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公开(公告)号：US20160047259A1
公开(公告)日：2016-02-18
申请号：US14783054
申请日：2014-04-11
Applicant: United Technologies Corporation
Inventor： Anton G. Banks , Anthony P. Cherolis , Donald Kastel
CPC classification number: F01D11/005 , F01D9/02 , F01D9/04 , F01D9/041 , F01D9/047 , F01D11/00 , F01D11/003 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/128 , F05D2240/55 , F05D2240/57 , F05D2260/20 , F05D2260/97
Abstract: A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot.
Abstract translation: 用于燃气涡轮发动机的喷嘴段包括弓形外叶片平台段。 与弓形外叶片平台段间隔开的弧形内叶片平台段。 弧形内叶片平台段与弧形外叶片平台段之间的多个翼型，弓形外叶片平台段包括扇贝槽和密封扇贝槽的密封件。
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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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公开(公告)号：US10309308B2
公开(公告)日：2019-06-04
申请号：US14598732
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Jeffrey J. Lienau , Robert Newman , Cheng-Zhang Wang
Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.
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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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Patent Agency Ranking
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：US09915171B2
公开(公告)日：2018-03-13
申请号：US14598474
申请日：2015-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joshua Daniel Winn , Anthony P. Cherolis
CPC classification number: F01D25/14 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F05D2220/32
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 a cooling airflow passage that extends in a radial direction and an axial direction, an elongated cylindrical portion, and a flange.
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公开(公告)号：US09732628B2
公开(公告)日：2017-08-15
申请号：US14663495
申请日：2015-03-20
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Joshua Daniel Winn , Jonathan Lemoine
CPC classification number: F01D25/125 , F01D9/065 , F01D25/12 , F01D25/162 , F02C7/06 , F02C7/18 , F05D2220/3213 , F05D2260/14 , F05D2260/20 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.
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公开(公告)号：US20160376925A1
公开(公告)日：2016-12-29
申请号：US14662347
申请日：2015-03-19
Applicant: United Technologies Corporation
Inventor： Seth A. Max , Anthony P. Cherolis , Steven D. Porter , Joshua D. Winn , Gregory E. Reinhardt , Jeffrey J. Lienau
CPC classification number: F01D25/28 , F01D11/003 , F01D11/006 , F01D25/24 , F01D25/243 , F05D2220/32 , F05D2230/00 , F05D2230/60 , F05D2240/55 , F05D2240/60 , F05D2260/97
Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.
Abstract translation: 用于涡轮机的密封支撑结构包括成形为安装到涡轮机的固定结构的安装部分和设置在从安装部分轴向延伸的安装部分上的圆柱形腿部。 圆柱形腿部可以包括径向延伸的凸缘。 凸缘可以从圆柱形腿部的端部以90度的角度延伸。 凸缘可以在轴向方向上至少部分地延伸。 圆筒形腿部可以与安装部一体地形成。 在实施例中，圆柱形腿部不与安装部分成一体，即，圆柱形腿部是与安装部分接合的分离件。
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