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公开(公告)号：US20220074348A1
公开(公告)日：2022-03-10
申请号：US17016670
申请日：2020-09-10
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.
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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：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：US20180355738A1
公开(公告)日：2018-12-13
申请号：US15621123
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Paul Hadley Vitt , Brian David Keith
Abstract: An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.
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公开(公告)号：US20170298747A1
公开(公告)日：2017-10-19
申请号：US15131292
申请日：2016-04-18
Applicant: General Electric Company
Inventor： Harjit Hura , Paul Hadley Vitt , Brian David Keith , Jonathan Ong
CPC classification number: F01D9/023 , F01D5/143 , F01D5/145 , F01D9/041 , F01D25/162 , F02C3/04 , F02C7/20 , F04D29/545 , F04D29/584 , F05D2220/32 , Y02T50/671 , Y02T50/673
Abstract: A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 50% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.
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Patent Agency Ranking
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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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：US11952912B2
公开(公告)日：2024-04-09
申请号：US17894307
申请日：2022-08-24
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/18 , F02C7/12 , F05D2260/20
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
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公开(公告)号：US20240093642A1
公开(公告)日：2024-03-21
申请号：US18524874
申请日：2023-11-30
Inventor： Paul Hadley Vitt , Michael Simonetti , Ashish Sharma
CPC classification number: F02C7/141 , F01D25/12 , F02C7/16 , F05D2220/32 , F05D2230/60 , F05D2260/205 , F05D2260/232
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
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公开(公告)号：US20230340906A1
公开(公告)日：2023-10-26
申请号：US17713649
申请日：2022-04-05
Inventor： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters , Jonathan Ong
CPC classification number: F02C3/067 , F02C7/141 , F02C7/36 , F05D2220/60 , F05D2260/213 , F05D2260/40311
Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
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