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Patent Agency Ranking
公开(公告)号：US09453422B2
公开(公告)日：2016-09-27
申请号：US13790758
申请日：2013-03-08
Applicant: General Electric Company
Inventor： Michael Alan Hile , Brian Agnew , James Hamilton Grooms , Richard William Jendrix
CPC classification number: F01D5/3015 , F01D5/3084 , F01D5/3092 , F05D2300/50212 , Y02T50/672 , Y10T29/49321
Abstract: A turbine disk and blade assembly comprises a turbine disk including a plurality of disk posts extending radially therefrom and a plurality of disk slots between adjacent disk posts. The turbine disk is of a first material having a first coefficient of thermal expansion. The assembly further comprises a plurality of turbine blades. One of the turbine blades is received in each disk slot. The turbine blades are of a second material having a second coefficient of thermal expansion. The assembly further comprises a plurality of seal plates, wherein one of the seal plates is positioned in each disk slot radially inward of the turbine blade. The seal plates are of a material having a coefficient of thermal expansion substantially similar to that of either the disk posts or the turbine blade.
Abstract translation: 涡轮盘和叶片组件包括涡轮盘，其包括从其径向延伸的多个盘柱和在相邻盘柱之间的多个盘槽。 涡轮盘是具有第一热膨胀系数的第一材料。 组件还包括多个涡轮叶片。 涡轮叶片中的一个被接收在每个盘槽中。 涡轮叶片是具有第二热膨胀系数的第二材料。 组件还包括多个密封板，其中一个密封板位于涡轮机叶片的径向内侧的每个盘槽中。 密封板是具有基本上类似于盘柱或涡轮叶片的热膨胀系数的材料。
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公开(公告)号：US20140286756A1
公开(公告)日：2014-09-25
申请号：US13790758
申请日：2013-03-08
Applicant: General Electric Company
Inventor： Michael Alan Hile , Brian Agnew , James Hamilton Grooms , Richard William Jendrix
CPC classification number: F01D5/3015 , F01D5/3084 , F01D5/3092 , F05D2300/50212 , Y02T50/672 , Y10T29/49321
Abstract: A turbine disk and blade assembly comprises a turbine disk including a plurality of disk posts extending radially therefrom and a plurality of disk slots between adjacent disk posts. The turbine disk is of a first material having a first coefficient of thermal expansion. The assembly further comprises a plurality of turbine blades. One of the turbine blades is received in each disk slot. The turbine blades are of a second material having a second coefficient of thermal expansion. The assembly further comprises a plurality of seal plates, wherein one of the seal plates is positioned in each disk slot radially inward of the turbine blade. The seal plates are of a material having a coefficient of thermal expansion substantially similar to that of either the disk posts or the turbine blade.
Abstract translation: 涡轮盘和叶片组件包括涡轮盘，其包括从其径向延伸的多个盘柱和在相邻盘柱之间的多个盘槽。 涡轮盘是具有第一热膨胀系数的第一材料。 组件还包括多个涡轮叶片。 涡轮叶片中的一个被接收在每个盘槽中。 涡轮叶片是具有第二热膨胀系数的第二材料。 组件还包括多个密封板，其中一个密封板位于涡轮机叶片的径向内侧的每个盘槽中。 密封板是具有基本上类似于盘柱或涡轮叶片的热膨胀系数的材料。
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公开(公告)号：US20250116243A1
公开(公告)日：2025-04-10
申请号：US18982445
申请日：2024-12-16
Applicant: General Electric Company
Inventor： William Joseph Bowden , Keith Edward James Blodgett , Mustafa Dindar , David Cerra , James Hamilton Grooms , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberely Simpson
Abstract: A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.
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公开(公告)号：US20230035302A1
公开(公告)日：2023-02-02
申请号：US17388228
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Travis J. Packer , James Hamilton Grooms , David Fasig , Richard William Jendrix , Scott Alan Schimmels , Bradford Alan Tracey , Michael Alan Hile , Thomas Ryan Wallace
Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
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公开(公告)号：US11970946B2
公开(公告)日：2024-04-30
申请号：US17388228
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Travis J. Packer , James Hamilton Grooms , David Fasig , Richard William Jendrix , Scott Alan Schimmels , Bradford Alan Tracey , Michael Alan Hile , Thomas Ryan Wallace
CPC classification number: F01D11/24 , F01D9/02 , F01D25/243 , F05D2240/126 , F05D2240/55
Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
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