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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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72.发明申请公开(公告)号：US20160348590A1
公开(公告)日：2016-12-01
申请号：US14727475
申请日：2015-06-01
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Donald W. Peters , James P. Bangerter
CPC classification number: F02C7/28 , F02C3/04 , F02K1/805 , F05D2220/32 , F05D2240/55 , F05D2240/58 , F05D2250/14 , F05D2250/314 , F05D2250/34 , F05D2250/41 , F05D2260/38 , F05D2260/57 , F05D2300/603 , F05D2300/6034 , F16J15/3488 , Y02T50/672
Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.
Abstract translation: 提供密封系统。 密封系统可以包括具有环形几何形状的第一管道，在径向方向上与第一管道重叠的第二管道以及设置在第一管道和第二管道之间的密封件。 密封件可以包括由第一管道限定的凹槽和构造成可滑动地接合凹槽的活塞。
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公开(公告)号：US20140373610A1
公开(公告)日：2014-12-25
申请号：US14308199
申请日：2014-06-18
Applicant: United Technologies Corporation
Inventor： David T. Feindel , Steven D. Porter
IPC: G01M15/14
CPC classification number: G01M15/14
Abstract: Inspection systems for a gas turbine engine (20) are provided. The inspection systems may comprise an inspection port (106), a bore-scope plug (100), a seal seat (108) and a seal (110A/110B). The bore-scope plug (100) may comprise a shaft (102A/102B) having a uniform or stepped profile. The seal (110A/110B) may be a multi-part seal (110A) or a piston seal (110B). Moreover, the bore-scope plug (100) may be configured to support, carry, and/or stabilize one or more internal structures such as, for example, a mid-turbine frame vane 82. In various embodiments, the inspection systems described herein may provide for increased inspection efficiency during development, qualification, maintenance, and event inspections.
Abstract translation: 提供了一种用于燃气涡轮发动机（20）的检查系统。 检查系统可以包括检查端口（106），孔眼插塞（100），密封座（108）和密封件（110A / 110B）。 内窥镜插头（100）可以包括具有均匀或阶梯轮廓的轴（102A / 102B）。 密封件（110A / 110B）可以是多部分密封件（110A）或活塞密封件（110B）。 此外，井眼式塞子（100）可以构造成支撑，运送和/或稳定一个或多个内部结构，例如中涡轮机叶片82.在各种实施例中，本文所述的检查系统 可以提供在开发，资格，维护和事件检查期间提高检查效率。
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公开(公告)号：US11078847B2
公开(公告)日：2021-08-03
申请号：US16815127
申请日：2020-03-11
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , John W. Mubeezi
Abstract: A heat shield panel for a combustor of a gas turbine engine including a panel body having a first surface and a second surface. The second surface being configured to be oriented toward a combustor liner of the combustor. The heat shield further includes a plurality of first pin fins projecting from the second surface of the panel body. Each of the plurality of first pin fins has a rounded top opposite the second surface. The heat shield further includes a plurality of second pin fins projecting from the second surface of the panel body. Each of the plurality of second pin fins has a flat top opposite the second surface. The plurality of second pin fins are intermittently spaced amongst the plurality of first pin fins. The plurality of second pin fins are organized in a uniform distribution across the second surface of the heat shield panel.
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公开(公告)号：US11047575B2
公开(公告)日：2021-06-29
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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Patent Agency Ranking
公开(公告)号：US10830437B1
公开(公告)日：2020-11-10
申请号：US16807478
申请日：2020-03-03
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , John W. Mubeezi
Abstract: A method of manufacturing a heat shield panel including pouring melted wax into a negative pattern of the heat shield panel, the heat shield panel including first pin fins with rounded tops and second pin fins with flat tops; allowing the wax to solidify to form a positive pattern of the heat shield panel; removing the positive pattern from the negative pattern by using an ejector rod to push the positive pattern away from the negative pattern at the flat top of each of the one or more second pin fins; coating the positive pattern with a ceramic; melting the positive pattern away from the ceramic, the ceramic having a cavity forming a second negative pattern of the heat shield panel; pouring melted metal into the cavity; allowing metal in the cavity to cool to form the heat shield panel; and removing the ceramic from the heat shield panel.
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公开(公告)号：US20200348023A1
公开(公告)日：2020-11-05
申请号：US16402707
申请日：2019-05-03
Applicant: United Technologies Corporation
Inventor： Corneil S. Paauwe , Eva Wong , San Quach , Jeremy Styborski , Caroline Karanian , Lauryn M. Curtis , Steven D. Porter , Zhongtao Dai
Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface opposite the first surface of the second component; and a cooling circuit formed in the second component, the cooling circuit including an inlet at the second surface of the second component, an outlet at the first surface of the second component, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween, wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the second component and the second surface of the second component.
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公开(公告)号：US20200326072A1
公开(公告)日：2020-10-15
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
IPC: F23R3/06
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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公开(公告)号：US20200263607A1
公开(公告)日：2020-08-20
申请号：US16815127
申请日：2020-03-11
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , John W. Mubeezi
Abstract: A heat shield panel for a combustor of a gas turbine engine including a panel body having a first surface and a second surface. The second surface being configured to be oriented toward a combustor liner of the combustor. The heat shield further includes a plurality of first pin fins projecting from the second surface of the panel body. Each of the plurality of first pin fins has a rounded top opposite the second surface. The heat shield further includes a plurality of second pin fins projecting from the second surface of the panel body. Each of the plurality of second pin fins has a flat top opposite the second surface. The plurality of second pin fins are intermittently spaced amongst the plurality of first pin fins. The plurality of second pin fins are organized in a uniform distribution across the second surface of the heat shield panel.
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公开(公告)号：US10738701B2
公开(公告)日：2020-08-11
申请号：US15690555
申请日：2017-08-30
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
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