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公开(公告)号：US20170138202A1
公开(公告)日：2017-05-18
申请号：US14941706
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Aspi Rustom Wadia , Lyle Douglas Dailey , Christopher Ryan Johnson , Daniel Mollmann
CPC classification number: F01D5/141 , F01D9/041 , F05D2220/32 , F05D2240/125 , F05D2240/307 , Y02T50/672 , Y02T50/673
Abstract: Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly includes a row of circumferentially adjacent turbine rotor blades, each blade in the row of blades including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each blade are shorter than the chords in span regions adjacent to the blade root and the blade tip. In another exemplary embodiment, a turbine assembly includes a row of circumferentially adjacent turbine stator vanes, each vane in the row of vanes including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each vane are shorter than the chords in span regions adjacent to the vane root and the vane tip. A turbine rotor blade for a gas turbine engine also is provided.
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公开(公告)号：US12071889B2
公开(公告)日：2024-08-27
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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公开(公告)号：US20240254882A1
公开(公告)日：2024-08-01
申请号：US18594594
申请日：2024-03-04
Applicant: GE Avio S.r.l. , General Electric Company
Inventor： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2240/301 , F05D2240/305 , F05D2240/306 , F05D2250/181 , F05D2250/711 , F05D2250/712
Abstract: An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.
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公开(公告)号：US20220243596A1
公开(公告)日：2022-08-04
申请号：US17523505
申请日：2021-11-10
Applicant: GE Avio S.r.l. , General Electric Company
Inventor： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC: F01D5/14
Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.
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公开(公告)号：US20210270137A1
公开(公告)日：2021-09-02
申请号：US17148635
申请日：2021-01-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
IPC: F01D5/14
Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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Patent Agency Ranking
公开(公告)号：US20170211399A1
公开(公告)日：2017-07-27
申请号：US15002782
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
CPC classification number: F01D9/041 , F01D5/141 , F01D5/143 , F01D25/162 , F01D25/246 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2250/71 , Y02T50/673
Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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公开(公告)号：US11885233B2
公开(公告)日：2024-01-30
申请号：US17876009
申请日：2022-07-28
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
CPC classification number: F01D5/141 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/30
Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US20230374935A1
公开(公告)日：2023-11-23
申请号：US17747497
申请日：2022-05-18
Inventor： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters
CPC classification number: F02C3/067 , F02C6/00 , F02C7/36 , F05D2220/76
Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction
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公开(公告)号：US11434765B2
公开(公告)日：2022-09-06
申请号：US17148635
申请日：2021-01-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US11274563B2
公开(公告)日：2022-03-15
申请号：US15002782
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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