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公开(公告)号：US10473330B2
公开(公告)日：2019-11-12
申请号：US15031070
申请日：2014-11-18
Applicant: United Technologies Corporation
Inventor： Seth A. Max , Kevin J. Low
Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.
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公开(公告)号：US10215098B2
公开(公告)日：2019-02-26
申请号：US14603088
申请日：2015-01-22
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Jorge I. Farah , Seth A. Max , John H. Mosley , Steven D. Porter , Gregory E. Reinhardt , Kevin Zacchera
Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.
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公开(公告)号：US20160215702A1
公开(公告)日：2016-07-28
申请号：US14603088
申请日：2015-01-22
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Jorge I. Farah , Seth A. Max , John H. Mosley , Steven D. Porter , Gregory E. Reinhardt , Kevin Zacchera
CPC classification number: F02C7/28 , F01D11/005 , F01D25/125 , F01D25/162 , F02C3/14 , F02C7/06 , F05D2220/32 , F05D2230/60 , F05D2240/55 , F16J15/06 , Y02T50/675
Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.
Abstract translation: 密封装置包括具有密封环的涡轮机静态结构，其具有带有接触表面的凹槽。 还包括具有第二接触表面的轴承室和位于涡轮机静态结构和轴承室之间的活塞密封件。 活塞密封件包括被配置为接触接触表面并定位在凹槽中的侧面。
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公开(公告)号：US10101031B2
公开(公告)日：2018-10-16
申请号：US14911205
申请日：2014-06-30
Applicant: United Technologies Corporation
Inventor： Alexander W. Williams , Seth A. Max , Christopher B. Lyons
Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.
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公开(公告)号：US10088166B2
公开(公告)日：2018-10-02
申请号：US14904490
申请日：2014-05-15
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Seth A. Max , Meggan Harris
Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.
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Patent Agency Ranking
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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公开(公告)号：US10161256B2
公开(公告)日：2018-12-25
申请号：US14603033
申请日：2015-01-22
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Seth A. Max
Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.
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公开(公告)号：US10107141B2
公开(公告)日：2018-10-23
申请号：US14685437
申请日：2015-04-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth A. Max , Anthony P. Cherolis
Abstract: The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a first circumferential seal, a second circumferential seal and a seal support structure configured to retain at least a portion of each of the first and second seals. The seal support structure is mounted between a turbine assembly and bearing compartment, and wherein the first and second seals provide barriers to a cavity between the turbine assembly and bearing compartment.
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公开(公告)号：US09828881B2
公开(公告)日：2017-11-28
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.
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公开(公告)号：US20160201915A1
公开(公告)日：2016-07-14
申请号：US14911205
申请日：2014-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Alexander W. Williams , Seth A. Max , Christopher B. Lyons
CPC classification number: F23R3/12 , F23R3/14 , F23R3/286 , F23R3/60 , F23R2900/00017 , Y02T50/675
Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.
Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括旋流器外部主体，其具有围绕旋流器中心纵向轴线限定的卡扣配合接口的阳性卡扣部件和/或阴性卡扣部件。 用于燃气涡轮发动机的燃烧器的隔板组件包括通过卡扣配合接口安装到隔板支撑壳体上的旋流器。
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