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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：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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公开(公告)号：US11125089B2
公开(公告)日：2021-09-21
申请号：US16534724
申请日：2019-08-07
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Francesco Bertini , Aspi Rustom Wadia , Lyle D. Dailey , Andrea Arnone , Filippo Rubechini , Matteo Giovannini , Paul Hadley Vitt , Jeffrey Donald Clements
Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.
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公开(公告)号：US20200049014A1
公开(公告)日：2020-02-13
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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公开(公告)号：US10914318B2
公开(公告)日：2021-02-09
申请号：US16244559
申请日：2019-01-10
Applicant: General Electric Company
Inventor： Joseph Capozzi , Aspi Rustom Wadia
Abstract: A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.
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Patent Agency Ranking
公开(公告)号：US10883515B2
公开(公告)日：2021-01-05
申请号：US15601674
申请日：2017-05-22
Applicant: General Electric Company
Inventor： David Paul Lurie , Sherif Alykadry Abdelfattah , Michael Julian Castillo , Anthony Louis DiPietro, Jr. , Aspi Rustom Wadia , Eric Andrew Falk , William Joseph Solomon , Andrew Breeze-Stringfellow
Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
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公开(公告)号：US10934858B2
公开(公告)日：2021-03-02
申请号：US16365105
申请日：2019-03-26
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
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公开(公告)号：US10670037B2
公开(公告)日：2020-06-02
申请号：US15819215
申请日：2017-11-21
Applicant: General Electric Company
Inventor： Aspi Rustom Wadia , Deepak Manohar Kamath , Daniel Waslo
Abstract: A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.
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公开(公告)号：US20190218918A1
公开(公告)日：2019-07-18
申请号：US16365105
申请日：2019-03-26
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
CPC classification number: F01D5/20 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/06 , F02C7/18 , F05D2220/36 , F05D2230/10 , F05D2240/307 , F05D2240/35 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
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公开(公告)号：US20170167275A1
公开(公告)日：2017-06-15
申请号：US14967069
申请日：2015-12-11
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
CPC classification number: F01D5/20 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/06 , F02C7/18 , F05D2220/36 , F05D2230/10 , F05D2240/307 , F05D2240/35 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
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