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公开(公告)号：US10941674B2
公开(公告)日：2021-03-09
申请号：US16389193
申请日：2019-04-19
Applicant: United Technologies Corporation
Inventor： Matthew Budnick , Conway Chuong , Jonathan Ariel Scott , Darrell Weidner , Chris Bates
Abstract: An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.
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公开(公告)号：US10378370B2
公开(公告)日：2019-08-13
申请号：US14655906
申请日：2013-12-17
Applicant: United Technologies Corporation
Inventor： Matthew Budnick , Conway Chuong , Jonathan Ariel Scott
Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
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公开(公告)号：US20160201490A1
公开(公告)日：2016-07-14
申请号：US14758382
申请日：2013-12-19
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott
CPC classification number: F01D25/24 , F01D9/065 , F01D25/30 , F05D2220/32 , F05D2230/60
Abstract: A turbine exhaust case frame (100) comprises an inner ring (104), an outer ring (102), and a plurality of load-bearing struts (106). The inner ring is configured to carry load from inner bearings. The outer ring features a multi-function boss (116) with a service line aperture (124) and a mounting point for the turbine exhaust case. The load-bearing struts connect the inner ring to the outer ring, and have a service line passage (128) extending from the service line aperture to the inner ring.
Abstract translation: 涡轮机排气箱框架（100）包括内圈（104），外圈（102）和多个承载支柱（106）。 内圈配置为承载内轴承的负载。 外环具有多功能凸台（116），其具有服务线孔（124）和用于涡轮机排气箱的安装点。 承载支柱将内圈连接到外圈，并具有从服务线孔延伸到内圈的服务线通道（128）。
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公开(公告)号：US20150354410A1
公开(公告)日：2015-12-10
申请号：US14655906
申请日：2013-12-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Budnick , Conway Chuong , Jonathan Ariel Scott
CPC classification number: F01D9/041 , F01D25/145 , F01D25/162 , F01D25/24 , F01D25/246 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2240/15 , F05D2260/231 , F05D2260/30 , F05D2260/31
Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
Abstract translation: 涡轮机排气箱包括框架，整流罩，隔热罩和机械连杆。 框架包括外圈，内圈和连接外环和内圈的多个支柱。 整流罩包括设置在框架内的环形支撑结构。 隔热罩设置在框架和整流罩之间。 机械连接将隔热罩连接到整流罩。 在一个实施例中，隔热罩包括防止框架和整流罩之间的热传递的多件式隔热罩。 在各种实施例中，机械联动装置包括用于将隔热罩联接到整流罩的滑动接头或固定接头。
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公开(公告)号：US10060279B2
公开(公告)日：2018-08-28
申请号：US14652711
申请日：2013-12-23
Applicant: United Technologies Corporation
Inventor： Tuan David Vo , Jonathan Ariel Scott
CPC classification number: F01D11/001 , F01D11/005 , F01D25/24 , F01D25/243 , F05D2240/59 , F16J15/0887
Abstract: An assembly for a gas turbine engine includes a first module, a second module interconnected with the first module, a first gas turbine component, and a seal assembly. The first gas turbine component includes a body extending generally radially between an inner mounting portion and an outer seal carrier portion. The inner mounting portion is fastened to the first module such that the first gas turbine component forms a boundary between a first annular cavity in the first module, and a second annular cavity in the second module. The seal assembly is mounted to the seal carrier portion of the first gas turbine component, and includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to a first axial side of the seal carrier portion.
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Patent Agency Ranking
公开(公告)号：US09982564B2
公开(公告)日：2018-05-29
申请号：US14654953
申请日：2013-12-11
Applicant: United Technologies Corporation
Inventor： William Yeager , Jonathan Ariel Scott
CPC classification number: F01D25/162 , F01D25/145 , F01D25/26 , F01D25/30 , F05D2220/32 , F05D2230/00 , F05D2240/15 , F05D2260/231 , F05D2300/171 , F05D2300/175 , Y10T29/49321
Abstract: A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine.
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公开(公告)号：US20150345334A1
公开(公告)日：2015-12-03
申请号：US14758268
申请日：2013-12-20
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott
CPC classification number: F01D25/243 , F01D25/162 , F01D25/30 , Y10T29/49828
Abstract: A turbine exhaust case (28) comprises a fairing (120) defining an airflow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102) disposed concentrically outward of the inner ring, a plurality of bossed covers (110), and a plurality of radial struts (106). The plurality of bossed covers are bolted to the outer ring at locations circumferentially distributed about the outer diameter of the outer ring. The plurality of radial struts pass through the fairing and are secured via non-radial convectors (112, 114) to the inner ring and the bossed covers.
Abstract translation: 涡轮机排气箱（28）包括限定通过涡轮机排气箱的气流路径的整流罩（120）和多件式框架（100）。 多片框架布置在整流罩周围并且围绕整流罩支撑轴承负载，并且包括内环（104），同心地设置在内环外部的外环（102），多个凸起的盖（110）， 和多个径向支柱（106）。 多个凸起的盖在围绕外圈的外径周向分布的位置处被螺栓连接到外圈。 多个径向支柱穿过整流罩并通过非径向对流体（112,114）固定到内环和凸起的盖上。
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公开(公告)号：US20150345330A1
公开(公告)日：2015-12-03
申请号：US14655833
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Budnick , Conway Chuong , Jonathan Ariel Scott , Darrell Weidner , Chris Bates
CPC classification number: F01D25/145 , F01D25/162 , F01D25/24 , F05D2220/32 , F05D2230/232 , F05D2230/60 , F05D2240/15 , F05D2260/231 , Y10T29/49321
Abstract: An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing.
Abstract translation: 用于燃气涡轮发动机的组件包括第一壳体，整流罩和多件式隔热罩组件。 整流罩邻近第一壳体设置。 多件式隔热罩组件包括安装到第一壳体并在第一壳体和整流罩之间延伸的第一屏蔽件，以及安装到整流罩并在整流罩和第一壳体之间延伸的第二屏蔽件。
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公开(公告)号：US20150330244A1
公开(公告)日：2015-11-19
申请号：US14653243
申请日：2013-12-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tuan David Vo , Conway Chuong , Matthew Budnick , Jonathan Ariel Scott
CPC classification number: F01D11/02 , F01D9/065 , F01D11/001 , F01D11/122 , F01D25/162 , F01D25/28 , F02C7/28
Abstract: A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a) discourager portion, a seal portion, and a meshing portion.
Abstract translation: 燃气涡轮发动机组件包括第一模块，可围绕燃气涡轮发动机的中心线旋转并与第一模块流体连接的第二模块，以及多用途密封支撑件。 多用途密封件支撑件包括固定到第一模块的后端和靠近第二模块设置的前端。 前端具有disc disc部分，密封部分和啮合部分。
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公开(公告)号：US20140245750A1
公开(公告)日：2014-09-04
申请号：US13730890
申请日：2012-12-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Conway Chuong , Jonathan Ariel Scott , Matthew Budnick
IPC: F02C7/20
CPC classification number: F02C7/20 , F01D25/162 , F01D25/28 , F05D2250/42
Abstract: An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame.
Abstract translation: 用于燃气涡轮发动机的组件包括框架，底座和整流罩。 安装架连接到框架，整流罩连接到安装座。 整流罩和安装座具有接合防偏转特征，其接合以防止整流罩相对于框架的圆周运动。
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