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公开(公告)号：US11952900B2
公开(公告)日：2024-04-09
申请号：US17949601
申请日：2022-09-21
Applicant: General Electric Company
Inventor： Alexander Martin Sener , Brian David Keith , David Alan Frey , Jamil Darnell Grant
CPC classification number: F01D11/005 , F01D9/042 , F01D11/003 , F01D17/162 , F02C3/04 , F02C9/22 , F05D2220/32 , F05D2220/3213 , F05D2240/35
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：US20230014436A1
公开(公告)日：2023-01-19
申请号：US17949601
申请日：2022-09-21
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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Patent Agency Ranking
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：US10822981B2
公开(公告)日：2020-11-03
申请号：US15796942
申请日：2017-10-30
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：US10760426B2
公开(公告)日：2020-09-01
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：US10344602B2
公开(公告)日：2019-07-09
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
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 30% 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：US20190128131A1
公开(公告)日：2019-05-02
申请号：US15796942
申请日：2017-10-30
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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