein the main body portion comprises cooling passages comprising a leading edge cooling passage adjacent to the leading edge wall, having a leading edge periphery on a side of the leading edge cooling passage adjacent to the leading edge wall, which generally conforms to the undercut profile of the leading edge wall.
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公开(公告)号：US20160201467A1
公开(公告)日：2016-07-14
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
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′.
Abstract translation: 用于涡轮机的叶片外部空气密封件（BOAS）可以包括BOAS主体，其包括基本上符合本文表1所示的一组笛卡尔坐标定义的多个冷却孔，其中笛卡尔坐标相对于 点P位于圆弧W的中心并具有加工表面V的共同平面机。用于涡轮机的叶片外部空气密封（BOAS）可以包括BOAS主体，其包括基本上符合设定的多个冷却孔 的笛卡尔坐标，其中相对于位于弧W'中心的点P'提供笛卡尔坐标，并且具有加工表面V'的共刨床。
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公开(公告)号：US20160169020A1
公开(公告)日：2016-06-16
申请号：US14908225
申请日：2014-07-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kevin J. Ryan , Karl A. Mentz , Mark J. Rogers
CPC classification number: F01D11/005 , F01D9/041 , F01D11/003 , F01D11/08 , F04D29/083 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/24 , F05D2250/232 , F05D2260/98 , F05D2300/17 , F05D2300/611 , F16J15/0887 , F16J15/28
Abstract: A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces. The first and second sealing rings slideably engage one another at a sliding wedge interface.
Abstract translation: 用于燃气涡轮发动机的密封组件装置包括分别提供第一和第二面的第一和第二非旋转结构。 密封组件包括分别与第一和第二表面接合的第一和第二密封环。 第一和第二密封环在滑动楔形界面处可滑动地彼此接合。
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