General Electric Company

General Electric Technology Gmbh

Arthur Samuel Peck

Jon Conrad Schaeffer

Michael Douglas Arnett

Srikanth Chandrudu Kottilingam

Akane Suzuki

Warren Tan King

Jian Zheng

Yan Cui

Kevin Weston McMahan

Canan Uslu Hardwicke

Ronald Ralph Cairo

Pazhayannur Ramanathan Subramanian

Michael F Henry

Jason Robert Parolini

Maxim Konter

Richard DiDomizio

Charles Gitahi Mukira

Timothy Hanlon

Shenyan Huang

Shan Liu

Thomas Michael Moors

Christopher Michael Penny

James Eric Reed

Srinivasan Raghavan

Paul S Dimascio

Stephen Joseph Balsone

Steven Charles Rauch

Chen Shen

Dayananda Narayana

Nicholas Vlessis

Gabriel DellaFera

A composition includes, by weight percent: Cobalt (Co) between about 4.5 and about 7.0; Chromium (Cr) between about 10.2 and about 11.5; Molybdenum (Mo) between about 0.5 and about 2.5; Tungsten (W) between about 4.0 and about 5.5; Rhenium (Re) between about 0 and about 1.2; Aluminum (Al) between about 6.2 and about 6.8; Tantalum (Ta) between about 4.5 and about 6.0; Titanium (Ti) between about 0 and about 0.5; Hafnium (Hf) between about 0 and about 0.5; Carbon (C) between about 0 and about 0.2; Boron (B) between about 0 and about 0.02; and the balance Nickel (Ni), and other incidental impurities.

Nickel-based superalloy

Embodiments of the disclosure provide a turbomachine component, including: a base portion configured for mounting on a rotor; an airfoil portion having a first end coupled to the base portion, and a second end opposite the first end. A creep resistance of the airfoil portion is greater than the base portion, and a fracture toughness of the airfoil portion is less than the base portion. A tip portion may be coupled to the second end of the airfoil portion. A creep resistance of the tip portion is less than the airfoil portion and greater than the base portion. A fracture toughness of the tip portion is less than the base portion and greater than the airfoil portion.

System and method to apply multiple thermal treatments to workpiece and related turbomachine components

In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Nickel-based superalloy with microstructure including rafting-resistant gamma prime phase and article prepared therefrom

A method of treating a substrate of a turbomachine component includes applying a coating to a surface of the substrate of the turbomachine component and peening the substrate after applying the coating to the surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate. A method of treating an internal surface of a turbomachine component includes directing a peening force at the internal surface within a cooling passage of the turbomachine component.

Peening coated internal surfaces of turbomachine components

A casting method and cast article are provided. The casting method includes providing a casting furnace, the casting furnace including a withdrawal region in a lower end, positioning a mold within the casting furnace, positioning a molten material in the mold, partially withdrawing the mold a withdrawal distance through the withdrawal region in the casting furnace, the withdrawal distance providing a partially withdrawn portion, then reinserting at least a portion of the partially withdrawn portion into the casting furnace through the withdrawal region, and then completely withdrawing the mold from the casting furnace. The reinserting at least partially re-melts a solidified portion within the partially withdrawn portion to reduce or eliminate freckle grains. The cast article includes a microstructure and occurrence of freckle grains corresponding to being formed by a process comprising partially withdrawing, reinserting, and completely withdrawing of a mold from a casting furnace to form the cast article.

Casting method and cast article

A method of forming a component having an internal passage defined therein includes positioning a jacketed core with respect to a mold. The jacketed core includes a hollow structure formed from a first material, an inner core disposed within the hollow structure, and a core channel that extends from at least a first end of the inner core through at least a portion of inner core. The method also includes introducing a component material in a molten state into a cavity of the mold, such that the component material in the molten state at least partially absorbs the first material from the jacketed core within the cavity. The method further includes cooling the component material in the cavity to form the component. The inner core defines the internal passage within the component.

Method and assembly for forming components having internal passages using a jacketed core

A method for forming a CMC article is disclosed, including forming a CMC precursor ply assembly. Forming the CMC precursor ply assembly includes laying up a plurality of CMC precursor plies and entraining a melt infiltration agent to form an entrained agent supply. Each of the plurality of CMC precursor plies includes a matrix precursor and a plurality of ceramic fibers. The plurality of CMC precursor plies and the entrained agent supply are arranged to form the CMC precursor ply assembly, which includes an article conformation. The method further includes carbonizing the CMC precursor ply assembly, infusing the melt infiltration agent from the entrained agent supply into the plurality of CMC precursor plies, and densifying the CMC precursor ply assembly with the melt infiltration agent to form the CMC article.

