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公开(公告)号：US20180298823A1
公开(公告)日：2018-10-18
申请号：US16011737
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Matthew Andrew Hough , Jonathan Lemoine , Christopher Treat , Alberto A. Mateo
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.
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公开(公告)号：US09995171B2
公开(公告)日：2018-06-12
申请号：US14598452
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Andrew D. Burdick , Anthony P. Cherolis , Christopher Treat , Jonathan Lemoine , Robert Russell Mayer , Jorge I. Farah , John H. Mosley
CPC classification number: F01D25/12 , F01D5/02 , F01D5/081 , F01D9/065 , F01D25/125 , F01D25/162 , F01D25/26 , F02C7/12 , F05D2220/32 , F05D2260/2212 , Y02T50/673 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.
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公开(公告)号：US20160208647A1
公开(公告)日：2016-07-21
申请号：US14598492
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , John H. Mosley , Kalpendu J. Parekh , Christopher Treat , Alberto A. Mateo
CPC classification number: F01D25/14 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F02C7/12 , F05D2220/32 , F05D2260/20 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.
Abstract translation: 用于燃气涡轮发动机的中涡轮机框架包括内框架，其包括流体通道。 旋流管与流体通道流体连通，并且构造成在径向向内和向下流动的方向引导冷却气流。
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公开(公告)号：US10577971B2
公开(公告)日：2020-03-03
申请号：US15806370
申请日：2017-11-08
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.
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公开(公告)号：US10392974B2
公开(公告)日：2019-08-27
申请号：US14612469
申请日：2015-02-03
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Alexander Broulidakis , Paul K. Sanchez , Anthony P. Cherolis , Joseph J. Sedor , Christopher Treat
Abstract: A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.
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Patent Agency Ranking
公开(公告)号：US10036503B2
公开(公告)日：2018-07-31
申请号：US14685118
申请日：2015-04-13
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Alexander Broulidakis , Matthew A. Hough , Jonathan Lemoine , Christopher Treat
IPC: F16L55/00 , F01D9/06 , F16L21/035
CPC classification number: F16L55/00 , F01D9/065 , F05D2240/58 , F05D2300/43 , F16L21/035
Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.
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公开(公告)号：US20180087402A1
公开(公告)日：2018-03-29
申请号：US15806370
申请日：2017-11-08
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
CPC classification number: F01D25/145 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F01D25/243 , F01D25/28 , F05D2260/20 , Y02T50/672 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.
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公开(公告)号：US09920651B2
公开(公告)日：2018-03-20
申请号：US14598492
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , John H. Mosley , Kalpendu J. Parekh , Christopher Treat , Alberto A. Mateo
CPC classification number: F01D25/14 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F02C7/12 , F05D2220/32 , F05D2260/20 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. At least one spoke includes an inlet passage with at least one branch extending in an axial direction in fluid communication with the fluid passage in the inner frame case. A fitting fluidly connects the at least one branch to the fluid passage in the inner frame case. The fitting also includes a transfer tube connecting the cooling airflow passage to a cup boss. The transfer tube is fixed relative to the cylindrical portion and moveable relative to the cup boss. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.
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公开(公告)号：US20160298472A1
公开(公告)日：2016-10-13
申请号：US14685118
申请日：2015-04-13
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Alexander Broulidakis , Matthew A. Hough , Jonathan Lemoine , Christopher Treat
CPC classification number: F16L55/00 , F01D9/065 , F05D2240/58 , F05D2300/43 , F16L21/035
Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.
Abstract translation: 本公开的方面针对被配置为传送流体，发动机的凸台和联接到管和凸起中的至少一个的垫片的飞行器的发动机的管，所述垫被配置为保持间隙 管和发动机组装时的老板。
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公开(公告)号：US20160222827A1
公开(公告)日：2016-08-04
申请号：US14612469
申请日：2015-02-03
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Alexander Broulidakis , Paul K. Sanchez , Anthony P. Cherolis , Joseph J. Sedor , Christopher Treat
CPC classification number: F01D25/28 , F01D5/02 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/26 , F02C7/12 , F05D2220/32 , F05D2220/3213 , F05D2240/24 , F05D2260/20 , F05D2260/31 , Y02T50/676
Abstract: A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.
Abstract translation: 紧固件组件包括包括衬套开口的第一部件。 第二部件包括紧固件开口。 螺纹衬套至少部分地位于衬套开口内。 紧固件延伸穿过紧固件开口并接合衬套。
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