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公开(公告)号：US20160017739A1
公开(公告)日：2016-01-21
申请号：US14793362
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： Michael C. Firnhaber , Enzo DiBenedetto
CPC classification number: F01D9/041 , F01D11/003 , F01D17/162 , F04D29/563 , F05D2230/90 , F05D2240/121
Abstract: The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.
Abstract translation: 本公开总体上涉及一种导叶组件，其包括第一翼型件，其包括第一翼型后缘，第二翼型件，第二翼型件，包括第二翼型件前缘，定位在第一翼型件之后，以在其间形成间隙;以及密封组件， 第一翼型后缘和第二翼型前缘的间隙。
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公开(公告)号：US20150377127A1
公开(公告)日：2015-12-31
申请号：US14765738
申请日：2014-02-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Enzo DiBenedetto
Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.
Abstract translation: 公开了一种燃气涡轮发动机，其包括与排气流路连通的压缩机部。 提供与泄放流路连通的旋转阀，以选择性地调节渗流流动路径内的流体流动。
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公开(公告)号：US09194499B2
公开(公告)日：2015-11-24
申请号：US14665068
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Colin D. Craig , Enzo DiBenedetto , Christopher P. Kmetz , Jonathan Logan Miller , Mark R. Sondeen
CPC classification number: F16J15/3468 , F01D11/003 , F05D2240/55
Abstract: One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The shroud includes a stem and a tip, and the tip is an insert secured to the stem.
Abstract translation: 本文所述的面密封件的一个实施例包括密封座和由密封壳体承载的密封元件。 密封元件与密封座配合以建立密封。 壳体包括密封元件支撑件和护罩。 护罩包括杆和尖端，并且尖端是固定到杆上的刀片。
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24.发明申请公开(公告)号：US20140255162A1
公开(公告)日：2014-09-11
申请号：US13745943
申请日：2013-01-21
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
CPC classification number: F01D25/18 , F01D25/162 , F02C7/06 , F02C7/36 , F05D2230/642 , F05D2260/602 , F05D2260/609 , F05D2300/50212 , Y02T50/671
Abstract: A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan. An oil channel collects oil thrown outwardly of the gear drive. A bearing support mounts bearings supporting the fan drive shaft. The oil channel and the bearing support each include mating faces that are bolted together by a plurality of bolts. The bolts extend through oil channel holes in the mating face of the oil channel. The oil channel holes have one dimension which closely receives the bolts and another dimension which is larger than an outer diameter of the extending portion of the bolts, such that the bolts may adjust radially within the oil channel holes.
Abstract translation: 涡轮机可操作地连接以驱动压缩机，并通过齿轮传动驱动风扇。 将涡轮机的输出轴与风扇的风扇驱动轴连接的多个中间齿轮。 油通道收集从齿轮传动器外面抛出的油。 轴承支架安装支撑风扇驱动轴的轴承。 油通道和轴承支撑件各自包括通过多个螺栓螺栓连接在一起的配合面。 螺栓延伸通过油通道配合面的油通道孔。 油通道孔具有紧密接收螺栓的一个尺寸和大于螺栓的延伸部分的外径的另一尺寸，使得螺栓可以在油通道孔内径向调节。
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公开(公告)号：US10823069B2
公开(公告)日：2020-11-03
申请号：US16185565
申请日：2018-11-09
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Matthew E. Bintz
Abstract: A high pressure compressor section of a gas turbine engine including: an inner case separating a core flow path of the gas turbine engine and a plenum formed between the inner case and an outer case; a bleed port located on an inner surface of the inner case, the inner surface being proximate the core flow path; an outlet located on an outer surface of the inner case, the outer surface being proximate the plenum; and a bleed air passageway passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.
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Patent Agency Ranking
公开(公告)号：US20200291781A1
公开(公告)日：2020-09-17
申请号：US16353182
申请日：2019-03-14
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Griffin D. Lavine
IPC: F01D5/06
Abstract: A tie shaft assembly for a gas turbine engine includes a compressor tie shaft that has an upstream end and a downstream end. The downstream end includes a radially outer threaded surface and a radially inner threaded surface. A turbine tie shaft has an upstream end with a radially outer threaded surface in engagement with the radially inner threaded surface on the compressor tie shaft.
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公开(公告)号：US20200248577A1
公开(公告)日：2020-08-06
申请号：US16724865
申请日：2019-12-23
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Enzo DiBenedetto
Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.
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公开(公告)号：US20200149474A1
公开(公告)日：2020-05-14
申请号：US16185565
申请日：2018-11-09
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Matthew E. Bintz
Abstract: A high pressure compressor section of a gas turbine engine including: an inner case separating a core flow path of the gas turbine engine and a plenum formed between the inner case and an outer case; a bleed port located on an inner surface of the inner case, the inner surface being proximate the core flow path; an outlet located on an outer surface of the inner case, the outer surface being proximate the plenum; and a bleed air passageway passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.
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公开(公告)号：US10436065B2
公开(公告)日：2019-10-08
申请号：US15240248
申请日：2016-08-18
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
Abstract: A gas turbine engine includes a bearing support ring with a first annular body and a second annular body disposed radially inward of the first annular body. A radial spring is connected to the first annular body and the second annular body. The gas turbine engine includes a frame with a case that extends around the first annular body. The frame includes an annular member connected to the case and positioned radially between the radial spring and the second annular body. A fluid port extends radially through the annular member. A seal is disposed around the annular member and forward of the fluid port. A first fluid passage extends through the case. A second fluid passage is formed between the bearing support ring and the frame and extends from the first fluid passage to the fluid port. A bearing outer race is disposed inward of the second annular body.
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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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