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公开(公告)号：WO2014137688A1
公开(公告)日：2014-09-12
申请号：PCT/US2014/018567
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HUBBERT, Corey L. , TOMEO, Peter V. , ANDERSON, Carney R.
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.
Abstract translation: 用于燃气涡轮发动机的风扇部分包括具有用于接收风扇叶片的根部的叶片槽的风扇轮毂。 锁定环构造成可旋转地从解锁位置移动到锁定位置，以将叶片根部固定在叶片槽中。 鼻锥固定在锁环上，从而固定在风扇部分。
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公开(公告)号：WO2014088673A3
公开(公告)日：2014-06-12
申请号：PCT/US2013/060085
申请日：2013-09-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KLING, Colin J. , BROWN, Charles W. , QUINN, Christopher M. , DUELM, Shelton O. , TOMEO, Peter V. , HUBBERT, Corey L.
Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.
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公开(公告)号：WO2011090970A1
公开(公告)日：2011-07-28
申请号：PCT/US2011/021633
申请日：2011-01-19
Applicant: UNITED TECHNOLOGIES CORPORATION , ANDERSON, Carney R. , TOMEO, Peter V.
Inventor： ANDERSON, Carney R. , TOMEO, Peter V.
IPC: F01D5/30
CPC classification number: F01D5/3015 , F01D5/326 , F05D2230/64 , Y10T29/49316 , Y10T29/49321
Abstract: A lock for constraining blades in a hub includes a flexible ring (15) for constraining the blades from moving axially in the hub, a finger (125) attached to the hub (10) for preventing the ring from rotating relative to the hub and whereby the ring flexes about at least a partial circumference thereof if urged axially by the blades (35).
Abstract translation: 用于在轮毂中约束叶片的锁包括用于限制叶片在轮毂中轴向移动的柔性环（15），附接到轮毂（10）的手指（125），用于防止环相对于轮毂旋转，由此 如果由叶片（35）轴向推动，则环绕其至少部分圆周弯曲。
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公开(公告)号：EP3287601A1
公开(公告)日：2018-02-28
申请号：EP17187342.5
申请日：2017-08-22
Applicant: United Technologies Corporation
Inventor： POPE, Andrew , TOMEO, Peter V.
IPC: F01D5/30
CPC classification number: F04D29/388 , F01D5/3084 , F02C3/04 , F02K3/06 , F04D19/002 , F04D29/325 , F04D29/34 , F04D29/384 , F05B2220/302 , F05B2260/30 , F05B2280/10304 , F05B2280/2006 , F05B2280/6003 , F05D2220/32 , F05D2220/36 , F05D2300/133 , F05D2300/603 , Y02T50/672
Abstract: A fan blade assembly (70) for a gas turbine engine (20) is provided. The fan blade assembly having: a non-linear composite airfoil (72); and a metal root (74) removably attached to the non-linear composite airfoil.
Abstract translation: 提供了一种用于燃气涡轮发动机（20）的风扇叶片组件（70）。 风扇叶片组件具有：非线性复合翼型件（72）; 和可拆卸地连接到非线性复合翼型件上的金属根部（74）。
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5.发明公开
公开(公告)号：EP3477047A1
公开(公告)日：2019-05-01
申请号：EP18201780.6
申请日：2018-10-22
Applicant: United Technologies Corporation
Inventor： TOMEO, Peter V. , MOFFITT, James H.
Abstract: A segmented structural link (302; 402) may comprise a base portion (304; 404) having a first face, a tail portion (408), and a distal end having a second face. The tail portion (408) may extend at an angle relative to the first face. The tail portion (408) may comprise a first bend (406) and may further comprise a second bend (410). The base portion (304; 404) may comprise at least one of a captured nut (321; 420), a nut plate, or a self-clinching nut. A gas turbine engine with such a segmented structural link and a method of tuning a vibrational response of a fan disc are also provided.
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Patent Agency Ranking
公开(公告)号：EP2526262B1
公开(公告)日：2015-06-03
申请号：EP11701429.0
申请日：2011-01-19
Applicant: United Technologies Corporation
Inventor： ANDERSON, Carney R. , TOMEO, Peter V.
CPC classification number: F01D5/3015 , F01D5/326 , F05D2230/64 , Y10T29/49316 , Y10T29/49321
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公开(公告)号：EP3473810A1
公开(公告)日：2019-04-24
申请号：EP18200956.3
申请日：2018-10-17
Applicant: United Technologies Corporation
Inventor： TOMEO, Peter V. , ANDERSON, Carney R.
IPC: F01D5/26 , F01D9/04 , F01D25/06 , F01D5/10 , F01D5/16 , F01D5/30 , F01D5/32 , F01D11/00 , F01D25/04
Abstract: A rotor disk assembly (100) may include a rotor disk (110) and a retention ring (120) coupled to the rotor disk (110). Generally, the retention ring (120) is tuned to adjust a modal frequency response of the rotor disk (110)/rotor disk assembly (100). In various embodiments, dimensions of the retention ring (120) vary circumferentially. In various embodiments, the retention ring (120) includes an axially extending flange (121) and a radially extending flange (123). A radial thickness of the axially extending flange (121) may vary circumferentially and/or an axial thickness of the radially extending flange (123) may vary circumferentially.
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公开(公告)号：EP3058180B1
公开(公告)日：2018-12-12
申请号：EP14863712.7
申请日：2014-09-05
Applicant: United Technologies Corporation
Inventor： HUBBERT, Corey L. , TOMEO, Peter V.
CPC classification number: F04D29/34 , F01D5/3007 , F01D5/3053 , F01D11/008 , F04D29/329 , F04D29/644 , F05D2220/36 , Y02T50/671
Abstract: A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.
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9.发明公开
公开(公告)号：EP3058180A2
公开(公告)日：2016-08-24
申请号：EP14863712.7
申请日：2014-09-05
Applicant: United Technologies Corporation
Inventor： HUBBERT, Corey L. , TOMEO, Peter V.
CPC classification number: F04D29/34 , F01D5/3007 , F01D5/3053 , F01D11/008 , F04D29/329 , F04D29/644 , F05D2220/36 , Y02T50/671
Abstract: A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.
Abstract translation: 一种用于飞机发动机的风扇转子，包括至少一个叶片根部附接凸耳，每个叶片根部附接凸耳包括附接凸耳表面，其中至少一个空腔设置在每个附接凸耳表面上。
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公开(公告)号：EP2964522A1
公开(公告)日：2016-01-13
申请号：EP14760886.3
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： HUBBERT, Corey L. , TOMEO, Peter V. , ANDERSON, Carney R.
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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