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公开(公告)号：US10196917B2
公开(公告)日：2019-02-05
申请号：US14789232
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
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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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公开(公告)号：US09670791B2
公开(公告)日：2017-06-06
申请号：US14772194
申请日：2014-03-04
Applicant: United Technologies Corporation
Inventor： Mark Broomer , Carson A. Roy Thill , Timothy M. Davis , Anthony P. Cherolis , Robert L. Hazzard , Craig R. McGarrah , Conway Choung , Russell E. Keene
CPC classification number: F01D11/08 , F01D5/14 , F01D9/02 , F01D11/003 , F01D11/005 , F01D25/246
Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.
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公开(公告)号：US20150016954A1
公开(公告)日：2015-01-15
申请号：US14504719
申请日：2014-10-02
Applicant: United Technologies Corporation
Inventor： Anne-Marie B. Thibodeau , Bruce E. Chick , Thurman Carlo Dabbs , James N. Knapp , Dmitriy A. Romanov , Russell E. Keene , Jeffrey Vincent Anastas
CPC classification number: F01D25/246 , F01D11/08 , F01D11/125 , F05D2240/11 , F05D2260/202
Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.
Abstract translation: 叶片外部空气密封支撑组件包括构造成支撑叶片外部空气密封件的主支撑构件。 主支撑构件在前缘部分和后缘部分之间大致轴向地延伸。 前缘部分构造成可滑动地容纳在由叶片外部空气密封件建立的凹槽内。 支撑翼片从主支撑构件朝向叶片外部空气密封件径向向内延伸。 所述支撑突出部构造成接触所述叶片外部空气密封件的延伸部以限制所述叶片外部空气密封件的相对轴向运动。 角撑板跨越支撑片和主支撑件之间。
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公开(公告)号：US10451204B2
公开(公告)日：2019-10-22
申请号：US14765849
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Mark Broomer , Russell E. Keene , Timothy M. Davis , Mark J. Rogers
Abstract: A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.
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Patent Agency Ranking
公开(公告)号：US10145308B2
公开(公告)日：2018-12-04
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
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.
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公开(公告)号：US20160362992A1
公开(公告)日：2016-12-15
申请号：US14736333
申请日：2015-06-11
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Russell E. Keene , Paul M. Lutjen
CPC classification number: F01D9/02 , F01D5/14 , F01D9/04 , F01D11/003 , F01D11/005 , F01D25/246
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件尤其包括在前表面和后表面之间具有周向侧的主体，每个周向侧限定配合面，附接构件从 主体和与本体和附接构件相邻的过渡构件。 过渡构件和主体限定了构造成接收密封构件的槽。 过渡构件从周向侧之一向内倾斜。 还公开了一种制造燃气涡轮发动机部件的方法。
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公开(公告)号：US20140127006A1
公开(公告)日：2014-05-08
申请号：US13668398
申请日：2012-11-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy A. Romanov , Brian Duguay , Russell E. Keene
IPC: F01D11/08
CPC classification number: F01D25/246 , F01D9/04 , F01D11/08 , F05D2240/11 , F05D2260/201 , F05D2260/221 , Y02T50/676 , Y02T50/6765
Abstract: A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括第一侧表面，第二侧表面和壁。 该壁在第一侧表面和第二侧表面之间延伸并且在其中形成有一个或多个孔。 孔与第一侧表面和/或第二侧表面间隔开并且具有在叶片外部空气密封件的表面积的约0.005％至0.450％之间的面积。
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公开(公告)号：US10077680B2
公开(公告)日：2018-09-18
申请号：US14504719
申请日：2014-10-02
Applicant: United Technologies Corporation
Inventor： Anne-Marie B. Thibodeau , Bruce E. Chick , Thurman Carlo Dabbs , James N. Knapp , Dmitriy A. Romanov , Russell E. Keene , Jeffrey Vincent Anastas
CPC classification number: F01D25/246 , F01D11/08 , F01D11/125 , F05D2240/11 , F05D2260/202
Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.
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公开(公告)号：US09951634B2
公开(公告)日：2018-04-24
申请号：US14736333
申请日：2015-06-11
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Russell E. Keene , Paul M. Lutjen
CPC classification number: F01D9/02 , F01D5/14 , F01D9/04 , F01D11/003 , F01D11/005 , F01D25/246
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.
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