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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：US12091984B2
公开(公告)日：2024-09-17
申请号：US18081844
申请日：2022-12-15
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US12085014B2
公开(公告)日：2024-09-10
申请号：US17754858
申请日：2020-10-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Simon Jean-Marie Bernard Cousseau , Mathieu Patrick Henri Delalandre , Patrick Jean Laurent Sultana , Laurent Cédric Zamai
IPC: F02C3/067
CPC classification number: F02C3/067 , F05D2240/24 , F05D2250/44
Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.
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公开(公告)号：US20240229629A1
公开(公告)日：2024-07-11
申请号：US18613786
申请日：2024-03-22
Applicant: TYPHON TECHNOLOGY SOLUTIONS (U.S.), LLC
Inventor： Todd Coli , Eldon Schelske
IPC: E21B43/26 , B01F23/43 , B01F27/05 , B01F35/32 , B01F35/71 , B01F101/49 , F01D15/10 , F04B1/06 , F04B1/16 , F04B17/03
CPC classification number: E21B43/26 , B01F23/43 , B01F27/05 , B01F35/3204 , B01F35/71 , E21B43/2607 , F01D15/10 , F04B1/06 , F04B1/16 , F04B17/03 , B01F2101/49 , F05D2240/24
Abstract: The present invention provides a method and system for providing on-site electrical power to a fracturing operation, and an electrically powered fracturing system. Natural gas can be used to drive a turbine generator in the production of electrical power. A scalable, electrically powered fracturing fleet is provided to pump fluids for the fracturing operation, obviating the need for a constant supply of diesel fuel to the site and reducing the site footprint and infrastructure required for the fracturing operation, when compared with conventional systems.
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公开(公告)号：US12025026B2
公开(公告)日：2024-07-02
申请号：US18365118
申请日：2023-08-03
Applicant: Honeywell International Inc.
Inventor： Richard David Conner , Ryan Cox , Josef Merki , Brian Larsen
CPC classification number: F01D5/10 , F01D5/022 , F01D5/03 , F01D5/143 , F03D1/0633 , F03D9/32 , F05B2220/31 , F05B2240/33 , F05B2240/923 , F05B2250/14 , F05B2250/141 , F05D2240/24
Abstract: A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.
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Patent Agency Ranking
公开(公告)号：US20240183276A1
公开(公告)日：2024-06-06
申请号：US18406438
申请日：2024-01-08
Applicant: RTX CORPORATION
Inventor： Jon E. Sobanski
CPC classification number: F01D5/282 , F01D5/18 , F01D5/186 , F01D9/041 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/50 , F05D2240/24 , F05D2240/35 , F05D2260/232 , F05D2300/6033
Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings. Each ring is comprised of inner and outer platform sections, a suction side wall that extends between the inner and outer platforms, and a pressure side wall that extends between the inner and outer platforms. The first ring mates at an interface with the second ring such that the suction side wall of the first ring and the pressure side wall of the second ring together form an airfoil that circumscribes an internal cavity. The interface along the airfoil includes a gap that is configured to emit cooling air from the internal cavity.
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公开(公告)号：US20240117741A1
公开(公告)日：2024-04-11
申请号：US18081844
申请日：2022-12-15
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US11814984B2
公开(公告)日：2023-11-14
申请号：US17615362
申请日：2020-05-27
Applicant: Mitsubishi Power, Ltd.
Inventor： Hidetaka Okui , Kondo Takahiro
CPC classification number: F01D5/3007 , F04D17/10 , F04D29/34 , F01D5/3015 , F04D29/322 , F05D2220/32 , F05D2240/24
Abstract: A rotor has formed therein a groove with which a moving blade including a dovetail portion and a platform portion connecting the dovetail portion and a blade portion engages. The groove opens in a surface intersecting the axis of rotation of the rotor, and includes a contacting portion extending obliquely with respect to the axis of rotation and coming into contact with the dovetail portion, a bottom portion of an end portion on the radially inner side of the rotor, a joining portion between the contacting portion and the bottom portion, a platform facing portion facing the platform portion, and a chamfered portion formed on an end surface in the groove-extending direction. The chamfered dimension of the joining portion is greater on the side with an acute angle between the groove and the end surface than on the side with an obtuse angle between the groove and the end surface.
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公开(公告)号：US11761346B2
公开(公告)日：2023-09-19
申请号：US17596405
申请日：2020-06-04
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Baptiste Rene Roger Batonnet , Alban Francois Louis
CPC classification number: F01D25/02 , B64C11/14 , B64D15/16 , F01D5/02 , F02C7/047 , F05D2220/323 , F05D2240/24
Abstract: The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.
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公开(公告)号：US11708752B2
公开(公告)日：2023-07-25
申请号：US17518309
申请日：2021-11-03
Applicant: TYPHON TECHNOLOGY SOLUTIONS, LLC
Inventor： Todd Coli , Eldon Schelske
IPC: E21B43/26 , F01D15/10 , F04B1/16 , F04B17/03 , B01F23/43 , B01F27/05 , B01F35/71 , B01F35/32 , B01F101/49
CPC classification number: E21B43/26 , B01F23/43 , B01F27/05 , B01F35/3204 , B01F35/71 , E21B43/2607 , F01D15/10 , F04B1/16 , F04B17/03 , B01F2101/49 , F05D2240/24
Abstract: The present invention provides a method and system for providing on-site electrical power to a fracturing operation, and an electrically powered fracturing system. Natural gas can be used to drive a turbine generator in the production of electrical power. A scalable, electrically powered fracturing fleet is provided to pump fluids for the fracturing operation, obviating the need for a constant supply of diesel fuel to the site and reducing the site footprint and infrastructure required for the fracturing operation, when compared with conventional systems.
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