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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：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：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：US11370181B2
公开(公告)日：2022-06-28
申请号：US15786804
申请日：2017-10-18
IPC分类号： B29C70/38 , B29C70/22 , B29D99/00 , B29C70/20 , B29C70/30 , B29L31/08 , B32B37/16 , F01D5/14 , B32B18/00 , B29C70/54 , F01D5/28 , B29C70/08 , B29B11/16 , B29C70/86
摘要： Methods for manufacturing composite components having complex geometries are provided. In one exemplary aspect, a method includes laying up each of a plurality of laminates to an initial shape with a substantially planar geometry or a gently curved geometry. Then, a laid up laminate is formed to a final shape for each predefined section defined by the composite component to be manufactured. Thereafter, the laminates formed to their respective final shapes are stacked to build up the complex geometry of the composite component. Next, the composite component can be cured and finish machined as necessary to form the completed composite component.
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公开(公告)号：US20210388739A1
公开(公告)日：2021-12-16
申请号：US16902480
申请日：2020-06-16
发明人： Arvind Namadevan , Arnab Sen , Wendy Wenling Lin , Shivam Mittal , Peeyush Pankaj , Shashank Suresh Puranik , Narayanan Payyoor , Praveen Sharma
IPC分类号： F01D25/24
摘要： A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin, wherein one or more of the plurality of core layers of reinforcing fibers comprises a shear thickening fluid. The core layer may include at least one fabric sheet comprising the reinforcing fibers.
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公开(公告)号：US20200109664A1
公开(公告)日：2020-04-09
申请号：US16150448
申请日：2018-10-03
IPC分类号： F02C7/045 , G10K11/172 , B32B3/12
摘要： Acoustic core segments include splicing resonant cells that resemble a first segment of a whole resonant cell configured to overlap and align with counterpart splicing resonant cells of another acoustic core segment so as to define a splice joint. The splicing resonant cells include one or more fastening elements configured to couple with corresponding counterpart splicing resonant cells thereby together defining coupled resonant cells. Acoustic liners have an acoustic core assembly that includes a first acoustic core segment mechanically joined with a second acoustic core segment by a combination of splicing resonant cells of the first acoustic core segment overlapping and aligning with splicing resonant cells of the second acoustic core segment so as to define a splice joint, and a plurality of fastening elements coupling splicing resonant cells of the first acoustic core segment with splicing resonant cells of the second acoustic core segment.
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公开(公告)号：US10107302B2
公开(公告)日：2018-10-23
申请号：US14964722
申请日：2015-12-10
摘要： An airfoil of a propulsion device having a first riblet laminate with a first adhesive layer on at least a first portion of the airfoil surface and a first riblet array sheet disposed on at least a portion of the first adhesive layer. The first riblet array sheet defines a first plurality of contiguous geometric features having rigid peaks and valleys extending in a first rib direction. The first plurality of contiguous geometric features define a total width to total height ratio W:H of about 1:1 to about 2.5:1 with a maximum total height of about 0.65 mm or less. A second riblet array laminate is also disclosed in an embodiment.
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公开(公告)号：US20220034331A1
公开(公告)日：2022-02-03
申请号：US17502620
申请日：2021-10-15
发明人： Nitesh Jain , Sujana Chandrasekar , Ramkrishna Maripalli , Nicholas Joseph Kray , Wendy Wenling Lin
IPC分类号： F04D29/38 , B32B5/02 , F02C3/04 , F04D29/32 , F02K3/06 , F04D29/02 , B29C70/02 , F01D5/28 , B32B37/14 , B29C70/20
摘要： A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.
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公开(公告)号：US20200148491A1
公开(公告)日：2020-05-14
申请号：US16598583
申请日：2019-10-10
发明人： Wendy Wenling Lin , Alexander Joseph Vallee , Derek Black , Stephen Grupinski , Damain Hendrix , Nathan Woodward
摘要： A system and method for separating a layer from a layer assembly when the layer assembly includes a backing layer and a material layer. The system includes an automated machine having a controller and an end effector. A separating tool is attached to the end effector of the automated machine. The separating tool includes a displacing member, with an outer face, configured to establish a void between the backing layer and the material layer by displacing a portion of the backing layer. The separating layer also includes a securing member configured to establish a mechanical connection with a displaced portion of the backing layer.
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