-
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。
-
Patent Agency Ranking
公开(公告)号：US10738630B2
公开(公告)日：2020-08-11
申请号：US15898690
申请日：2018-02-19
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray , Gerald Alexander Pauley , Ming Xie , Jorge Orlando Lamboy , Tod Winton Davis
Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.
-
公开(公告)号：US20190257210A1
公开(公告)日：2019-08-22
申请号：US15898690
申请日：2018-02-19
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray , Gerald Alexander Pauley , Ming Xie , Jorge Orlando Lamboy , Tod Winton Davis
Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.
-
公开(公告)号：US20140212295A1
公开(公告)日：2014-07-31
申请号：US13755426
申请日：2013-01-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Jorge Orlando Lamboy
IPC: F01D5/02
CPC classification number: F01D5/02 , F02C7/04 , F05D2300/43 , Y02T50/671
Abstract: A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings. The fairings may shield radially extending portions of the fan blades including portions of blade shanks or portions of transition regions of the blade shanks. The fairing shanks may be disposed between and monolithically formed with the fairings and fairing roots attached to the fairing shanks. The fairings may be made of an injectable thermoplastic and the shell made of metal. The fairing shanks may be setback from fairing forward tips and the fairing shanks may be setback from root forward tips of the fairing roots.
Abstract translation: 一种燃气涡轮发动机旋转器组件，其包括至少部分地限定空气动力学平滑表面的旋转器，至少部分地限定空气动力学平滑表面的壳体，以及围绕壳体的周向间隔开的可移除空气动力学整流罩。 布置在外壳中沿周向间隔开的轴向延伸的狭槽的整流罩可附接到空气动力学整流罩。 整流罩可以屏蔽风扇叶片的径向延伸部分，包括叶片柄的部分或叶片柄的过渡区域的部分。 整流罩可以布置在整流罩和整流罩之间，整流罩和整流罩根部连接在整流罩上。 整流罩可由可注射的热塑性材料制成，外壳由金属制成。 整流罩可能会从整流罩前端引起挫折，整流罩可能会从整流罩根部的根尖向后倾斜。
-
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。
-
公开(公告)号：US09297257B2
公开(公告)日：2016-03-29
申请号：US13755426
申请日：2013-01-31
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Jorge Orlando Lamboy
CPC classification number: F01D5/02 , F02C7/04 , F05D2300/43 , Y02T50/671
Abstract: A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings. The fairings may shield radially extending portions of the fan blades including portions of blade shanks or portions of transition regions of the blade shanks. The fairing shanks may be disposed between and monolithically formed with the fairings and fairing roots attached to the fairing shanks. The fairings may be made of an injectable thermoplastic and the shell made of metal. The fairing shanks may be setback from fairing forward tips and the fairing shanks may be setback from root forward tips of the fairing roots.
Abstract translation: 一种燃气涡轮发动机旋转器组件，其包括至少部分地限定空气动力学平滑表面的旋转器，至少部分地限定空气动力学平滑表面的壳体，以及围绕壳体的周向间隔开的可移除空气动力学整流罩。 布置在外壳中沿周向间隔开的轴向延伸的狭槽的整流罩可附接到空气动力学整流罩。 整流罩可以屏蔽风扇叶片的径向延伸部分，包括叶片柄的部分或叶片柄的过渡区域的部分。 整流罩可以布置在整流罩和整流罩之间，整流罩和整流罩根部连接在整流罩上。 整流罩可由可注射的热塑性材料制成，外壳由金属制成。 整流罩可能会从整流罩前端引起挫折，整流罩可能会从整流罩根部的根尖向后倾斜。
-
-
-
-
-
Search Results
6
records
(took 0.011 seconds)
