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21.发明申请公开(公告)号：US20160108812A1
公开(公告)日：2016-04-21
申请号：US14855859
申请日：2015-09-16
Applicant: United Technologies Corporation
Inventor： Daniel S. Rogers , Stephen W. Milks , Steven J. Feigleson
CPC classification number: F02C7/06 , F01D25/246 , F02C3/04 , F02C7/20 , F05D2220/32 , F05D2240/50 , F05D2260/30 , F05D2260/36 , F05D2300/50212
Abstract: Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket. A contact between the first panel and the at least one slot of the inner diameter shroud restricts a circumferential rotation of the inner diameter shroud with respect to a central axis of the gas turbine engine when the first panel is inserted in the at least one slot, but allows a radial motion of the inner diameter shroud with respect to the central axis.
Abstract translation: 公开了用于引导燃气涡轮发动机的低压压缩机的内径护罩的运动的导管。 内径护罩具有形成在一个或多个径向向内延伸的凸缘中的至少三个槽。 每个导管被配置成与至少三个槽中的相应一个组合。 每个导管包括具有第一面板的衬套，并且第一面板能够插入内径护罩的相应的一个槽中。 导管还包括能够附接到燃气涡轮发动机的风扇中间壳体的轴承支撑件的支架。 套管能够连接到支架上。 第一面板和内径护罩的至少一个狭槽之间的接触限制当第一面板插入在至少一个狭槽中时，内径护罩相对于燃气涡轮发动机的中心轴线的周向旋转， 但允许内径护罩相对于中心轴线的径向运动。
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公开(公告)号：US20150275694A1
公开(公告)日：2015-10-01
申请号：US14433861
申请日：2013-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gregory E. Reinhardt , Paul Thomas Rembish , Steven L. Conner , Thomas B. Hyatt , Steven J. Feigleson , Carl Brian Klinetob
CPC classification number: F01D25/26 , F01D9/02 , F01D25/162 , F05D2220/36 , F05D2230/64 , F05D2230/642 , F05D2230/644 , F05D2260/311 , F05D2260/36 , F05D2260/39 , Y10T29/49323
Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
Abstract translation: 涡轮风扇发动机结构导叶安装在内端的核心发动机外壳结构的前隔板和外端的风扇外壳上。 多个剪切销从结构导向叶片的后部延伸到限定在隔板中的相应的多个开口以用于承受圆周载荷。
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公开(公告)号：US20140082940A1
公开(公告)日：2014-03-27
申请号：US13626929
申请日：2012-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven J. Feigleson , Dennis R. Tremblay , Michael E. McMahon , Nathan Johnson
IPC: B23P15/04
CPC classification number: B23P15/04 , B23P15/06 , F01D9/04 , F01D9/041 , F01D25/285 , F05D2230/60 , F05D2230/68 , F05D2230/70 , Y10T29/49323 , Y10T29/53961
Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.
Abstract translation: 组装涡轮机翼型阵列的示例性方法包括将部分翼型阵列固定在固定装置内，部分翼型阵列具有至少一个现有的翼型件，该翼型件在内部和外部整流罩与开放区域之间径向延伸，至少至少 一个现有的翼型已被拆除。 该方法包括相对于固定装置的基座安装定位鞍座，定位鞍座与开放区域对准，使用定位鞍座保持替换机翼，在替换机翼与内外整流罩之间的界面处施加可固化材料 并固化可固化材料，同时保持替换翼型件与内外整流罩之间的相对位置。
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公开(公告)号：US10815826B1
公开(公告)日：2020-10-27
申请号：US15868424
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
IPC: F01D9/02 , F01D25/04 , F02C3/06 , F04D29/54 , F04D29/66 , F02K3/06 , F01D5/16 , F01D5/14 , F01D5/34
Abstract: An airfoil extends in a radial direction a span in a range 3.97-4.27 inch (100.9-108.6 mm). A chord length extends in a chordwise direction from a leading edge to a trailing edge at 50% span in a range 1.28-1.58 inch (32.4-40.0 mm). The airfoil includes at least two of a first mode with a frequency of 243±10% Hz, a second mode with a frequency of 374±10% Hz, a third mode with a frequency of 741±10% Hz, a fourth mode with a frequency of 1198±10% Hz, a fifth mode with a frequency of 1663±10% Hz, a sixth mode with a frequency of 2411±10% Hz, a seventh mode with a frequency of 3734±10% Hz, an eighth mode with a frequency of 6738±10% Hz and a ninth mode with a frequency of 8977±10% Hz.
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公开(公告)号：US10794223B2
公开(公告)日：2020-10-06
申请号：US15840348
申请日：2017-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel S. Rogers , Stephen W. Milks , Steven J. Feigleson
Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.
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Patent Agency Ranking
公开(公告)号：US10787910B1
公开(公告)日：2020-09-29
申请号：US15868465
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
Abstract: 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 2.59-2.89 inch (65.7-73.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.35-1.65 inch (34.4-42.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2241±10% Hz, a second mode with a frequency of 3598±10% Hz and a third mode with a frequency of 6212±10% Hz.
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公开(公告)号：US10760447B1
公开(公告)日：2020-09-01
申请号：US15869312
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Stephen W. Milks , Steven J. Feigleson , Mark A. Stephens , Joseph C. Straccia
Abstract: 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 3.84-4.14 inch (97.5-105.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.16-1.46 inch (29.5-37.1 mm). The airfoil element includes at least two of a first mode with a frequency of 326±10% Hz, a second mode with a frequency of 1252±10% Hz, a third mode with a frequency of 2475±10% Hz, a fourth mode with a frequency of 2951±10% Hz, a fifth mode with a frequency of 4356±10% Hz and a sixth mode with a frequency of 6086±10% Hz.
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公开(公告)号：US10465541B2
公开(公告)日：2019-11-05
申请号：US14770164
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven J. Feigleson
Abstract: A method of assembling gas turbine engine front architecture includes positioning a first shroud and a first shroud portion radially relative to one another. Multiple vanes are arranged circumferentially between the first shroud and the first shroud portion. A second shroud portion is secured to the first shroud portion about the vanes. The first and second shroud portions provide a second shroud. The vanes are mechanically isolated from the first and second shrouds.
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公开(公告)号：US10316749B2
公开(公告)日：2019-06-11
申请号：US14855859
申请日：2015-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel S. Rogers , Stephen W. Milks , Steven J. Feigleson
Abstract: Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket. A contact between the first panel and the at least one slot of the inner diameter shroud restricts a circumferential rotation of the inner diameter shroud with respect to a central axis of the gas turbine engine when the first panel is inserted in the at least one slot, but allows a radial motion of the inner diameter shroud with respect to the central axis.
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公开(公告)号：US09879565B2
公开(公告)日：2018-01-30
申请号：US14600239
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Daniel S. Rogers , Stephen W. Milks , Steven J. Feigleson
CPC classification number: F01D25/243 , F01D9/042 , F01D25/246
Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.
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