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公开(公告)号：US20150308343A1
公开(公告)日：2015-10-29
申请号：US14649161
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Ariel Scott , John J. Henderson , Ralph D. Harris
CPC classification number: F02C7/20 , F01D25/162 , F01D25/24 , F01D25/28 , F01D25/30
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 a load from inner bearings. The outer ring has installation bosses (116) with downward-facing mount surfaces (120). The load-bearing struts connect the inner ring to the outer 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。 外环具有带有向下安装表面（120）的安装凸台（116）。 承载支柱将内圈连接到外圈。
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公开(公告)号：US10801346B2
公开(公告)日：2020-10-13
申请号：US15225179
申请日：2016-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kevin W. White , Henry K. Webster , Jonathan Ariel Scott , Randall J. Brown , Alan D. Lees
Abstract: An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and including a plurality of fingers. The finger edge may be segmented by gaps disposed between adjacent fingers of the plurality of fingers. A gas turbine engine includes a combustor section, a turbine section, and an annular finger seal. The annular finger seal includes a plurality of fingers and the annular finger seal is disposed at an adjoining interface between the combustor section and the turbine section. The annular finger seal may be mounted to the turbine section and may engage a radially inward facing surface, relative to the engine central longitudinal axis, of the combustor section.
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公开(公告)号：US10330011B2
公开(公告)日：2019-06-25
申请号：US14773807
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Jason David Liles , Jonathan Ariel Scott
Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.
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公开(公告)号：US10329957B2
公开(公告)日：2019-06-25
申请号：US14758268
申请日：2013-12-20
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott
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 connectors (112, 114) to the inner ring and the bossed covers.
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公开(公告)号：US10054009B2
公开(公告)日：2018-08-21
申请号：US14758273
申请日：2013-12-20
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott
CPC classification number: F01D25/28 , F01D25/24 , F01D25/30 , Y10T29/49323
Abstract: A turbine exhaust case (28) comprises a one-piece fairing (120) defining an air-flow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the one-piece vane fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102), a plurality of covers (110), and a plurality of radial struts (106). The outer ring is disposed concentrically outward of the inner ring, and has hollow bosses (114) with strut apertures (SA) at vane locations. The covers are secured to the hollow bosses. The radial struts pass through the one-piece vane fairing and through apertures in the outer angled ring, and are radially fastened to the inner ring and the flat caps.
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Patent Agency Ranking
公开(公告)号：US09982561B2
公开(公告)日：2018-05-29
申请号：US14650956
申请日：2013-12-19
Applicant: United Technologies Corporation
Inventor： Matthew Budnick , Conway Chuong , Jonathan Ariel Scott
CPC classification number: F01D25/14 , F01D5/081 , F01D9/02 , F01D9/065 , F01D25/12 , F01D25/145 , F01D25/162 , F01D25/24 , F02C7/12 , F05D2220/32 , F05D2260/231 , Y02T50/673 , Y02T50/676
Abstract: An assembly for a gas turbine engine includes a strut and a heat shield. The heat shield is disposed adjacent the strut and the heat shield and is adapted to contain a cooling air flow that passes along first cavity between the heat shield and the strut.
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公开(公告)号：US20180030844A1
公开(公告)日：2018-02-01
申请号：US15225179
申请日：2016-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kevin W. White , Henry K. Webster , Jonathan Ariel Scott , Randall J. Brown , Alan D. Lees
Abstract: An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and including a plurality of fingers. The finger edge may be segmented by gaps disposed between adjacent fingers of the plurality of fingers. A gas turbine engine includes a combustor section, a turbine section, and an annular finger seal. The annular finger seal includes a plurality of fingers and the annular finger seal is disposed at an adjoining interface between the combustor section and the turbine section. The annular finger seal may be mounted to the turbine section and may engage a radially inward facing surface, relative to the engine central longitudinal axis, of the combustor section.
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公开(公告)号：US20160169050A1
公开(公告)日：2016-06-16
申请号：US14958984
申请日：2015-12-04
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott , Steven J. Bauer
CPC classification number: F01D25/28 , F01D9/065 , F02C7/20 , F05D2220/32 , F05D2260/31
Abstract: A gas turbine engine mid-turbine frame includes an annular case that has a hole. A tie rod with a first end extends through the hole. The first end includes a threaded portion. A nut is secured to the threaded portion to clamp the tie rod to the annular case. A tab washer is arranged between the nut and the annular case. The tab washer interlocks the nut to the case to prevent relative rotation therebetween.
Abstract translation: 燃气涡轮发动机中涡轮机架包括具有孔的环形壳体。 具有第一端的拉杆延伸穿过该孔。 第一端包括螺纹部分。 螺母被固定到螺纹部分以将拉杆夹紧到环形壳体。 在螺母和环形壳体之间布置有一个止动垫圈。 凸耳垫片将螺母与外壳相互锁定，以防止其间的相对转动。
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公开(公告)号：US09328629B2
公开(公告)日：2016-05-03
申请号：US13631770
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Jonathan Ariel Scott , Jorge I. Farah
CPC classification number: F01D25/162 , F01D25/24
Abstract: An outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub. The plurality of gusseted bosses are disposed circumferentially around the outer case and between the plurality of support member bosses.
Abstract translation: 在燃气涡轮发动机中使用的外壳包括多个支撑构件凸台和多个角撑板凸台。 多个支撑构件凸起围绕外壳设置成周向，用于接收和固定将外壳附接到内毂的支撑构件。 多个角撑板凸起围绕外壳设置在多个支撑构件凸台之间。
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公开(公告)号：US20160017807A1
公开(公告)日：2016-01-21
申请号：US14773807
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Conway Chuong , Jason David Liles , Jonathan Ariel Scott
CPC classification number: F02C7/20 , F01D25/162 , F01D25/246 , F01D25/30 , F05D2220/32 , F05D2230/232 , F05D2230/50 , F05D2240/90
Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.
Abstract translation: 用于涡轮机框架的整流罩子组件88包括内环50，外环48和多个支柱。 内环由多个内部段82形成。外环由多个外部段80形成。多个支撑壳84,86连接内部环48和外部环50.在另一个实施例中， 整流罩子组件包括连接多个内部部分82和多个支柱86的内部带45，以形成外部狭槽，以及连接多个外部部分80和多个支柱86的外部带44 形成内槽。 组装整流罩46的方法包括将上述整流罩子组件38插入涡轮机框架42的后端，在涡轮机架42的前端将多个前支柱84插入外槽和内槽中 并且将前支撑杆84连接到整流罩子组件88。
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