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公开(公告)号：US20220307380A1
公开(公告)日：2022-09-29
申请号：US17389945
申请日：2021-07-30
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
摘要： An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.
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公开(公告)号：US20230340885A1
公开(公告)日：2023-10-26
申请号：US18343013
申请日：2023-06-28
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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公开(公告)号：US12123324B2
公开(公告)日：2024-10-22
申请号：US18343013
申请日：2023-06-28
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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公开(公告)号：US11725524B2
公开(公告)日：2023-08-15
申请号：US17389945
申请日：2021-07-30
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.
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公开(公告)号：US20240352862A1
公开(公告)日：2024-10-24
申请号：US18304784
申请日：2023-04-21
发明人： Nicholas Joseph Kray , Tod Winton Davis , Nicholas Mark Daggett , Arthur William Sibbach , Elzbieta Kryj-Kos
CPC分类号： F01D5/3023 , F01D5/282 , F01D5/32 , F05D2260/37 , F05D2300/603
摘要： An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar further having a furcated tail with a set of branches defining an intervening gap between adjacent branches of the set of branches
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公开(公告)号：US20240151147A1
公开(公告)日：2024-05-09
申请号：US17979853
申请日：2022-11-03
发明人： Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Ming Xie , Elzbieta Kryj-Kos , Douglas Lorrimer Armstrong , Nicholas M. Daggett , Frank Worthoff , Scott Roger Finn
IPC分类号： F01D5/28
CPC分类号： F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2300/603
摘要： 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：US20230358242A1
公开(公告)日：2023-11-09
申请号：US17840410
申请日：2022-06-14
发明人： Mohan Kannaiah Raju , David Raju Yamarthi , Prachi Anand Tappu , Santosh Pattnaik , Adam Joseph Wangler , Elzbieta Kryj-Kos , Venkata Subramanya Sarma Devarakonda , Douglas Lorrimer Armstrong
CPC分类号： F04D25/026 , F04D29/403
摘要： High pressure magnetic coupling shrouds and methods of producing the same are disclosed herein. An example shroud disclosed herein includes an inner shell including a thermoplastic composite or a metal, and an outer shell including a composite material.
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公开(公告)号：US20170101878A1
公开(公告)日：2017-04-13
申请号：US15213504
申请日：2016-07-19
发明人： Mingchao Wang , Gerald Alexander Pauley , Courtney James Tudor , Elzbieta Kryj-Kos , Weizeng Kong
CPC分类号： F01D9/041 , F01D5/3007 , F01D11/008 , F01D25/005 , F05D2220/32 , F05D2230/30 , F05D2230/40 , F05D2230/50 , F05D2240/12 , F05D2240/30 , F05D2240/80 , F05D2300/43 , F05D2300/44 , F05D2300/501 , F05D2300/522 , F05D2300/601 , F05D2300/603 , F05D2300/612 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void. An insert is positioned within the enclosed void which is formed of a material having a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the component, while also reducing a weight of the component and an amount of stress on the component. The component may be a fan platform positioned between a plurality of fan blades, an outlet guide vane, or another component of the gas turbine engine.
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公开(公告)号：US12091768B2
公开(公告)日：2024-09-17
申请号：US18463350
申请日：2023-09-08
摘要： A method for depositing a metal layer on a component includes applying an electrically conductive coating composition comprising a resin and metal particles on a coating region of the component and partially curing the resin to a gel state to form an electrically conductive coating. The method also includes applying additional metal particles to the partially cured resin in the gel state and depositing, via an electrodeposition process, a metal layer on the electrically conductive coating.
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公开(公告)号：US20240209741A1
公开(公告)日：2024-06-27
申请号：US18088957
申请日：2022-12-27
CPC分类号： F01D5/282 , F01D5/147 , F01D5/3007 , F05D2220/32 , F05D2240/24 , F05D2240/30 , F05D2300/603
摘要： A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.
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