Method for forming CMC article

A casting method and cast article are provided. The casting method includes providing a casting furnace, the casting furnace including a withdrawal region in a lower end, positioning a mold within the casting furnace, positioning a molten material in the mold, partially withdrawing the mold a withdrawal distance through the withdrawal region in the casting furnace, the withdrawal distance providing a partially withdrawn portion, then reinserting at least a portion of the partially withdrawn portion into the casting furnace through the withdrawal region, and then completely withdrawing the mold from the casting furnace. The reinserting partially re-melts a solidified portion within the partially withdrawn portion to fill pores formed therein with the molten material. The cast article includes a microstructure and a porosity corresponding to being formed by a process comprising partially withdrawing, reinserting, and completely withdrawing of a mold from a casting furnace to form the cast article.

A combustion system including a transition piece and method of forming the transition piece using a cast nickel-based superalloy is provided. The transition piece includes a body defining a flowpath and enclosure, the body having a circular inlet section for receiving combustion product from the combustor and an outlet end for flowing the combustor products into a first stage nozzle of a gas turbine. The transition piece comprises a one-piece single casting construction of the circular inlet section, the body, and the outlet end. The transition piece is formed from a nickel-based superalloy. The transition piece has a thick-to-thin ratio of wall thickness of thick transition to wall thickness of thin transition of about 1.1 to about 2.5.

Combustion system including a transition piece and method of forming using a cast superalloy

A grain starter for use in solidification of molten metallic material forming an article having a directional grain structure and a method for solidifying an article having a directional grain structure with a substantial absence of stray grains. The grain starter comprises a grain-starting material that initiates grain growth in the molten metallic material in a preselected crystallographic direction. The grain-starting material has a melting temperature higher than the metallic material forming the article lest the grain starter be modified by contact with the molten material. The grain starter further includes a feature that modifies heat transfer characteristics of the metallic material in contact with it in order to produce an article having grains oriented in the preselected crystallographic orientation and modifies the profile of the advancing solidification front. The article is substantially free of stray grains not oriented in the preselected crystallographic direction.

Composite geometrical design for a grain starter in a bridgman investment casting process

A turbine bucket includes an airfoil and a shroud. The shroud includes first and second bearing surfaces, and the first and second bearing surfaces each comprise a single grain structure. A method for forming a turbine bucket includes orienting a mold vertically, wherein the mold includes a first portion that defines a shank, a second portion connected to the first portion that defines an airfoil, and a third portion connected to the second portion that defines a shroud, wherein the third portion includes first and second sides, and wherein the first portion is higher than the second portion and the second portion is higher than the third portion. The method further includes flowing a molten metal into the mold and selectively growing large single grains in at least one of the first or second sides.

System and method for reducing grain boundaries in shrouded airfoils

A method of assembling a fuel delivery system is provided. The method includes providing a base that includes a surface, a receptacle extending into the base from the surface along a longitudinal axis, and a plurality of channels extending into the base from the receptacle. Each of the plurality of channels includes an inlet end and an outlet end, and each of the plurality of channels intersects the receptacle at the outlet end, wherein the receptacle and the plurality of channels are formed integrally within the base such that the plurality of outlet ends are spaced axially from one another. The method further includes securing a fuel nozzle within the receptacle, the fuel nozzle including a plurality of separate flow paths, wherein each of the plurality of channels is in flow communication with one of the plurality of separate flow paths.

Fuel delivery system and method of assembling the same

Nickel based alloys are provided comprising from about 7.0 weight percent (wt %) to about 12.0 wt % chromium, from about 0.1 wt % to about 5 wt % molybdenum, from about 0.2 wt % to about 4.5 wt % titanium, from about 4 wt % to about 6 wt % aluminum, from about 3 wt % to about 4.9 wt % cobalt, from about 6.0 wt % to about 9.0 wt % tungsten, from about 4.0 wt % to about 6.5 wt % tantalum, from about 0.05 wt % to about 0.6 wt % hafnium, up to about 1.0 wt % niobium, up to about 0.02 wt % boron, and up to about 0.1 wt % carbon, with the remainder being nickel and incidental impurities. The alloys may be cast, directionally solidified and heat treated to provide articles having a gamma prime fraction of greater than about 50%.

Nickel-based superalloys and articles

A process for filling openings, including blind holes, through-holes, and cavities, in high temperature components. The process entails forming a powder mixture by mixing particles of at least a base alloy and a second alloy that contains a sufficient amount of a melting point depressant to have a lower melting temperature than the base alloy. The powder mixture is combined with a binder and compacted to form a compacted preform, which is then heated to remove the binder and form a rigid sintered preform. The sintered preform is produced, or optionally is further shaped, to have a cross-sectional shape and dimensions to achieve a clearance of up to 200 micrometers with the opening, after which the preform is placed in the opening and diffusion bonded within the opening to form a brazement comprising the particles of the base alloy dispersed in a matrix formed by the second alloy.

Process of filling openings in a component

A gas turbine airfoil is disclosed. The gas turbine airfoil includes a root section, a separate extension section attached to the root section, and a joint disposed between the root section and the extension section, the joint including at least one of a mechanical interlock and a metallurgical bond.

Growing community of inventors

Greenville, SC, United States of America

Arthur Samuel Peck