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公开(公告)号：US10883370B2
公开(公告)日：2021-01-05
申请号：US16103138
申请日：2018-08-14
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Ross Wilson
Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.
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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：US20190017607A1
公开(公告)日：2019-01-17
申请号：US15651081
申请日：2017-07-17
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson
CPC classification number: F16J15/442 , F01D5/03 , F01D11/025 , F01D11/14 , F02C3/14 , F05D2220/323 , F05D2240/55 , F16J15/441 , F16J15/445
Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.
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公开(公告)号：US09995163B2
公开(公告)日：2018-06-12
申请号：US15256134
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson , Joey Wong , Christpher J. Peters
IPC: F16J15/447 , F01D11/04 , F04D29/08
CPC classification number: F01D11/04 , F01D11/00 , F01D11/001 , F01D11/025 , F04D29/083 , F05D2220/32 , F05D2230/237 , F05D2230/238 , F16J15/44 , F16J15/442
Abstract: A seal sub-assembly may comprise a spacer, at least one secondary seal, and a secondary seal cover. At least a portion of the at least one secondary seal are located axially between the spacer and the secondary seal cover. The spacer is attached to the secondary seal cover. The spacer may comprise a first flange and a second flange. The at least one secondary seal may be located axially in line with and radially inward from the first flange. At least a portion of the secondary seal cover may be located axially in line with and radially inward from the second flange.
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Patent Agency Ranking
公开(公告)号：US20180058229A1
公开(公告)日：2018-03-01
申请号：US15253957
申请日：2016-09-01
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson
Abstract: A component retaining assembly includes a housing including a circumferential slot. A component is mated to the housing. The component includes a first face including at least two tabs. The at least two tabs extending at outward from the first face at least partially past a portion of the circumferential slot. A retaining ring is disposed within the circumferential slot and abuts the first face of the component. The at least two tabs overlap a portion of the retaining ring. A gas turbine engine and a method are also disclosed.
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公开(公告)号：US20170044908A1
公开(公告)日：2017-02-16
申请号：US14826831
申请日：2015-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David Richard Griffin , Ross Wilson , Zachary Mott , Dwayne K. Mecklenburg , Michael Lastrina
CPC classification number: F01D5/187 , F01D5/082 , F01D5/147 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/202
Abstract: A rotor assembly for a gas turbine engine includes a rotor disc having an axially extending rotor disc arm and a plurality of rotor blades extending radially outwardly from the rotor disc. A cover plate is located at an axial face of the rotor disc and at least partially retained at a rotor disc arm. The rotor disc and cover plate define a rotor cavity. A plurality of airflow openings extend into the cavity to allow a flow of air into the rotor cavity to thermally condition the rotor disc and the cover plate at the rotor cavity.
Abstract translation: 用于燃气涡轮发动机的转子组件包括具有轴向延伸的转子盘臂和从转子盘径向向外延伸的多个转子叶片的转子盘。 盖板位于转子盘的轴向表面处并且至少部分保持在转子盘臂上。 转子盘和盖板限定了转子腔。 多个气流开口延伸到空腔中以允许空气流入转子空腔中，以在转子腔处对转子盘和盖板进行热调节。
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公开(公告)号：US20160348510A1
公开(公告)日：2016-12-01
申请号：US14727194
申请日：2015-06-01
Applicant: United Technologies Corporation
Inventor： David Richard Griffin , Zachary Mott , Christopher Corcoran , Ross Wilson , Jason D. Himes
CPC classification number: F01D5/082 , F01D5/081 , F01D5/3007 , F05D2220/32 , F05D2230/12 , F05D2230/30 , F05D2240/81 , F05D2250/294 , F05D2260/20 , F05D2300/177 , Y02T50/676
Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.
Abstract translation: 提供转子盘。 转子盘可以包括盘凸耳和沟槽。 盘片可以固定在转子盘的远端表面上。 沟槽可以设置在盘形凸耳的表面上。 沟槽可以从盘片的远端表面径向向内延伸。 沟槽可以构造成至少部分地限定流动路径，通过该流动路径，冷却空气可以到达盘片的远侧表面，以便提供盘片冷却。
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公开(公告)号：US20160108750A1
公开(公告)日：2016-04-21
申请号：US14882672
申请日：2015-10-14
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey
CPC classification number: F01D11/025 , F01D11/00 , F01D11/001 , F01D11/003 , F01D11/02 , F01D25/04 , F05D2220/32 , F05D2240/55 , F16J15/16 , F16J15/445
Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a circumferential seal for a gas turbine engine includes a first beam, a second beam, a seal shoe and at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal. Another embodiment is directed to a circumferential seal including a beam spacer.
Abstract translation: 本公开涉及燃气轮机发动机的密封系统。 在一个实施例中，用于燃气涡轮发动机的周向密封件包括第一梁，第二梁，密封靴以及被配置成保持梁间隔件的第一梁和第二梁之间的至少一个特征，其中至少一个特征是 被配置成阻尼所述周向密封件的梁和鞋的振动中的至少一个。 另一实施例涉及包括梁间隔件的周向密封。
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公开(公告)号：US11287045B2
公开(公告)日：2022-03-29
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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