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公开(公告)号：US12123085B2
公开(公告)日：2024-10-22
申请号：US17892541
申请日：2022-08-22
Applicant: Raytheon Technologies Corporation
Inventor： Andrzej E. Kuczek , Tahany El-Wardany , Benjamin Bedard , Michael A Klecka , Randy P. Salva , Krzysztof Barnat
CPC classification number: C22F1/04 , B23Q1/40 , F01D5/147 , F01D25/285 , B23B2270/26 , F05D2220/32 , F05D2230/26 , Y10T29/49998
Abstract: A system for deep rolling a fan blade including a shaft assembly disposed along a first axis; a hub connected to a distal end of the shaft assembly, the hub having an upper hub portion and a lower hub portion extending along a second axis, the second axis forming an angle relative to a first axis; a roller disk joined to the lower portion of the hub, the roller disk configured to contact a fan blade; a fixture supporting the fan blade; the fixture comprising a body supporting a pivot clamp attached to the body with a pivot; a support attached to the body, the support is configured to engage an airfoil portion of the fan blade; a receiver formed in the body for supporting a root of the fan blade; and a shoulder attached to the body configured to support a platform portion of the fan blade.
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公开(公告)号：US12121969B2
公开(公告)日：2024-10-22
申请号：US17770238
申请日：2020-10-13
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Christian Suchel , Sébastien Gouet , Sophie Martine Jobez , Christine Macheret
CPC classification number: B22F10/80 , B29C65/48 , B29C66/721 , B29C66/742 , B33Y50/00 , B29L2031/082 , F01D5/147 , F01D5/282 , F05D2230/23 , F05D2240/303 , F05D2300/603
Abstract: A method for manufacturing a blade in composite material with added metal leading edge for gas turbine aeroengine, the method including producing a batch of plurality of blade bodies in composite material; creating a digital model of a blade body from a blade in the batch of plurality of blade bodies; creating a digital model of a theoretical final blade including a leading edge; generating a digital model of a leading edge from the digital model of a blade body and final blade model; manufacturing at least one leading edge via additive manufacturing from the generated leading edge digital model; bonding each manufactured leading edge onto a blade body from the batch of plurality of blade bodies.
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公开(公告)号：US12110805B2
公开(公告)日：2024-10-08
申请号：US18329467
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
CPC classification number: F01D5/147 , F01D5/02 , G06F30/17 , F05D2220/32 , F05D2230/80 , F05D2240/24
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.
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公开(公告)号：US12078189B2
公开(公告)日：2024-09-03
申请号：US17884167
申请日：2022-08-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Jason Nichols , David Batch , Daniel Poick
CPC classification number: F04D29/563 , F01D5/141 , F01D5/147 , F01D9/041 , F01D17/162 , F04D29/547 , F01D7/00 , F05D2240/12 , F05D2240/128
Abstract: A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.
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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：US20240280024A1
公开(公告)日：2024-08-22
申请号：US18171533
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2300/603
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US12065943B2
公开(公告)日：2024-08-20
申请号：US17533566
申请日：2021-11-23
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Scott Roger Finn
CPC classification number: F01D5/147 , F01D5/282 , F05D2300/505 , F05D2300/603
Abstract: Morphable rotor blades for a turbine engine systems include a root portion and an airfoil portion having a morphable portion including a morphable material that changes shape in response to a stimulus.
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公开(公告)号：US12055067B2
公开(公告)日：2024-08-06
申请号：US18183079
申请日：2023-03-13
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski
CPC classification number: F01D5/187 , F01D5/081 , F01D5/14 , F01D5/147 , F01D5/18 , F01D5/282 , F01D9/041 , F05D2220/323 , F05D2240/305 , F05D2240/306 , F05D2260/2214 , F05D2300/601 , F05D2300/603
Abstract: A method of fabricating a fiber-reinforced airfoil ring includes providing a mandrel that has a mandrel suction side and mandrel pressure side, and forming an endless braid around the mandrel. The endless braid conforms to the mandrel suction side and the mandrel pressure side. The endless braid is then consolidated with a matrix material. The mandrel is then removed, leaving the consolidated endless braid as a fiber-reinforced airfoil ring that has a suction side wall that extends between inner and outer platforms, a pressure side wall that extends between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction side wall and the pressure side wall, and at least one of the suction or pressure side mate faces includes protrusions along a trailing edge.
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公开(公告)号：US12055065B1
公开(公告)日：2024-08-06
申请号：US18536535
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Vamshi Krishna Reddy Kommareddy , Nuthi Srinivas , Guru Venkata Dattu Jonnalagadda , Sandeep Kumar
CPC classification number: F01D5/147 , F01D5/282 , F01D9/02 , F01D25/005 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/30 , F05D2300/17 , F05D2300/603
Abstract: An airfoil for a gas turbine engine includes an exterior skin layer having a pressure side surface, a suction side surface, a leading edge, and a trailing edge. The exterior skin layer defines an interior volume. The airfoil further includes a primary structure within the interior volume between the pressure and suction side surfaces. The primary structure includes one or more primary meta-structures. The airfoil further includes a secondary structure within the interior volume adjacent to the primary structure between the pressure and suction side surfaces. The secondary structure includes at least one isogrid structure. Further, one or more of the plurality of primary meta-structures of the primary structure is connected to at least a portion of the at least one isogrid structure of the secondary structure.
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公开(公告)号：US12037924B2
公开(公告)日：2024-07-16
申请号：US17784932
申请日：2020-12-14
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D5/288 , F01D5/147 , F05D2220/32 , F05D2230/20 , F05D2230/31 , F05D2240/30
Abstract: A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.
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