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公开(公告)号：US20140186187A1
公开(公告)日：2014-07-03
申请号：US13731459
申请日：2012-12-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jorge Orlando Lamboy , Matthew Glen Gann , Nicholas Joseph Kray , Gerald Alexander Pauley , Daniel Allen Wilkin, II , Ming Xie
IPC: F01D5/30
CPC classification number: F01D5/3038 , F01D5/3007 , F01D11/008 , F02K3/06 , F04D29/321 , F04D29/644 , F05D2220/36 , F05D2260/30 , Y02T50/672 , Y10T29/4932
Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.
Abstract translation: 描述了一种燃气涡轮发动机风扇叶片平台，相关的转子组件和燃气涡轮发动机，以及其组装方法。 平台具有靠近旋转轴线的前部，后部部分和前部和后部之间的过渡部分。 前部具有面向轴向前方的前向接口表面，后部具有面向径向外侧的后界面，并且该过渡部具有至少一个安装特征。 对于组装方法，后部支撑件安装在风扇盘和助力阀芯组件上。 将多个风扇叶片安装到风扇盘中，随后在相邻叶片之间安装风扇平台并将安装特征固定到盘上，从而填充风扇盘的环形空间。 最后，风扇盘上安装了前向支持。
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Patent Agency Ranking
公开(公告)号：US11300136B2
公开(公告)日：2022-04-12
申请号：US16577573
申请日：2019-09-20
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
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公开(公告)号：US20200025213A1
公开(公告)日：2020-01-23
申请号：US16577573
申请日：2019-09-20
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
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公开(公告)号：US20180073518A1
公开(公告)日：2018-03-15
申请号：US15266603
申请日：2016-09-15
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
CPC classification number: F04D29/384 , F01D5/14 , F02K3/06 , F04D29/322 , F04D29/324 , F04D29/34 , F04D29/522 , F05D2220/326 , F05D2220/36 , F05D2240/12 , F05D2240/14 , F05D2240/30 , F05D2250/70 , F05D2300/133 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
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公开(公告)号：US10458426B2
公开(公告)日：2019-10-29
申请号：US15266603
申请日：2016-09-15
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
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公开(公告)号：US09399922B2
公开(公告)日：2016-07-26
申请号：US13731459
申请日：2012-12-31
Applicant: General Electric Company
Inventor： Jorge Orlando Lamboy , Matthew Glen Gann , Nicholas Joseph Kray , Gerald Alexander Pauley , Daniel Allen Wilkin, II , Ming Xie
CPC classification number: F01D5/3038 , F01D5/3007 , F01D11/008 , F02K3/06 , F04D29/321 , F04D29/644 , F05D2220/36 , F05D2260/30 , Y02T50/672 , Y10T29/4932
Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.
Abstract translation: 描述了一种燃气涡轮发动机风扇叶片平台，相关的转子组件和燃气涡轮发动机，以及其组装方法。 平台具有靠近旋转轴线的前部，后部部分和前部和后部之间的过渡部分。 前部具有面向轴向前方的前向接口表面，后部具有面向径向外侧的后界面，并且该过渡部具有至少一个安装特征。 对于组装方法，后部支撑件安装在风扇盘和助力阀芯组件上。 将多个风扇叶片安装到风扇盘中，随后在相邻叶片之间安装风扇平台并将安装特征固定到盘上，从而填充风扇盘的环形空间。 最后，风扇盘上安装了前向支持。
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