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公开(公告)号：US20240026799A1
公开(公告)日：2024-01-25
申请号：US17871063
申请日：2022-07-22
Applicant: General Electric Company
Inventor： Narendra Anand Hardikar , Deepak Trivedi , Ravindra Shankar Ganiger , Scott Alan Schimmels , Kevin Richard Graziano
CPC classification number: F01D11/02 , F01D11/12 , F05D2220/30 , F05D2240/55 , F05D2260/80
Abstract: A seal assembly at a rotor-stator interface includes at least one non-contacting seal interface and at least one rub detection feature. The rub detection feature(s) is configured to generate a signal upon the rotor and the stator making contact at the rotor-stator interface and causing wear above a certain threshold at the rotor-stator interface. The seal assembly also includes at least one sensor arranged at the rotor-stator interface. The sensor is configured to sense the signal. The seal assembly further includes a controller communicatively coupled with the sensor(s). The controller is configured to receive the signal and estimate at least one of an amount and a location of the wear at the rotor-stator interface based on the signal.
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公开(公告)号：US11879349B2
公开(公告)日：2024-01-23
申请号：US17565528
申请日：2021-12-30
Applicant: General Electric Company
Inventor： Jan Christopher Schilling , Andrew John Breslin , Bryce Loring Heitman
CPC classification number: F01D25/246 , F01D9/04 , F01D11/12 , Y02T50/60
Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
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公开(公告)号：US11788424B2
公开(公告)日：2023-10-17
申请号：US17595755
申请日：2020-05-20
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Thomas Louis Guedot , Fabien Hourquet , Eloi Duflos , Patrice Postel
CPC classification number: F01D11/12 , F01D11/08 , F01D11/14 , F02C7/28 , F05D2220/323 , F05D2230/31 , F05D2240/55
Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.
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公开(公告)号：US20190242268A1
公开(公告)日：2019-08-08
申请号：US16385725
申请日：2019-04-16
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation , Rolls-Royce plc
Inventor： Daniel K. Vetters , Aaron D. Sippel , David J. Thomas , Andrew J. Eifert , Paul A. Davis , Simon L. Jones , Peter Broadhead , Bruce E. Varney , Jeffrey A. Walston , Steven Hillier
CPC classification number: F01D11/122 , C04B35/803 , C04B35/806 , C04B35/83 , C04B2235/5252 , C04B2235/94 , F01D11/12 , F01D25/005 , F01D25/12 , F04D29/164 , F04D29/526 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/22141 , F05D2260/52 , F05D2300/6033 , Y02T50/672
Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
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公开(公告)号：US20190170495A1
公开(公告)日：2019-06-06
申请号：US15832184
申请日：2017-12-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eli Cole Warren , Peter J. Walsh
CPC classification number: G01B7/023 , F01D11/12 , F01D11/14 , F01D17/02 , F05D2270/80 , F05D2300/44 , G01B7/14
Abstract: A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane.
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Patent Agency Ranking
公开(公告)号：US10060288B2
公开(公告)日：2018-08-28
申请号：US14879416
申请日：2015-10-09
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Paul M. Lutjen
CPC classification number: F01D25/12 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2220/32 , F05D2230/50 , F05D2240/11 , F05D2240/307 , F05D2240/81 , F05D2260/20
Abstract: A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.
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公开(公告)号：US10053999B2
公开(公告)日：2018-08-21
申请号：US14781263
申请日：2014-04-07
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Brandon T. Rouse , Mark Borja , Igor S. Garcia , John R. Farris , Thomas Almy , Brian R. Pelletier
CPC classification number: F01D11/08 , F01D9/04 , F01D11/12 , F01D11/14 , F01D11/20 , F01D11/22 , F01D11/24 , F01D25/24 , Y02T50/672
Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.
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公开(公告)号：US10030531B2
公开(公告)日：2018-07-24
申请号：US15004533
申请日：2016-01-22
Applicant: United Technologies Corporation
Inventor： Christopher J. Peters
IPC: F16J15/44 , F01D11/12 , F01D5/02 , F01D9/02 , F03B3/12 , F03B3/16 , F03D3/04 , F03D3/06 , F01D11/02
CPC classification number: F01D11/12 , F01D5/02 , F01D9/02 , F01D11/025 , F03B3/12 , F03B3/16 , F03D3/04 , F03D3/06 , F05B2240/57 , F05D2220/32 , F16J15/442 , Y02T50/671
Abstract: A non-contact seal assembly is provided. This assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. An aperture may extend partially axially into the first seal shoe from the first shoe end and laterally within the first seal shoe. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.
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公开(公告)号：US09908173B2
公开(公告)日：2018-03-06
申请号：US14009301
申请日：2012-04-02
Applicant: Karl Schreiber
Inventor： Karl Schreiber
CPC classification number: B22C9/22 , B22C7/02 , B22C9/04 , C23C4/02 , F01D5/28 , F01D5/288 , F01D11/12 , F01D11/125 , F05D2230/211 , Y02T50/672
Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fiber composite layer and/or a plastic component.
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公开(公告)号：US20180051582A1
公开(公告)日：2018-02-22
申请号：US15237692
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Xiaoqing Zheng , Gene David Palmer , Michael Dennis Mack , David Bruce Knorr , Jason Lyn Bowers
CPC classification number: F01D11/12 , F01D5/02 , F01D9/02 , F05D2220/31 , F05D2220/32 , F05D2240/56 , F05D2250/232 , F05D2260/30 , F16J15/3288
Abstract: A brush seal has bristles with a free end sealing against a radially inward surface of a stationary component. The bristles are angled axially 15 degrees to 70 degrees, and circumferentially at an angle that is less than the axial angle. A retaining plate extends radially outward from the rotating component, and supports the bristles from centrifugal loading in an operative state of a turbomachine. A bristle shield extends radially outward along a length of the bristles, such that the bristle shield is configured to shield the bristles from flow during an operative state of the turbomachine. The bristles are located between the retaining plate and the bristle shield. A circumferential groove has a downstream side and an upstream side, and a side plate is attached to the upstream side. The fixed end of the bristles is attached to the upstream side of the groove by the side plate.
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