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公开(公告)号：US20180200967A1
公开(公告)日：2018-07-19
申请号：US15410172
申请日：2017-01-19
Applicant: General Electric Company
Inventor： Thomas Michael Sutter , Joseph Thomas Begovich, JR. , Matthew Elias Voznick , Dennis Mason Diem , Kevin Stanley Snyder , Leslie Louis Langenbrunner , Ming Xie
CPC classification number: B29C70/342 , B29C70/54 , B29C70/543 , B29L2031/7504
Abstract: A tooling assembly and method for forming a flange of a composite component is provided. The tooling assembly includes a mold configured to receive a composite material. The composite material may include a plurality of fabric plies impregnated with resin. The fabric plies may be debulked as they are being laid using a plurality of debulking tools, with the radius of each debulking tool growing as additional fabric plies are laid. A gas-permeable bagging material may be placed along the edge of the composite material to restrict resin flow while allowing for outgassing. The tooling assembly may further include a flange shoe tool that is joined with the mold to form the flange of the composite material. The mold and flange shoe tool may define a chamber and venting passageways that allow gases such as volatile compounds to escape while the composite component is being cured.
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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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公开(公告)号：US12215592B1
公开(公告)日：2025-02-04
申请号：US18435191
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Ming Xie , Mingchao Wang , Douglas Lorrimer Armstrong , Mitchell Boyer
Abstract: A preform for making a casing structure for turbine engines. The preform includes a plurality of reinforcing fiber tows arranged in a two-dimensional weave structure, a three-dimensional weave structure, or a braided structure. The plurality of reinforcing fiber tows include integrally woven or braided fiber tows having a diameter or a density greater than a respective diameter or density of other woven or braided fiber tows in the two-dimensional weave structure, the three-dimensional weave structure, or the braided structure. The integrally woven or braided fiber tows are located in an area of the preform that is bent to form an angled corner to thereby provide strength to a casing structure comprising the angled corner.
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公开(公告)号：US20240352863A1
公开(公告)日：2024-10-24
申请号：US18509528
申请日：2023-11-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ming Xie , Mitchell Harold Boyer , Tod Winton Davis
CPC classification number: F01D5/3023 , F01D5/282 , F01D5/32 , F05D2230/60 , F05D2260/37 , F05D2300/603
Abstract: An airfoil assembly for a turbine engine. The airfoil assembly has an airfoil, and a spa. The airfoil has a wall bounding an interior and defining an exterior surface. The wall extends between a leading edge and a trailing edge to define a chordwise direction, and between a root and a tip to define a spanwise direction. The spar includes a centerline axis. the spar extends into the interior of the airfoil.
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公开(公告)号：US12078080B1
公开(公告)日：2024-09-03
申请号：US18304663
申请日：2023-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ming Xie , Tod Winton Davis
CPC classification number: F01D5/282 , F01D5/147 , F05D2220/36 , F05D2230/60 , F05D2260/74 , F05D2300/603
Abstract: An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, a skin, and an insert. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket. The skin having a braided or woven fiber.
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Patent Agency Ranking
公开(公告)号：US20240151147A1
公开(公告)日：2024-05-09
申请号：US17979853
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Ming Xie , Elzbieta Kryj-Kos , Douglas Lorrimer Armstrong , Nicholas M. Daggett , Frank Worthoff , Scott Roger Finn
IPC: F01D5/28
CPC classification number: F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2300/603
Abstract: The present disclosure relates to an airfoil assembly for a turbine engine and methods of assembly thereof. The airfoil assembly generally includes a composite airfoil and a spar. The composite airfoil has a pressure side and a suction side extending in an axial direction between a leading edge and a trailing edge defining a chordwise direction and extending radially between a root and a tip defining a spanwise direction and having a span-length. The spar includes a first portion including a first material and a second portion joined at an interface with the first portion. The second portion further includes a second material, different from the first material, joined to the first portion at an interface. The method generally includes joining the first portion with the second portion at the interface; and assembling the spar with the composite airfoil.
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公开(公告)号：US11015461B2
公开(公告)日：2021-05-25
申请号：US15850842
申请日：2017-12-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Douglas Duane Ward , Ming Xie
Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.
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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.
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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.
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公开(公告)号：US09964309B2
公开(公告)日：2018-05-08
申请号：US14579267
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier , Mark Eugene Noe , Michael Todd Radwanski , Oliver Roghe , Jessica Licardi Subit , Ming Xie
CPC classification number: F23R3/42 , F23R3/002 , F23R3/007 , F23R2900/00017 , Y10T29/4932 , Y10T29/49826
Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.
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