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公开(公告)号：US10801364B1
公开(公告)日：2020-10-13
申请号：US15868449
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
Abstract: An airfoil 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 3.26-3.56 inch (82.9-90.5 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 1.25-1.55 inch (31.8-39.4 mm). The airfoil element includes at least two of a first mode with a frequency of 323±10% Hz, a second mode with a frequency of 476±10% Hz, a third mode with a frequency of 1005±10% Hz, a fourth mode with a frequency of 2670±10% Hz, a fifth mode with a frequency of 3255±10% Hz and a sixth mode with a frequency of 7628±10% Hz.
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公开(公告)号：US10767488B1
公开(公告)日：2020-09-08
申请号：US15871197
申请日：2018-01-15
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 is joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.18-3.48 inch (80.7-88.4 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 1.17-1.47 inch (29.6-37.3 mm). The airfoil element includes at least two of a first mode with a frequency of 333±10% Hz, a second mode with a frequency of 1554±10% Hz, a third mode with a frequency of 2356±10% Hz, a fourth mode with a frequency of 2830±10% Hz, a fifth mode with a frequency of 4075±10% Hz and a sixth mode with a frequency of 5239±10% Hz.
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公开(公告)号：US20170335701A1
公开(公告)日：2017-11-23
申请号：US15162032
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： David Biolsi , Kevin C. Eckland , Steven J. Feigleson , Thomas Freeman
IPC: F01D9/04
CPC classification number: F01D9/042 , F01D9/041 , F01D11/001 , F05D2220/32 , F05D2230/30 , F05D2240/12 , F05D2240/80 , F05D2260/30 , F05D2300/501 , F05D2300/615 , Y02T50/672 , Y02T50/673
Abstract: A stator assembly having: an inner air seal carrier having a mounting body; a plurality of guide vanes secured to the mounting body via a plurality of fasteners; and a fastener retention mechanism secured to the mounting body via the plurality of fasteners. The fastener retention mechanism having: a housing defining an inner chamber; and a filler located within the inner chamber. The portions of the plurality of fasteners are encapsulated within the filler.
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公开(公告)号：US09567863B2
公开(公告)日：2017-02-14
申请号：US14568257
申请日：2014-12-12
Applicant: United Technologies Corporation
Inventor： Michael E. McMahon , Steven J. Feigleson , Dennis R. Tremblay
CPC classification number: F01D9/042 , F01D25/285 , F05D2230/60 , F05D2240/10 , F05D2240/55 , Y10T29/49234 , Y10T29/49321 , Y10T29/53961 , Y10T29/53991
Abstract: A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.
Abstract translation: 用于组装用于燃气涡轮发动机的定子叶片组件的固定装置包括：外定位环，其包括多个外定位销，所述外定位销限定相对于外整流罩的多个叶片中的每一个的位置。 内定位环包括多个内定位环，其限定多个叶片中的每一个相对于内部整流罩的位置。 夹紧部分包括夹紧部分和夹紧销，所述夹紧销限定所述多个叶片中的每一个相对于所述内部和外部整流罩中的每一个的角度定向。 内部定位部分支撑多个径向定位销，其限定多个叶片中的每一个相对于内部和外部整流罩的径向位置。
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公开(公告)号：US10683761B1
公开(公告)日：2020-06-16
申请号：US15871392
申请日：2018-01-15
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 2.13-2.43 inch (54.2-61.8 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 3.56-3.86 inch (90.3-97.9 mm). The airfoil element includes at least one of a first mode with a frequency of 1049±10% Hz and a second mode with a frequency of 1271±10% Hz.
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Patent Agency Ranking
公开(公告)号：US10202857B2
公开(公告)日：2019-02-12
申请号：US14616274
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark E. Simonds , Steven J. Feigleson
Abstract: A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.
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公开(公告)号：US20180340432A1
公开(公告)日：2018-11-29
申请号：US15606191
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Dennis R. Tremblay , Steven J. Feigleson
Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.
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公开(公告)号：US20160084094A1
公开(公告)日：2016-03-24
申请号：US14955337
申请日：2015-12-01
Applicant: United Technologies Corporation
Inventor： Steven J. Feigleson , Dennis R. Tremblay , Michael E. McMahon , Nathan C. Johnson
IPC: F01D9/04
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：US20160003075A1
公开(公告)日：2016-01-07
申请号：US14770164
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven J. Feigleson
CPC classification number: F01D9/044 , F01D9/042 , F01D11/005 , F01D25/04 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/11 , F05D2240/12 , F05D2300/437 , F05D2300/501
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.
Abstract translation: 燃气涡轮发动机正面结构的组装方法包括相对于彼此径向相对定位第一护罩和第一护罩部分。 多个叶片周向地布置在第一护罩和第一护罩部分之间。 第二护罩部分围绕叶片固定到第一护罩部分。 第一和第二护罩部分提供第二护罩。 叶片与第一和第二护罩机械隔离。
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公开(公告)号：US11698002B1
公开(公告)日：2023-07-11
申请号：US15868483
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
IPC: F01D25/04
CPC classification number: F01D25/04 , F01D9/02 , F02C3/06 , F04D29/544 , F04D29/668 , F02K3/06 , F05D2220/32 , F05D2230/80 , F05D2300/173 , F05D2300/501 , F05D2300/522
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 3.46-3.76 inch (87.8-95.5 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 1.98-2.28 inch (50.2-57.8 mm). The airfoil element includes at least one of a first mode with a frequency of 1056 ± 10% Hz and a second mode with a frequency of 1582 ± 10% Hz.
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