-
公开(公告)号：US11365632B2
公开(公告)日：2022-06-21
申请号：US16881358
申请日：2020-05-22
摘要： A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles disposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (437 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.
-
公开(公告)号：US11318553B2
公开(公告)日：2022-05-03
申请号：US16240308
申请日：2019-01-04
发明人： Paul Sheedy , John A. Sharon , Wayde R. Schmidt
摘要： An embodiment of a method includes fabricating a first single crystal boule having a uniform composition and grain orientation. The first uniform single crystal boule is divided into a first plurality of layered shapes. The shapes of the first plurality are stacked with at least a second plurality of layered shapes along a first axis. The second plurality of layered shapes have at least one physical aspect differing from at least one corresponding physical aspect of the first plurality of layered shapes. The first plurality of layered shapes and at least the second plurality of layered shapes are joined via a field assisted sintering technique (FAST) to form a bulk component.
-
公开(公告)号：US10913122B2
公开(公告)日：2021-02-09
申请号：US16207816
申请日：2018-12-03
发明人： Eric Fromerth , Daniel J Wright , Chung Y. Wu
摘要： A forming tool for forming leading edges of turbine blades is disclosed. In various embodiments, a forming tool may comprise a cylindrically-shaped body having a notch around the circumference of the cylindrically-shaped body. The notch may be positioned perpendicularly to a center axis of the cylindrically-shaped body. Further, the notch may have a notch contour with an upper notch contour and a lower notch contour, and where the notch contour is a relief of a selected turbine blade leading edge. The forming tool may be a grinding tool or a cutting tool. Moreover, a forming process may comprise forming, by a forming tool, a first portion of a turbine blade leading edge with a rough edge result, and forming, by a milling cutter, a second portion of the turbine blade leading edge with a rough edge result.
-
公开(公告)号：US10793943B2
公开(公告)日：2020-10-06
申请号：US15922230
申请日：2018-03-15
发明人： Eric W. Malmborg
IPC分类号： B33Y10/00 , F01D5/14 , F01D5/16 , F01D5/20 , C23C4/134 , B23K10/02 , B23P15/02 , C23C4/08 , F01D5/28 , B33Y80/00 , B23K101/04
摘要： A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.
-
公开(公告)号：US20200040745A1
公开(公告)日：2020-02-06
申请号：US16051560
申请日：2018-08-01
摘要： Cladding material is applied by laser to a net-shape. A method of cladding a host component includes installing the component in a fixture. A shroud component is located against the host component adjacent a select location for the cladding. Cladding is applied to the host component to the select location and adjacent to shroud component so that the shroud component defines an edge of the cladding as applied. The edge of the cladding as defined by the shroud component defines a desired cladding profile requiring no/approximately no post-cladding processing to remove over-cladded material.
-
公开(公告)号：US10480528B2
公开(公告)日：2019-11-19
申请号：US15659128
申请日：2017-07-25
申请人： ROLLS-ROYCE plc
IPC分类号： F04D29/38 , B21D26/027 , B21D26/029 , B21D26/059 , B23P15/02 , F04D29/02
摘要： An aerofoil structure with a hollow cavity is manufactured by diffusion bonding and superplastic forming. Outer panels are formed of a first material; a membrane is formed of a second material. Stop-off material is applied to preselected areas on at least one side of the membrane or of one of the panels so as to prevent diffusion bonding between the panels and the membrane at the preselected areas. The panels and the membrane are arranged in a stack and a diffusion bonding process is performed to bond together the first and second panels and the membrane to form an assembly. A superplastic forming process is performed at a forming temperature to expand the assembly to form the aerofoil structure. The forming temperature is selected so that the second material undergoes superplastic deformation at the forming temperature and the first material does not undergo superplastic deformation at the forming temperature.
-
公开(公告)号：US20190284675A1
公开(公告)日：2019-09-19
申请号：US15922230
申请日：2018-03-15
发明人： Eric W. Malmborg
摘要： A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.
-
公开(公告)号：US10384326B2
公开(公告)日：2019-08-20
申请号：US14977374
申请日：2015-12-21
IPC分类号： B24B39/00 , B24B39/06 , B23P15/02 , F01D5/02 , B23D45/00 , B24B27/00 , B24B41/06 , B24C1/00 , B24B7/04 , B24B7/16 , B26F3/00 , F01D5/00
摘要： Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or repaired turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface rotates about a second axis of rotation substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.
-
公开(公告)号：US10384316B2
公开(公告)日：2019-08-20
申请号：US14964653
申请日：2015-12-10
IPC分类号： B23P6/00 , C22C19/05 , C22F1/10 , F01D5/14 , B23P15/02 , B23K9/04 , B23K9/167 , B23K9/235 , B23K10/02 , B23K15/00 , B23K26/34 , F01D5/00 , B23K101/00 , F01D5/28
摘要： Method of repairing and manufacturing of turbine engine components includes application of a transition layer by fusion welding with dissimilar nickel based filler material, preferably comprising from about 0.05 wt. % to about 1.2 wt. % B and other alloying elements, followed by a diffusion and primary aging heat treatment and application of the top oxidation resistance layer using dissimilar nickel based filler materials comprised 3-6 wt. % Al, 0.5-6 wt. % Si, 12-25 wt. % Cr and other alloying elements that enhance strength and oxidation resistance followed by a secondary aging heat treatment and machining of the repaired area to restore geometry of turbine engine components. The inventions also relates to a turbine engine components repaired and manufactured by the method.
-
公开(公告)号：US20190106994A1
公开(公告)日：2019-04-11
申请号：US16151476
申请日：2018-10-04
摘要： Aspects of the disclosure are directed to a method for processing a component that includes a substrate and a coating coupled to the substrate, the method comprising: applying a laser beam to the coating in a first stage, the first stage characterized by a first number of pulses of the laser beam and a first offset corresponding to a focal point of the laser beam coinciding with an exterior surface of the coating, and applying the laser beam to the coating in a second stage, the second stage characterized by a second number of pulses of the laser beam and a second offset corresponding to the focal point of the laser beam being located within a span of the substrate.
-
-
-
-
-
-
-
-
-
搜索结果
872 条记录 (耗时 0.124 秒)