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公开(公告)号：US20230296024A1
公开(公告)日：2023-09-21
申请号：US17951653
申请日：2022-09-23
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Francesco Bertini , Davide Torzo , Pratish Patil , John Joseph , Mahendran Manoharan , Ganesh Seshadri
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.
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公开(公告)号：US10815824B2
公开(公告)日：2020-10-27
申请号：US15478321
申请日：2017-04-04
Applicant: General Electric Company
Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.
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公开(公告)号：US20250146418A1
公开(公告)日：2025-05-08
申请号：US19013045
申请日：2025-01-08
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
Abstract: A turbomachinery apparatus 10 includes: a turbine 22, including: a turbine component 36 defining at least one arcuate flowpath surface 40; an array of axial-flow turbine airfoils 46 extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils 146 extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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公开(公告)号：US20220220854A1
公开(公告)日：2022-07-14
申请号：US17529685
申请日：2021-11-18
Applicant: GE Avio S.r.l. , GENERAL ELECTRIC COMPANY
Inventor： Pratish Patil , Amit Goyal , Mahendran Manoharan , Francesco Bertini , Jaikumar Loganathan
IPC: F01D5/14
Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.
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5.发明申请公开(公告)号：US20190162074A1
公开(公告)日：2019-05-30
申请号：US15824151
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ganesh Seshadri , Mahendran Manoharan
Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.
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Patent Agency Ranking
公开(公告)号：US20240254884A1
公开(公告)日：2024-08-01
申请号：US18635858
申请日：2024-04-15
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Francesco Bertini , Davide Torzo , Pratish Patil , John Joseph , Mahendran Manoharan , Ganesh Seshadri
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.
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公开(公告)号：US10982554B2
公开(公告)日：2021-04-20
申请号：US15796494
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Ganesh Seshadri , Pranav Kamat , Mahendran Manoharan , Dhananjaya Gottapu , Ravikanth Avancha
IPC: F01D5/22
Abstract: A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.
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公开(公告)号：US20190284946A1
公开(公告)日：2019-09-19
申请号：US16293751
申请日：2019-03-06
Applicant: General Electric Company
Inventor： Tomasz Edward Berdowski , Artur Miroslaw Malek , Marcin Piotr Rykala , Adam Kiciak , Mahendran Manoharan , Zbigniew Michal Schabowski , Marcin Kawalkowski
Abstract: An inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.
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公开(公告)号：US20180283203A1
公开(公告)日：2018-10-04
申请号：US15478321
申请日：2017-04-04
Applicant: General Electric Company
CPC classification number: F01D21/02 , F01D5/02 , F01D5/12 , F01D9/042 , F01D21/045 , F01D25/24 , F01D25/246 , F05D2220/323 , F05D2260/311 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.
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公开(公告)号：US12221898B2
公开(公告)日：2025-02-11
申请号：US16490416
申请日：2018-03-06
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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