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公开(公告)号：US09551230B2
公开(公告)日：2017-01-24
申请号：US14622344
申请日：2015-02-13
发明人： Jordan J. Franklin
CPC分类号： F01D5/3061 , B23K20/1205 , B23K20/129 , B23K2101/001 , F01D5/005 , F01D5/02 , F01D5/34 , F04D29/322 , F04D29/644 , F05D2220/323 , F05D2220/36 , F05D2230/232 , F05D2230/236 , F05D2230/239 , F05D2240/30
摘要： Systems and methods are provided related to manufacturing, repairing or otherwise providing an integrally bladed rotor. In one method, a set of preform rotor blades are arranged relative to a rotor disk. The preform rotor blades are concurrently bonded to the rotor disk.
摘要翻译： 提供了与制造，修理或以其他方式提供整体叶片转子有关的系统和方法。 在一种方法中，相对于转子盘布置一组预制件转子叶片。 预型转子叶片同时结合到转子盘上。
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公开(公告)号：US11268397B2
公开(公告)日：2022-03-08
申请号：US16785145
申请日：2020-02-07
IPC分类号： F01D11/00
摘要： A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.
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公开(公告)号：US10760592B1
公开(公告)日：2020-09-01
申请号：US15869253
申请日：2018-01-12
发明人： Xuedong Zhou , Jordan J. Franklin , Michael A. Weisse , Lee Drozdenko , Mouhamadou Diop , Daniel W. Yebo , Linda S. Li
摘要： A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51±10% Hz, a second mode with a frequency of 147±10% Hz, a third mode with a frequency of 267±10% Hz, a fourth mode with a frequency of 350±10% Hz, a fifth mode with a frequency of 454±10% Hz and a sixth mode with a frequency of 619±10% Hz.
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4.发明申请GAS TURBINE FAN FAIRING PLATFORM AND METHOD OF FAIRING A ROOT LEADING EDGE OF A FAN BLADE OF A GAS TURBINE ENGINE 审中-公开气体涡轮风扇平台和燃气涡轮发动机风扇叶的根尖边缘的方法公开(公告)号：US20170058916A1
公开(公告)日：2017-03-02
申请号：US14841852
申请日：2015-09-01
CPC分类号： F04D29/667 , F01D5/145 , F01D11/008 , F04D29/325 , F04D29/384 , F04D29/703 , F05D2220/36 , F05D2240/303 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.
摘要翻译： 燃气涡轮风扇整流平台包括限定表面的至少一个主体，并且具有接受刀片的开口，从沿着沿着刀片的根部附近的前缘定位突出部的方向从表面向外延伸的突起。
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公开(公告)号：US20210246798A1
公开(公告)日：2021-08-12
申请号：US16785145
申请日：2020-02-07
IPC分类号： F01D5/22
摘要： A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.
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公开(公告)号：US10920613B2
公开(公告)日：2021-02-16
申请号：US16165935
申请日：2018-10-19
发明人： Jordan J. Franklin , Joshua W. Sampsell , Mahesh Gajanan Kavimandan , Chaitanya Mokkapati , Satyannarayana Chintapalli , Sai deepika Vemula , Vishnu Murthy Pendum , Naveen Prasad Babu Ramireddy Gari , Naga Pradeep Buddhavarapu
IPC分类号： F01D25/14
摘要： A fire protection system for a gas turbine engine is disclosed. In various embodiments, the system includes a first fire blanket wall and a second fire blanket wall, the first fire blanket wall configured for attachment to a first fairing wall and the second fire blanket wall configured for attachment to a second fairing wall, and an attachment system configured to attach the first fire blanket wall to the first fairing wall and the second fire blanket wall to the second fairing wall.
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公开(公告)号：US20200072080A1
公开(公告)日：2020-03-05
申请号：US16165935
申请日：2018-10-19
发明人： Jordan J. Franklin , Joshua W. Sampsell , Mahesh Gajanan Kavimandan , Chaitanya Mokkapati , Satyannarayana Chintapalli , Sai deepika Vemula , Vishnu Murthy Pendum , Naveen Prasad Babu Ramireddy Gari , Naga Pradeep Buddhavarapu
IPC分类号： F01D25/14
摘要： A fire protection system for a gas turbine engine is disclosed. In various embodiments, the system includes a first fire blanket wall and a second fire blanket wall, the first fire blanket wall configured for attachment to a first fairing wall and the second fire blanket wall configured for attachment to a second fairing wall, and an attachment system configured to attach the first fire blanket wall to the first fairing wall and the second fire blanket wall to the second fairing wall.
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公开(公告)号：US20160237834A1
公开(公告)日：2016-08-18
申请号：US14622344
申请日：2015-02-13
发明人： Jordan J. Franklin
CPC分类号： F01D5/3061 , B23K20/1205 , B23K20/129 , B23K2101/001 , F01D5/005 , F01D5/02 , F01D5/34 , F04D29/322 , F04D29/644 , F05D2220/323 , F05D2220/36 , F05D2230/232 , F05D2230/236 , F05D2230/239 , F05D2240/30
摘要： Systems and methods are provided related to manufacturing, repairing or otherwise providing an integrally bladed rotor. In one method, a set of preform rotor blades are arranged relative to a rotor disk. The preform rotor blades are concurrently bonded to the rotor disk.
摘要翻译： 提供了与制造，修理或以其他方式提供整体叶片转子有关的系统和方法。 在一种方法中，相对于转子盘布置一组预制件转子叶片。 预型转子叶片同时结合到转子盘上。
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