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公开(公告)号：US12228048B2
公开(公告)日：2025-02-18
申请号：US18487495
申请日：2023-10-16
Applicant: GENERAL ELECTRIC COMPANY
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：US11939880B1
公开(公告)日：2024-03-26
申请号：US17980134
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Paul Hadley Vitt , Matthew Brian Surprenant , Brian David Keith , Prem Venugopal , Thomas William Vandeputte
CPC classification number: F01D5/02 , F01D5/14 , F05D2220/30
Abstract: A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.
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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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公开(公告)号：US20240068370A1
公开(公告)日：2024-02-29
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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Patent Agency Ranking
公开(公告)号：US20210040861A1
公开(公告)日：2021-02-11
申请号：US17079577
申请日：2020-10-26
Applicant: General Electric Company
Inventor： Alexander Martin Sener , Brian David Keith , David Alan Frey , Jamil Darnell Grant
Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.
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公开(公告)号：US10329922B2
公开(公告)日：2019-06-25
申请号：US15018977
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Peter Frank Martinello , Stephen Mark Molter , Brian David Keith
Abstract: An apparatus and method of cooling a tip of an airfoil for a gas turbine engine, includes a rib circumscribing the tip to define a tip plenum. A tip baffle partially divides the tip plenum, being spaced from the rib by a baffle slot. The rib includes a tip slot in fluid communication with the baffle slot to provide a flow of cooling fluid along the tip of the airfoil for exhausting out the tip slot.
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公开(公告)号：US20170226868A1
公开(公告)日：2017-08-10
申请号：US15018977
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Peter Frank Martinello , Stephen Mark Molter , Brian David Keith
CPC classification number: F01D5/186 , F01D5/187 , F01D11/10 , F05D2240/304 , F05D2240/307 , F05D2260/22141 , Y02T50/676
Abstract: An apparatus and method of cooling a tip of an airfoil for a gas turbine engine, includes a rib circumscribing the tip to define a tip plenum. A tip baffle partially divides the tip plenum, being spaced from the rib by a baffle slot. The rib includes a tip slot in fluid communication with the baffle slot to provide a flow of cooling fluid along the tip of the airfoil for exhausting out the tip slot.
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公开(公告)号：US09222437B2
公开(公告)日：2015-12-29
申请号：US13624543
申请日：2012-09-21
Applicant: General Electric Company
Inventor： Joseph Machnaim , Brian David Keith , Scott Michael Carson
CPC classification number: F02K3/065 , B23P11/00 , F01D9/02 , F04D29/547 , Y10T29/49323
Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.
Abstract translation: 提供了一种用于涡轮发动机的过渡管道。 过渡管道包括径向内壁和围绕径向内壁定位在其间的流动通道定位的径向外壁。 径向外壁从过渡管道的上游端延伸到下游端。 这样，径向外壁的斜面从上游端增加到预定的轴向位置，并从预定的轴向位置减小到下游端。
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公开(公告)号：US20140086739A1
公开(公告)日：2014-03-27
申请号：US13624543
申请日：2012-09-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph Machnaim , Brian David Keith , Scott Michael Carson
CPC classification number: F02K3/065 , B23P11/00 , F01D9/02 , F04D29/547 , Y10T29/49323
Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.
Abstract translation: 提供了一种用于涡轮发动机的过渡管道。 过渡管道包括径向内壁和围绕径向内壁定位在其间的流动通道定位的径向外壁。 径向外壁从过渡管道的上游端延伸到下游端。 这样，径向外壁的斜面从上游端增加到预定的轴向位置，并从预定的轴向位置减小到下游端。
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