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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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Patent Agency Ranking
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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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：US20160319681A1
公开(公告)日：2016-11-03
申请号：US14702097
申请日：2015-05-01
Applicant: General Electric Company
Inventor： Richard William Jendrix , Christopher Thomas Schuppe , Christopher John Van Derven , Samuel Joseph Stoughton , Charles Thomas McMillan , John David Bibler
CPC classification number: F01D5/3007 , F01D11/02
Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.
Abstract translation: 燃气涡轮发动机涡轮机叶片组件包括接合到叶片根部的中空翼型件，结合或附接到根部的底部表面的燕尾槽隔热屏蔽件，以及从隔热件的屏蔽出口开口到径向延伸穿过径向内端部的入口孔 根。 防护罩可以具有腿部，其从腿部向下延伸，并且具有从护罩底部向上延伸的体部，倾斜的上游端部，腿部的自由端比隔热罩底部长。 法兰可以沿着自由端定位并结合到底面。 身体，护罩底部和/或腿部可以是圆形的。 圆盘包括形成在边缘中的多个燕尾槽，互补的多个涡轮机叶片，其通过根部可拆卸地保持在燕尾槽中，燕尾槽的槽底部周向延伸到轮辋内的盘柱之间。 热屏蔽底部可以在槽底部径向间隔开。
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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：US10094228B2
公开(公告)日：2018-10-09
申请号：US14702097
申请日：2015-05-01
Applicant: General Electric Company
Inventor： Richard William Jendrix , Christopher Thomas Schuppe , Christopher John Van Derven , Samuel Joseph Stoughton , Charles Thomas McMillan , John David Bibler
Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.
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