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公开(公告)号：US10087884B2
公开(公告)日：2018-10-02
申请号：US14877607
申请日：2015-10-07
Applicant: United Technologies Corporation
Inventor： Donald W. Peters , James P. Bangerter
Abstract: Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing.
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公开(公告)号：US20180238240A1
公开(公告)日：2018-08-23
申请号：US15913105
申请日：2018-03-06
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.
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公开(公告)号：US09938930B2
公开(公告)日：2018-04-10
申请号：US14709072
申请日：2015-05-11
Applicant: United Technologies Corporation
Inventor： Donald W. Peters , Emma J. Place
CPC classification number: F02K1/80 , F01D25/168 , F02K1/1223 , F05D2220/32 , F05D2240/128 , F05D2260/231 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16C29/001 , F16C29/02 , F16C33/201 , Y02T50/672
Abstract: A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
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公开(公告)号：US20180010482A1
公开(公告)日：2018-01-11
申请号：US15207207
申请日：2016-07-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Donald W. Peters , Andreas Sadil , Nico M. RappoIi , Amarnath Ramlogan
CPC classification number: F01D25/04 , F01D25/162 , F01D25/30 , F02C7/20 , F02C7/22 , F02K3/10 , F05D2220/323 , F05D2230/237 , F05D2260/96 , F16F7/116
Abstract: A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.
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公开(公告)号：US09803557B2
公开(公告)日：2017-10-31
申请号：US14600951
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Jorge I. Farah , Donald W. Peters , Adam Covino , Curtis C. Cowan , James R. Harders , Nicholas W. Kantany
CPC classification number: F02C9/18 , F01D17/105 , F01D17/141 , F01D17/143 , F02C7/14 , F02K3/075 , F02K3/077 , F02K3/10 , F05D2250/411 , F05D2260/213 , F05D2260/50 , Y02T50/675
Abstract: A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.
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Patent Agency Ranking
公开(公告)号：US20160223133A1
公开(公告)日：2016-08-04
申请号：US14612453
申请日：2015-02-03
Applicant: United Technologies Corporation
Inventor： Donald W. Peters , Brandon T. Slaney , Gonazlo F. Martinez, JR.
CPC classification number: F16M13/02 , F16B5/0241 , F16B37/044 , F16F15/04
Abstract: An apparatus includes a nut plate with a plurality of retention tabs integrally attached to the nut plate. A spring assembly is contained with the plurality of retention tabs. The apparatus also includes a nut retained by the retention tabs.
Abstract translation: 一种装置包括：螺母板，其具有与螺母板一体地连接的多个保持突片。 弹簧组件包含有多个保持突片。 该装置还包括由保持片保持的螺母。
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公开(公告)号：US20160208714A1
公开(公告)日：2016-07-21
申请号：US14600951
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Jorge I. Farah , Donald W. Peters , Adam Covino , Curtis C. Cowan , James R. Harders , Nicholas W. Kantany
IPC: F02C9/18
CPC classification number: F02C9/18 , F01D17/105 , F01D17/141 , F01D17/143 , F02C7/14 , F02K3/075 , F02K3/077 , F02K3/10 , F05D2250/411 , F05D2260/213 , F05D2260/50 , Y02T50/675
Abstract: A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.
Abstract translation: 可用于可应用于燃气涡轮发动机的冷却系统的阻塞门组件包括围绕发动机轴线周向隔开的多个阻挡门。 每个阻塞门被构造和布置成沿圆周方向移动至少部分地控制通过相邻固定装置中的通道的气流。 同步环围绕发动机轴线同心地定位，设置在与每个通道直接连通的环形第一管道中，并且与多个阻挡门中的每一个接合以进行同时操作。 同步环是航空动态的，以减少周围的气流阻力。
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公开(公告)号：US20160169261A1
公开(公告)日：2016-06-16
申请号：US14965435
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Donald W. Peters , Gonzalo F. Martinez, JR.
CPC classification number: F16B33/004 , F01N13/1805 , F16B5/02 , F16B33/006 , F16B2001/0085
Abstract: Aspects of the disclosure are directed to a bolt assembly comprising: a ceramic fastener, and metal threads coupled to the ceramic fastener. Aspects of the disclosure are directed to a system comprising: a panel configured to provide thermal insulation, and a bolt assembly coupled to the panel, the bolt assembly comprising: a ceramic fastener, and metal threads coupled to the ceramic fastener.
Abstract translation: 本公开的方面涉及一种螺栓组件，其包括：陶瓷紧固件和联接到陶瓷紧固件的金属螺纹。 本公开的方面涉及一种系统，包括：被配置为提供热绝缘的面板和联接到面板的螺栓组件，所述螺栓组件包括：陶瓷紧固件和联接到所述陶瓷紧固件的金属螺纹。
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公开(公告)号：US20160169108A1
公开(公告)日：2016-06-16
申请号：US14877607
申请日：2015-10-07
Applicant: United Technologies Corporation
Inventor： Donald W. Peters , James P. Bangerter
CPC classification number: F02K1/1223 , B64D33/04 , F02K1/08 , F02K1/09 , F02K1/1292 , F02K1/822 , Y02T50/672 , Y02T50/675
Abstract: Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing,
Abstract translation: 本公开的方面涉及一种飞行器系统，包括：至少一个整流罩，衬套和致动器，其被配置为使所述至少一个整流罩相对于所述衬套平移，以便获得计量的调制 内衬与至少一个整流罩之间的区域，
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公开(公告)号：US20140238027A1
公开(公告)日：2014-08-28
申请号：US13725114
申请日：2012-12-21
Applicant: United Technologies Corporation
Inventor： Donald W. Peters
IPC: F02C7/24
CPC classification number: F02C7/24 , F01D25/12 , F02K1/822 , F02K3/10 , F05D2220/80 , F05D2230/54 , F05D2230/642 , F05D2240/15 , F05D2250/12 , F05D2250/14 , F05D2250/313 , F05D2260/202 , F05D2300/501 , Y02T50/675
Abstract: A stiffener for a liner assembly of a gas turbine engine includes a second resilient member arranged on a first resilient member at substantially ninety (90) degree orientation.
Abstract translation: 用于燃气涡轮发动机的衬套组件的加强件包括以基本上九十（90）度取向布置在第一弹性构件上的第二弹性构件。
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