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公开(公告)号：US11377967B2
公开(公告)日：2022-07-05
申请号：US16705451
申请日：2019-12-06
Applicant: United Technologies Corporation
Inventor： Vladimir Skidelsky , Carlos Calixtro , Matthew B. DeGostin , John E. Paul , Mohamed Hassan , Charles Thistle , Jeffrey Michael Jacques
Abstract: A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.
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公开(公告)号：US09963991B2
公开(公告)日：2018-05-08
申请号：US14852819
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John W. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Edwin Otero , Alan W. Stoner
IPC: F01D11/08 , F01D11/00 , F01D11/02 , F16J15/3288 , F16J15/44 , F01D5/02 , F01D25/28 , F16J15/3268
CPC classification number: F01D11/08 , F01D5/02 , F01D11/001 , F01D11/025 , F01D25/28 , F05D2220/32 , F05D2240/56 , F16J15/3268 , F16J15/3288 , F16J15/442
Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.
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公开(公告)号：US20160130963A1
公开(公告)日：2016-05-12
申请号：US14830636
申请日：2015-08-19
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , Edwin Otero , John E. Paul
CPC classification number: F01D11/001 , F01D11/025 , F05D2240/55 , F05D2260/38 , F05D2260/96 , F16J15/44
Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.
Abstract translation: 本公开总体上涉及一种具有由至少两个梁支撑的鞋的静水超前低泄漏密封件。 防振梁隔离件设置成与两个相邻的梁接触并且可操作以减轻外部感应的梁的振动响应。
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公开(公告)号：US20200025293A1
公开(公告)日：2020-01-23
申请号：US16243632
申请日：2019-01-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Ross Wilson , Edwin Otero , Alan W. Stoner
Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.
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公开(公告)号：US20190331003A1
公开(公告)日：2019-10-31
申请号：US16455093
申请日：2019-06-27
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Alan W. Stoner , Edwin Otero
IPC: F01D25/28 , F01D25/24 , F01D11/12 , F01D11/00 , F01D9/04 , F01D9/02 , F01D5/28 , F01D5/24 , F01D5/22 , F16J15/16 , F01D5/26
Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
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Patent Agency Ranking
公开(公告)号：US10385705B2
公开(公告)日：2019-08-20
申请号：US15147954
申请日：2016-05-06
Applicant: United Technologies Corporation
Inventor： Peter Balawajder , Benjamin F. Hagan , Jeffrey Michael Jacques
Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
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公开(公告)号：US10443450B2
公开(公告)日：2019-10-15
申请号：US14921533
申请日：2015-10-23
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Alan W. Stoner , Edwin Otero
IPC: F01D25/28 , F16J15/16 , F01D5/22 , F01D5/24 , F01D5/26 , F01D5/28 , F01D9/02 , F01D9/04 , F01D11/00 , F01D11/12 , F01D25/24
Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
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公开(公告)号：US10436051B2
公开(公告)日：2019-10-08
申请号：US14921503
申请日：2015-10-23
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Alan W. Stoner , Edwin Otero
Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.
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公开(公告)号：US10301951B2
公开(公告)日：2019-05-28
申请号：US15160216
申请日：2016-05-20
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Jeffrey Michael Jacques , Daniel Belotto
Abstract: A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.
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公开(公告)号：US10018062B2
公开(公告)日：2018-07-10
申请号：US14790589
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Ryan Alan Waite , Jeffrey Michael Jacques , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D9/02 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/20 , F16L9/006 , Y02T50/675
Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.
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