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公开(公告)号：US10260350B2
公开(公告)日：2019-04-16
申请号：US14831979
申请日：2015-08-21
Applicant: United Technologies Corporation
Inventor： Carney R. Anderson , William R. Graves
Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.
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公开(公告)号：US20140133991A1
公开(公告)日：2014-05-15
申请号：US13677470
申请日：2012-11-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carney R. Anderson , Peter V. Tomeo
IPC: F01D5/30
CPC classification number: F01D5/3015 , F01D5/323 , Y02T50/673
Abstract: A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub.
Abstract translation: 燃气涡轮发动机风扇叶片锁定组件包括风扇毂，其具有各自被配置为接收风扇叶片的根部的叶片槽。 风扇毂包括周向间隔开的第一槽。 锁定环配置为在未锁定位置和锁定位置之间移动。 锁定环包括在锁定位置与第一槽对准的周向间隔开的第二槽和多个分立的销。 每个销被构造成在锁定位置可滑动地容纳在成对的第一和第二槽中，以防止锁环相对于风扇毂的旋转运动。
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公开(公告)号：US20140127007A1
公开(公告)日：2014-05-08
申请号：US13671205
申请日：2012-11-07
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , Carney R. Anderson
IPC: F01D11/00
CPC classification number: F01D11/001
Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.
Abstract translation: 用于将燃气涡轮发动机的叶片转子密封到其定子的旋转密封件包括密封元件和密封元件支撑件，所述密封元件和密封元件支撑件包括固定密封元件的径向外边缘部分，适于附接到 支撑的转子轮毂和在径向外边缘部分和径向内部安装部分之间延伸的柔性内侧腹板部分。
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公开(公告)号：US20190353040A1
公开(公告)日：2019-11-21
申请号：US15982648
申请日：2018-05-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Robertson, JR. , Carney R. Anderson , Peter T. Schutte
Abstract: An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.
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公开(公告)号：US10458244B2
公开(公告)日：2019-10-29
申请号：US15787478
申请日：2017-10-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Peter V. Tomeo , Carney R. Anderson
Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.
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Patent Agency Ranking
公开(公告)号：US09790803B2
公开(公告)日：2017-10-17
申请号：US14185962
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： Carney R. Anderson , Peter V. Tomeo
CPC classification number: F01D5/326 , F01D5/3015 , Y10T29/49321
Abstract: A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade. The rotor includes an annular groove for a first and second retaining ring. The retaining rings are received within a common annular groove for holding each of the plurality of blades within the slots of the rotor.
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公开(公告)号：US20190024673A1
公开(公告)日：2019-01-24
申请号：US15652385
申请日：2017-07-18
Applicant: United Technologies Corporation
Inventor： Carney R. Anderson
Abstract: An integrally bladed rotor according to an example of the present disclosure includes a hub, and a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub. Each rotor airfoil has a main body that extends radially outward from a root to a tip. A first fillet has a first radius that provides a transition from the outer platform of the hub, and a second fillet situated adjacent to and radially outward of the first fillet, that provides a transition between the first fillet and the main body. The second fillet has a second radius that is less than the first radius.
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公开(公告)号：US10072509B2
公开(公告)日：2018-09-11
申请号：US14768228
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Corey L. Hubbert , Peter V. Tomeo , Carney R. Anderson
CPC classification number: F01D5/32 , F01D5/02 , F01D5/066 , F01D5/12 , F01D5/30 , F01D5/3007 , F01D9/04 , F02K3/06 , F05D2220/32 , F05D2230/60 , Y02T50/673 , Y10T29/49323
Abstract: A fan section for a gas turbine engine includes a fan hub having blade slots for receiving a root of a fan blade. A lock ring is configured to move rotatably from an unlocked position to a locked position for securing the blade root in the blade slot. A nose cone is secured to the lock ring, and thereby secured to the fan section.
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公开(公告)号：US09682450B2
公开(公告)日：2017-06-20
申请号：US13739294
申请日：2013-01-11
Applicant: United Technologies Corporation
Inventor： Peter V. Tomeo , Carney R. Anderson
CPC classification number: B23P15/04 , F01D5/025 , F01D5/282 , F01D11/008 , F02C7/04 , F05D2220/3216 , F05D2220/36 , Y02T50/672 , Y02T50/673 , Y10T29/49327
Abstract: A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub. The spinner supports a first fastening element and the nose cone includes an annular cover arranged over the fastening element. The spinner and annular cover provide an aerodynamic exterior surface of the nose cone without exposed fasteners. A second fastening element cooperates with the first fastening element to secure the spinner relative to the fan hub. The first and second fastening elements are oriented transversely to the axis.
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公开(公告)号：US20160069188A1
公开(公告)日：2016-03-10
申请号：US14831979
申请日：2015-08-21
Applicant: United Technologies Corporation
Inventor： Carney R. Anderson , William R. Graves
CPC classification number: F01D5/141 , F01D5/147 , F01D5/3007 , F01D21/045 , F05D2240/80 , F05D2260/94 , Y02T50/673
Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.
Abstract translation: 翼型结构包括具有前缘的翼型和包括附接到翼型的第一侧和与翼型相对的第二侧的平台。 平台包括在与前缘轴向对准的平台的第二侧上的浮雕切割。
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