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公开(公告)号：US20160010484A1
公开(公告)日：2016-01-14
申请号：US14773190
申请日：2014-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy A. Romanov
CPC classification number: F01D11/16 , F01D11/18 , F01D25/14 , F01D25/24 , F01D25/243 , F01D25/246 , F01D25/26 , F01D25/265 , F01D25/28 , F05D2220/32 , F05D2240/10 , F05D2240/20 , F05D2240/55 , Y02T50/675
Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.
Abstract translation: 用于燃气涡轮发动机的环形适应支撑件尤其包括环形壳体和调节构件，其如果暴露于热能则相对于环形壳体转动。
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公开(公告)号：US11131199B2
公开(公告)日：2021-09-28
申请号：US16672781
申请日：2019-11-04
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov
Abstract: Impingement assemblies and components of gas turbine engines are described. The impingement assemblies include an impingement plate having a plurality of impingement holes formed therein and an impingement surface arranged relative to the impingement plate with an impingement cavity defined between the impingement plate and the impingement surface. A raised wall is configured on the impingement surface and extends in a direction from the impingement surface toward the impingement plate and defines a plurality of impingement cells each having a geometric shape on the impingement surface.
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公开(公告)号：US20200095887A1
公开(公告)日：2020-03-26
申请号：US16141228
申请日：2018-09-25
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov
Abstract: An impingement plate for providing cooling to a gas turbine engine component includes a first surface with a second surface opposite the first surface. The first surface and the second surface are surrounded by a perimeter defining an edge. A first plurality of holes extend through the impingement plate. A plurality of protrusions extend outward from one of the first surface or the second surface and have a distal surface transverse to one of the first surface or the second surface. At least one second impingement hole extends through the distal surface.
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公开(公告)号：US10077672B2
公开(公告)日：2018-09-18
申请号：US14773190
申请日：2014-02-18
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov
CPC classification number: F01D11/16 , F01D11/18 , F01D25/14 , F01D25/24 , F01D25/243 , F01D25/246 , F01D25/26 , F01D25/265 , F01D25/28 , F05D2220/32 , F05D2240/10 , F05D2240/20 , F05D2240/55 , Y02T50/675
Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.
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公开(公告)号：US10006367B2
公开(公告)日：2018-06-26
申请号：US14216014
申请日：2014-03-17
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Mark F. Zelesky
CPC classification number: F02C7/18 , F01D11/122 , F05D2240/11 , F05D2260/20 , Y02T50/676 , Y02T50/6765
Abstract: A turbine component for a gas turbine engine includes a multiple of self-opening cooling passages each of which defines a self-opening cooling passage axis that extends through a gas path surface.
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Patent Agency Ranking
公开(公告)号：US20170101889A1
公开(公告)日：2017-04-13
申请号：US14879416
申请日：2015-10-09
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Paul M. Lutjen
CPC classification number: F01D25/12 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2220/32 , F05D2230/50 , F05D2240/11 , F05D2240/307 , F05D2240/81 , F05D2260/20
Abstract: A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.
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公开(公告)号：US20160326907A1
公开(公告)日：2016-11-10
申请号：US14704752
申请日：2015-05-05
Applicant: United Technologies Corporation
Inventor： Brian Duguay , Dmitriy A. Romanov
CPC classification number: F01D25/12 , F01D5/187 , F01D11/08 , F05D2220/32 , F05D2230/10 , F05D2240/11 , F05D2260/20 , Y02T50/676
Abstract: A blade outer air seal (BOAS) includes a body defining a core having a forward cavity portion and a plurality of forward hooks extending radially from the body, the hooks extending to a hook height. The BOAS includes a seal surface defined between the forward hooks and which includes a forward side, an aft side, and a seal surface height. The seal surface is aft of the forward cavity portion. The BOAS includes a thermal regulation channel defining an inlet aft of the sealing surface and an outlet defined in fluid communication with the forward cavity portion.
Abstract translation: 叶片外部空气密封件（BOAS）包括限定具有前腔部分的芯部和从主体径向延伸的多个前钩的主体，钩延伸到钩高度。 BOAS包括限定在前钩之间的密封表面，其包括前侧，后侧和密封表面高度。 密封表面是前腔部分的后部。 BOAS包括限定密封表面的入口尾部的热调节通道和限定为与前腔部分流体连通的出口。
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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：US20210131290A1
公开(公告)日：2021-05-06
申请号：US16672781
申请日：2019-11-04
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov
IPC: F01D5/18
Abstract: Impingement assemblies and components of gas turbine engines are described. The impingement assemblies include an impingement plate having a plurality of impingement holes formed therein and an impingement surface arranged relative to the impingement plate with an impingement cavity defined between the impingement plate and the impingement surface. A raised wall is configured on the impingement surface and extends in a direction from the impingement surface toward the impingement plate and defines a plurality of impingement cells each having a geometric shape on the impingement surface.
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公开(公告)号：US10309255B2
公开(公告)日：2019-06-04
申请号：US15104092
申请日：2014-12-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy A. Romanov
Abstract: A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is provided in the second wall at the first end. An outlet is provided at the second end.
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