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公开(公告)号：US20190211683A1
公开(公告)日：2019-07-11
申请号：US15864925
申请日：2018-01-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Enzo DiBenedetto , Paul E. Coderre
CPC classification number: F01D5/087 , F01D5/06 , F01D11/001 , F01D11/02 , F02C7/141 , F02C7/18 , F04D29/321 , F04D29/582 , F05D2210/12 , F05D2220/3218 , F05D2220/3219 , F05D2240/11 , F05D2240/12 , F05D2240/24 , F05D2240/55 , F05D2260/20 , F05D2260/209 , F05D2260/213
Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
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公开(公告)号：US10161251B2
公开(公告)日：2018-12-25
申请号：US14851588
申请日：2015-09-11
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Matthew P. Forcier , Paul J. Hiester
Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.
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23.发明申请VANE STRUT POSITIONING AND SECURING SYSTEMS INCLUDING LOCKING WASHERS 审中-公开VANE STRUT定位和安全系统，包括锁定垫圈公开(公告)号：US20160333727A1
公开(公告)日：2016-11-17
申请号：US14713002
申请日：2015-05-15
Applicant: United Technologies Corporation
Inventor： Enzo Dibenedetto , Matthew E. Bintz
Abstract: A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing.
Abstract translation: 叶片支柱定位和固定系统包括壳体，其包括限定在其内径中的垫圈孔和布置在壳体的垫圈孔内的锁定垫圈，锁定垫圈构造成将叶片支柱取向压靠在叶片支柱垫圈 。 垫圈孔部分地通过壳体的厚度限定，并且壳体包括从壳体的内径到壳体的外径限定穿过壳体的支柱孔口。
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公开(公告)号：US10808539B2
公开(公告)日：2020-10-20
申请号：US15218376
申请日：2016-07-25
Applicant: United Technologies Corporation
Inventor： Taryn Narrow , Matthew E. Bintz , Lucas D. Sorensen , Daniel J. Monahan , Steven D. Roberts , Jordan T. Wall , Yuan Dong , Lisa I. Brilliant , Andrew J. Murphy
Abstract: A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.
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公开(公告)号：US10253644B2
公开(公告)日：2019-04-09
申请号：US14937397
申请日：2015-11-10
Applicant: United Technologies Corporation
Inventor： Ryan Edward LeBlanc , Jordan T. Wall , Matthew E. Bintz
Abstract: A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment.
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Patent Agency Ranking
公开(公告)号：US20180023396A1
公开(公告)日：2018-01-25
申请号：US15218376
申请日：2016-07-25
Applicant: United Technologies Corporation
Inventor： Taryn Narrow , Matthew E. Bintz , Lucas D. Sorensen , Daniel J. Monahan , Steven D. Roberts , Jordan T. Wall , Yuan Dong , Lisa I. Brilliant , Andrew J. Murphy
Abstract: A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.
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公开(公告)号：US09834835B2
公开(公告)日：2017-12-05
申请号：US14624817
申请日：2015-02-18
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Matthew E. Bintz
IPC: C23C4/02 , C22C27/02 , C22C27/04 , C22C27/06 , C23C4/10 , C23C4/14 , F04D29/02 , F04D29/16 , F04D29/32 , F04D29/52 , C23C28/00 , F01D11/12 , C23C4/11 , C23C4/134 , F01D5/28
CPC classification number: C23C4/02 , C22C27/025 , C22C27/04 , C22C27/06 , C23C4/11 , C23C4/134 , C23C28/321 , C23C28/3455 , C23C28/347 , F01D5/288 , F01D11/122 , F04D29/023 , F04D29/164 , F04D29/321 , F04D29/526 , F05D2230/312 , F05D2240/11 , F05D2300/174 , F05D2300/2118
Abstract: A coated substrate comprises: a metallic substrate; a bondcoat atop the substrate; and a ceramic barrier coat atop the bondcoat. The bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight.
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公开(公告)号：US20170254208A1
公开(公告)日：2017-09-07
申请号：US15058892
申请日：2016-03-02
Applicant: United Technologies Corporation
Inventor： Troy Shannon Prince , Matthew E. Bintz , Charles P. Gendrich
CPC classification number: F01D5/148 , B29C35/02 , B29C65/48 , B29C66/742 , B29C70/865 , B29C70/88 , B29D99/0025 , B29K2305/00 , B29L2031/082 , F01D5/141 , F01D5/147 , F01D5/282 , F03G7/065 , F05D2220/36 , F05D2300/505 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
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公开(公告)号：US20150218955A1
公开(公告)日：2015-08-06
申请号：US14422368
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Peter T. Schutte , Brian J. Schuler , Anthony R. Bifulco
CPC classification number: F01D5/288 , F01D5/14 , F01D5/141 , F01D5/20 , F01D9/04 , F01D11/122 , F05D2240/125 , F05D2240/307 , Y02T50/673
Abstract: A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.
Abstract translation: 悬臂式翼型件尤其包括具有主体部分和尖端的翼型件，主体部分沿相对于径向成角度的第一方向延伸，翼型件的尖端相对于第二方向沿第二方向径向地成角度 身体部位。
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公开(公告)号：US11008879B2
公开(公告)日：2021-05-18
申请号：US16251674
申请日：2019-01-18
Applicant: United Technologies Corporation
Inventor： William S. Pratt , Matthew E. Bintz , Steven D. Roberts , Adam Hart
Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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