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公开(公告)号：US20190323381A1
公开(公告)日：2019-10-24
申请号：US16451336
申请日：2019-06-25
Applicant: United Technologies Corporation
Inventor： Jeffrey D. Ponchak , Mark J. Rogers , James R. Plante
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.
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公开(公告)号：US20190063248A1
公开(公告)日：2019-02-28
申请号：US15687900
申请日：2017-08-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark J. Rogers , Timothy M. Davis
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D11/005 , F05D2240/56 , F16J15/3288
Abstract: A seal system may comprise a seal cavity defined, at least partially, by a first axial surface and a second axial surface. The second axial surface may be recessed with respect to the first axial surface. A brush seal may be disposed in the seal cavity. The brush seal may comprise a first bristle pack and a backing plate coupled to the first bristle pack. A first group of bristles of the first bristle pack may be radially inward of the first axial surface.
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公开(公告)号：US20160298476A1
公开(公告)日：2016-10-13
申请号：US15038570
申请日：2014-10-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul M. Lutjen , Mark J. Rogers
CPC classification number: F01D11/005 , F01D9/04 , F01D11/08 , F05D2220/32 , F05D2230/54 , F05D2240/11 , F05D2240/80 , F05D2250/70 , F05D2300/10 , F16J15/0887
Abstract: A seal for a gas turbine engine comprises a seal body extending from a first end to a second end. A wrap extends at least partially around the first and second ends of the seal body. A gas turbine engine is also disclosed.
Abstract translation: 用于燃气涡轮发动机的密封件包括从第一端延伸到第二端的密封体。 包装至少部分地围绕密封体的第一端和第二端延伸。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20160237839A1
公开(公告)日：2016-08-18
申请号：US15026709
申请日：2014-09-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark J. Rogers , Carl S. Richardson , Richard K. Hayford , Kenneth E. Carman , Jonathan J. Earl
CPC classification number: F01D11/005 , F01D9/041 , F01D11/001 , F01D11/08 , F01D25/04 , F05D2220/32 , F05D2260/52
Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
Abstract translation: 叶片密封系统包括具有在其一端具有第一凹部的第一翼型件的第一不可旋转叶片段。 第二不可旋转的叶片段包括第二翼型件，在其一端具有与第一凹口间隔开的第二凹口。 密封件横跨该间隙并在第一袋和第二袋中延伸。 密封构件包括密封元件和至少一个弹簧部分，其构造成将密封构件朝向密封方向正向定位。 还公开了一种用于叶片密封系统的密封件及其相关方法，用于阻止第一袋和第二袋之间的相对运动。
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公开(公告)号：US20150226132A1
公开(公告)日：2015-08-13
申请号：US14611920
申请日：2015-02-02
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Mark Broomer , Timothy M. Davis , Craig R. McGarrah , Mark J. Rogers , Russell E. Keene , Anthony B. Swift
CPC classification number: F02C7/28 , F01D11/005 , F01D25/24 , F01D25/246 , F02C3/04 , F05D2240/56 , F05D2240/58 , F05D2260/30 , F16J15/0887
Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.
Abstract translation: 用于燃气涡轮发动机的密封组件包括发动机静止结构。 第一和第二构件将空腔彼此流体地分开。 密封组件由发动机结构捕获。 密封组件包括承载件和接合第一构件的密封件。 第二个成员由承运人捕获。
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Patent Agency Ranking
公开(公告)号：US11066953B2
公开(公告)日：2021-07-20
申请号：US16451336
申请日：2019-06-25
Applicant: United Technologies Corporation
Inventor： Jeffrey D. Ponchak , Mark J. Rogers , James R. Plante
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.
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公开(公告)号：US10808563B2
公开(公告)日：2020-10-20
申请号：US15026709
申请日：2014-09-09
Applicant: United Technologies Corporation
Inventor： Mark J. Rogers , Carl S. Richardson , Richard K. Hayford , Kenneth E. Carman , Jonathan J. Earl
Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
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公开(公告)号：US20200025008A1
公开(公告)日：2020-01-23
申请号：US16386640
申请日：2019-04-17
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Timothy M. Davis , Mark J. Rogers
Abstract: A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component.
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公开(公告)号：US09957827B2
公开(公告)日：2018-05-01
申请号：US14830771
申请日：2015-08-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M Davis , Paul M Lutjen , Mark J. Rogers
CPC classification number: F01D11/005 , F05D2220/32 , F05D2240/55 , F16J15/0887 , F16J15/104
Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an adjacent second seal section, each including a base and two extending legs defining respective first and second ends of the seal. At least the first seal section includes a first plurality of slots extending from the first end to the base and a second plurality of slots extending from the second end to the base.
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公开(公告)号：US20160333890A1
公开(公告)日：2016-11-17
申请号：US15110856
申请日：2014-12-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Richard K. Hayford , Mark J. Rogers , Carl S. Richardson , Jonathan J. Earl
CPC classification number: F04D29/542 , F01D9/042 , F04D29/023 , F04D29/522 , F04D29/644 , F05B2220/302 , F05B2240/124 , F05B2280/10743 , F05B2280/50032 , F05D2220/3219 , F05D2230/642 , F05D2240/129 , F05D2300/177 , F05D2300/50212
Abstract: A gas turbine engine includes a circumferential array of vanes slidably supported in an inner case shroud segment. Multiple segments are secured to one another to provide an annular engine static structure section. The inner case shroud segment and the vanes have different material properties than one another.
Abstract translation: 燃气涡轮发动机包括可滑动地支撑在内壳体护罩段中的周向阵列的叶片。 多个段彼此固定以提供环形发动机静态结构部分。 内壳护罩段和叶片具有彼此不同的材料性质。
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