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公开(公告)号：US20170058692A1
公开(公告)日：2017-03-02
申请号：US14630228
申请日：2015-02-24
发明人： Nicholas W. Kantany , Edward Boucher , Kristine Marie Carnavos , Adam Covino , Melaine Ho , Jorge I. Farah , Donald W. Peters
CPC分类号： F01D17/145 , F01D17/141 , F01D17/143 , F01D17/167 , F01D25/005 , F04D27/0215 , F05D2220/32 , F05D2270/3061 , F16K39/045
摘要： An air modulating system for a gas turbine engine includes a fixed plate with a fluid passage inlet, a floating plate with a first side adjacent to the fluid passage inlet, an actuated mount configured to move the floating plate relative to the fixed plate, and a linkage element for connecting the floating plate to the actuated mount. The linkage element includes a mounting flange configured to slidably engage the floating plate.
摘要翻译： 用于燃气涡轮发动机的空气调节系统包括具有流体通道入口的固定板，具有与流体通道入口相邻的第一侧的浮动板，构造成使浮动板相对于固定板移动的致动安装板，以及 连接元件，用于将浮动板连接到致动的安装座。 联动元件包括安装凸缘，该安装凸缘被构造成可滑动地接合浮动板。
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公开(公告)号：US20150377048A1
公开(公告)日：2015-12-31
申请号：US14766178
申请日：2014-01-28
CPC分类号： F01D9/047 , F01D25/162 , F02C7/20 , F05D2230/23 , F05D2240/12 , F05D2240/80
摘要： A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
摘要翻译： 定子叶片组件包括多个不同的叶片段，每个叶片段分别包括第一平台，第二平台和在其相对端连接到第一平台和第二平台的至少一个叶片翼型件。 第一平台在不同的第一接头彼此相交，并且第二平台在彼此不同的第二接头处相交，使得多个叶片段形成环形结构。
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公开(公告)号：US20150233295A1
公开(公告)日：2015-08-20
申请号：US14429167
申请日：2013-03-01
发明人： Jorge I. Farah , Kalpendu J. Parekh
CPC分类号： F02C7/18 , F01D5/08 , F01D5/18 , F01D9/065 , F01D25/28 , F02C3/045 , F02C6/08 , F02C7/12 , F02C7/20 , F05D2250/18 , Y02T50/675
摘要： A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.
摘要翻译： 燃气涡轮发动机包括具有压缩机部分，燃烧器部分和涡轮部分的核心发动机。 热管理系统被配置为接收冷却流。 热管理系统包括位于核心发动机外径附近的计量装置。 计量装置构造成将冷却流分成多个分离的通道。 计量装置可以被配置为在第一通道和与第一通道同心的第二通道之间划分冷却流。
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公开(公告)号：US10337341B2
公开(公告)日：2019-07-02
申请号：US15292835
申请日：2016-10-13
发明人： Javier N. Johnson , Chris Bates , Eric Beach , Jorge I. Farah , Caleb N. Cross
摘要： An augmentor vane assembly includes an additively manufactured augmentor vane and a fuel line additively manufactured within the augmentor vane. A method of manufacture including additively manufacturing an augmentor vane having a wall that forms an internal volume therein; and additively manufacturing a fuel line within the augmentor vane that extends through the internal volume.
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35.发明授权公开(公告)号：US10240468B2
公开(公告)日：2019-03-26
申请号：US14432432
申请日：2013-01-09
摘要： A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.
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公开(公告)号：US10132181B2
公开(公告)日：2018-11-20
申请号：US15876602
申请日：2018-01-22
发明人： Curtis C. Cowan , Jorge I. Farah
摘要： A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.
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公开(公告)号：US10100676B2
公开(公告)日：2018-10-16
申请号：US14972360
申请日：2015-12-17
发明人： Jorge I. Farah , Christopher Treat , Jenny Chan
摘要： An inner case for a gas turbine engine includes a case body defining a centerline axis. The case body includes a turbine seal support, and an I-rod support downstream of the turbine seal support. A mid-turbine frame for a gas turbine engine includes an inner case having an integral case body. A method for manufacturing an inner case for a turbomachine with an integral high pressure turbine seal support includes fabricating a case body.
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公开(公告)号：US20180209471A1
公开(公告)日：2018-07-26
申请号：US15925812
申请日：2018-03-20
IPC分类号： F16B39/10
CPC分类号： F16B39/108 , F16B39/101 , Y10T29/49908
摘要： A disclosed lock washer includes a first opening spaced apart from a second opening for receiving fasteners and preventing rotation. A first set of tabs is associated with the first opening and a second set of tabs is associated with the second opening. Each of the first and second set of tabs are bendable to a lock position preventing rotation of a fastener received within a corresponding one of the first opening and the second opening.
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公开(公告)号：US10006308B2
公开(公告)日：2018-06-26
申请号：US14438562
申请日：2013-09-11
CPC分类号： F01D25/28 , F01D25/162 , F01D25/24 , F01D25/26 , F02C7/20 , F05D2240/91
摘要： A mid-turbine frame (MTF) system for a gas turbine engine is disclosed. The MTF includes an inner case, an outer case and a fairing sandwiched between the inner and outer cases. The fairing includes an inner ring spaced apart from and coupled to an outer ring by a plurality of hollow struts. The hollow struts accommodate support rods that connect the inner case to the outer case. Further, the hollow struts act as turning vanes for turning the flow of gases passing from a high pressure turbine (HPT) to a low pressure turbine (LPT) for purposes of providing the correct incidence angle to the first vane of the LPT. The outer ring of the fairing includes a plurality of bosses which receive attachment pins that pass through the outer case for correctly locating the fairing with respect to the outer case and for permitting radial expansion in contraction of the fairing.
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公开(公告)号：US20180031241A1
公开(公告)日：2018-02-01
申请号：US15224935
申请日：2016-08-01
发明人： Javier N. Johnson , Chris Bates , Eric Beach , Jorge I. Farah
CPC分类号： F23R3/20 , B33Y10/00 , B33Y80/00 , F01D5/185 , F01D9/041 , F01D9/06 , F02K3/10 , F05D2220/32 , F05D2230/12 , F05D2230/20 , F05D2230/22 , F05D2230/31 , F05D2230/53 , F05D2240/12 , F05D2260/20 , F05D2260/232 , F05D2300/17 , F23R3/286
摘要： An aerospace component includes a wall with an integral longitudinal wall passage formed therein, the integral longitudinal wall passage including at least one entrance apertures and at least one exit aperture, the exit aperture transverse to the integral longitudinal wall passage. The aerospace component may be additively manufactured.
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