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公开(公告)号：US20240360769A1
公开(公告)日：2024-10-31
申请号：US18688009
申请日：2022-08-16
发明人： Nicolas Daniel DELAPORTE , Pierre Marie MULHEIM , Arnaud MARTINE , Antoine GIGUET , Vincent GOYON
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/3023 , F05D2220/323 , F05D2240/20 , F05D2240/30
摘要： A foil for a turbomachine rotor blade, configured to be mounted on a root of the rotor blade and including an embossment located in a lower surface of the foil and forming, in the lower surface of the foil, a convex protrusion capable of being inserted into a housing formed in a lower face of the blade root.
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公开(公告)号：US20240352942A1
公开(公告)日：2024-10-24
申请号：US18762512
申请日：2024-07-02
申请人： RTX CORPORATION
CPC分类号： F04D29/324 , F01D5/142 , F01D5/146 , F01D5/3007 , F01D5/3038 , F01D5/34 , F04D19/02 , F04D29/321 , F04D29/322 , F04D29/644 , F01D9/041 , F02C3/04 , F05D2220/32
摘要： A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.
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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
CPC分类号： F01D5/3023 , F01D5/282 , F01D5/32 , F05D2230/60 , F05D2260/37 , F05D2300/603
摘要： 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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4.发明公开公开(公告)号：US20240351135A1
公开(公告)日：2024-10-24
申请号：US18640473
申请日：2024-04-19
申请人： SAFRAN AERO BOOSTERS
发明人： Johann PANCRACE
IPC分类号： B23K20/12 , B23K101/00 , F01D5/30
CPC分类号： B23K20/129 , F01D5/3061 , B23K2101/001 , F05D2230/239
摘要： A method for sizing a junction section by orbital friction welding between a blade and a stub of a bladed disk for a turbomachine. The section is sized such that the ratio of an average ray length extending fully into the section from a point at the periphery of said section and sweeping across said section, where said average ray length is a maximum average length, and an average length of rays extending completely into the section from another point at the periphery of said section and sweeping through said section, where said average length is a minimum average length, is less than or equal to 2.
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公开(公告)号：US12123305B2
公开(公告)日：2024-10-22
申请号：US17993517
申请日：2022-11-23
CPC分类号： F01D11/003 , F01D5/025 , F01D5/30 , F05D2220/32 , F05D2240/20 , F05D2240/55
摘要： A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal, and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：US20240337193A1
公开(公告)日：2024-10-10
申请号：US18295408
申请日：2023-04-04
IPC分类号： F01D5/30
CPC分类号： F01D5/303 , F05D2220/30
摘要： A turbine blade assembly for a rotor groove is disclosed. A dovetail of the turbine blade includes a mounting arm and an end surface facing radially inward relative to the rotor axis. An extension insert includes a first end configured to contact the end surface of the dovetail and a second end. At least one positioning leg extends radially inward relative to the axis from the second end of the insert. The dovetail and the extension insert are configured to be positioned in the rotor groove to mount the turbine blade to the rotor. The mounting arm engages a radially inward facing rotor hook of the rotor groove and positioning leg(s) engage one of a radially outward facing surface of the rotor groove and a planar plate shim between the positioning leg(s) and the radially outward facing surface of the rotor groove.
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公开(公告)号：US12110809B1
公开(公告)日：2024-10-08
申请号：US18295408
申请日：2023-04-04
CPC分类号： F01D5/303 , F01D5/3038 , F01D5/32 , F01D5/3092 , F05D2220/30
摘要： A turbine blade assembly for a rotor groove is disclosed. A dovetail of the turbine blade includes a mounting arm and an end surface facing radially inward relative to the rotor axis. An extension insert includes a first end configured to contact the end surface of the dovetail and a second end. At least one positioning leg extends radially inward relative to the axis from the second end of the insert. The dovetail and the extension insert are configured to be positioned in the rotor groove to mount the turbine blade to the rotor. The mounting arm engages a radially inward facing rotor hook of the rotor groove and positioning leg(s) engage one of a radially outward facing surface of the rotor groove and a planar plate shim between the positioning leg(s) and the radially outward facing surface of the rotor groove.
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公开(公告)号：US20240309762A1
公开(公告)日：2024-09-19
申请号：US18600026
申请日：2024-03-08
发明人： Sho Bonkohara , Masamitsu OKUZONO
CPC分类号： F01D5/143 , F01D5/145 , F01D5/3007 , F05D2240/305 , F05D2240/306 , F05D2240/307
摘要： A rotor disk includes a blade root groove into which a blade root of a turbine blade is insertable. The blade root groove includes a first bearing surface, a first disk neck outer curved surface which gradually moves toward a first circumferential side as it goes from an edge on an inner radial side of the first bearing surface toward the inner radial side, and a first disk neck inner curved surface which gradually moves toward a second circumferential side as it goes from a first disk neck position corresponding to an edge on the inner radial side of the first disk neck outer curved surface toward the inner radial side. The first disk neck outer curved surface includes a first curvature changing surface of which a curvature gradually increases from the first disk neck position toward an outer radial side.
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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
发明人： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC分类号： F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
摘要： 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：US20240301800A1
公开(公告)日：2024-09-12
申请号：US18118337
申请日：2023-03-07
发明人： Masoud Roshan Fekr , Rana Foroutan
CPC分类号： F01D5/30 , F01D5/14 , F05D2230/60
摘要： A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having a first inner opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the first inner opening extends from and is located within two second inner openings, one of which extends from the leading edge of the root portion and the other extends from the trailing edge of the root portion.
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