-
公开(公告)号：US20240293988A1
公开(公告)日：2024-09-05
申请号：US18571057
申请日：2022-06-16
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B29D99/0025 , F01D5/147 , F05D2220/36 , F05D2230/10 , F05D2230/60
Abstract: A method for manufacturing a blade made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield is attached to one edge of an airfoil, the shield having a generally elongated shape along an elongation axis of the airfoil. The shield includes at least one excess dimension so as to be able to adjust the moment weight of the blade along the axis according to the position of the shield on the edge of the axis, and the method includes a step for removing a surplus portion of the shield so s to balance the blade.
-
公开(公告)号：US12060808B2
公开(公告)日：2024-08-13
申请号：US18457491
申请日：2023-08-29
Applicant: General Electric Company
Inventor： Michael Ericson Friedman , Gang Liu
CPC classification number: F01D5/027 , B23B29/043 , B23C3/18 , B23C5/00 , B23C5/12 , F05D2220/32 , F05D2230/10 , F05D2240/24 , F05D2260/96
Abstract: A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.
-
公开(公告)号：US20240254889A1
公开(公告)日：2024-08-01
申请号：US18596421
申请日：2024-03-05
Applicant: RTX Corporation
Inventor： Christopher W. Strock
CPC classification number: F01D11/122 , B23P15/008 , F05D2230/10 , F05D2230/90 , F05D2240/11 , F05D2240/55 , F05D2300/2285 , F05D2300/6033 , F05D2300/611 , Y10T29/4932
Abstract: An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.
-
公开(公告)号：US20240229648A9
公开(公告)日：2024-07-11
申请号：US17973198
申请日：2022-10-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ananda Barua , Changjie Sun , Christopher Edward Wolfe , John Matthew Sassatelli
CPC classification number: F01D5/005 , B23P6/007 , F05D2230/10 , F05D2230/22
Abstract: A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.
-
公开(公告)号：US11920478B2
公开(公告)日：2024-03-05
申请号：US17385003
申请日：2021-07-26
Applicant: Raytheon Technologies Corporation
Inventor： Christopher W. Strock
CPC classification number: F01D11/122 , B23P15/008 , F05D2230/10 , F05D2230/90 , F05D2240/11 , F05D2240/55 , F05D2300/2285 , F05D2300/6033 , F05D2300/611 , Y10T29/4932
Abstract: In a method for manufacturing an article, the article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface. Each of the first channels are machined in the body by plunging a rotating bit into the first surface and drawing the rotating bit down the bevel surface. The coating is thereafter applied.
-
Patent Agency Ranking
公开(公告)号：US20240044256A1
公开(公告)日：2024-02-08
申请号：US18379952
申请日：2023-10-13
Applicant: RTX Corporation
Inventor： Rafael A. Perez Reisler , Andy Turko , Xuan Liu , Danielle E. Jencks , Glenn A. Cotnoir , Russell F. Croft
IPC: F01D5/28
CPC classification number: F01D5/288 , F05D2300/611 , F05D2230/90 , F05D2230/314 , F05D2230/30 , F05D2220/32 , F05D2230/10
Abstract: A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.
-
公开(公告)号：US11773730B2
公开(公告)日：2023-10-03
申请号：US17508314
申请日：2021-10-22
Inventor： Michael J. Whittle , Steven Hillier , Stephen Harris , Sungbo Shim
CPC classification number: F01D5/187 , C04B35/80 , C04B41/457 , F01D5/147 , F01D5/282 , F01D5/284 , F01D9/041 , C04B2235/616 , F05D2230/10 , F05D2230/21 , F05D2240/123 , F05D2240/124 , F05D2260/2212 , F05D2260/232 , F05D2300/6033
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.
-
公开(公告)号：US11739648B2
公开(公告)日：2023-08-29
申请号：US17531207
申请日：2021-11-19
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Yasuhiro Sasao , Soichiro Tabata , Ryo Takata , Takeshi Kudo
CPC classification number: F01D5/22 , F05D2230/10 , F05D2260/602
Abstract: Water droplets that are moved on blade surfaces of a rotor blade are effectively guided toward the blade trailing edge while influence on the strength of the rotor blade is suppressed. A steam turbine rotor blade having a tie-boss for joining to adjacent blades at an intermediate position in the blade length direction is provided. The steam turbine rotor blade includes an airfoil part in which a blade surface is partly hollow as viewed in a section obtained by cutting by an orthogonal plane to a rotation center line of a turbine and a recessed blade surface that is this hollow partial blade surface passes through the blade root side of the tie-boss at least in a region on the pressure side and extends in a strip shape in the blade chord length direction.
-
公开(公告)号：US11731221B2
公开(公告)日：2023-08-22
申请号：US17427321
申请日：2020-02-04
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B23P19/04 , B23P6/002 , B24C1/10 , B24C5/005 , B26F3/06 , B64C11/205 , F01D5/005 , F01D5/288 , F05D2230/10
Abstract: A method for separating a first mechanical part from a second mechanical part is described, wherein the second mechanical part is bonded to the first mechanical part by an adhesive film along a connecting area, the first mechanical part having a first specific thermal conductivity and the second mechanical part having a second thermal conductivity that is higher than the first thermal conductivity. The method includes at least one cooling step during which the second mechanical part is cooled to a negative temperature and at least one stressing step during which the second mechanical part is subjected to mechanical stress in order to cause the adhesive film to break.
-
公开(公告)号：US11702987B2
公开(公告)日：2023-07-18
申请号：US17480325
申请日：2021-09-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Scott A. Kovach , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine article includes a baffle that is configured to be mounted in a cavity of a gas turbine engine component. The baffle has a baffle wall that circumscribes an open interior region. The baffle wall includes a forward wall, side walls, and an aft wall. The side walls include impingement orifices, and the aft wall defines two datum features. At least one of the datum features is a dimple that is a portion of a sphere.
-
-
-
-
-
-
-
-
-
Search Results
880
records
(took 0.018 seconds)
