Siemens Energy, Inc.

Siemens Aktiengesellschaft

Siemens Power Generation, Inc.

Mikro Systems, Inc.

Siemens Energy Global Gmbh & Co. Kg

Other

Rolls-royce Corporation

Siemens Westinghouse Power Corporation

Allister William James

Douglas J Arrell

Anand A Kulkarni

Jay Alan Morrison

Gary Brian Merrill

Christian X Campbell

Ahmed Kamel

John Joseph Marra

Iain Fraser

Brian J Wessell

Raymond G Snider

Daniel M Eshak

Gerald Joseph Bruck

Jay Edgar Lane

Steven James Vance

Andrew Jeremiah Burns

Jan H Marsh

Paul J Gear

Brij B Seth

David B Allen

Benjamin E Heneveld

Randolph Clifford Helmink

Gregg P Wagner

Maurice Gell

Bruce A Ewing

Zafir A M Abdo

David W Hunt

Sushil K Jain

Kevin C Sheehan

Gerhard E Fuchs

Kenneth A Green

Christian X Campbell, Jr

Ravishankar P Angal

Phillip Behling

Iain Alasdair Fraser

Christian Xavier Campbell

Iain A Fraser

A method for attaching a first component composed of a ceramic matrix composite (CMC) to a second component composed of a metallic substructure is provided. The first component comprises at least two slots formed within a body of the first component and a configured to accommodate a thickness of a continuous CMC strap. The ends of the CMC strap are inserted into respective slots in the first component and then inserted into corresponding slots in a second component. The ends are secured to the second component by a fastening means thus securing the first component to the second component.

Method of securing a ceramic matrix composite (CMC) component to a metallic substructure using CMC straps

There is provided a process for heat treating a component () having a first section () and a section shot peened section (), the first section () and shot peened second section () formed from a nickel-based gamma prime strengthened superalloy. The process includes heating the first section () to at least a gamma prime solvus temperature thereof; and during the heating of the first section () to at least the gamma prime solvus temperature thereof, preventing the shot peened second section () from reaching a recrystallization temperature thereof.

Process for preventing recrystallization of shot peened blade roots during a heat treatment process

A method () of using hot isostatic pressing to join metallic members that form a component in a gas turbine engine is disclosed. The method () may include applying () a surface treatment to the outer surfaces () of first and second metallic members () based on whether a mechanical or metallurgical joint for the component is desired. Additionally, the method () may include aligning () the outer surfaces () of the first and second metallic members () to create a sealed cavity, which encompasses the joint, between the first and second metallic members (). Once the outer surfaces () are aligned, the method () may include subjecting () the members () to hot isostatic pressing such that material from the first metallic member () flows into a recess () within the second metallic member () so as to join the first and second metallic members () to form a consolidated component (). The consolidated component () may then be machined and finished () for use in a turbine engine.

Hot isostatic pressing system for the assembly of modular components usable in a turbine engine

A gas turbine engine blade (), including a base portion () having a cast wall, and a tip portion () attached to the base portion and having a wall () formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings () defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.

Gas turbine blade with corrugated tip wall

An additive manufacturing apparatus () including: a container () configured to bound a bed of powdered metal material; a fluidization arrangement () configured to fluidize the bed of powered material; an articulation mechanism () disposed within the container and configured to support and to rotate a component () about at least one horizontal axis; and an energy beam () configured to selectively scan portions () of a surface of the bed of powdered metal material to melt or sinter the selectively scanned portions onto the component.

Articulating build platform for laser additive manufacturing

A method of manufacturing an assembly (), including: positioning a first component () and a second component () in a desired positional relationship with each other; and building-up a locking component () by depositing layer after layer of material onto a surface () of the assembly until a completed locking component is formed in-situ that holds the first component and the second component in the desired positional relationship.

Mechanical joining using additive manufacturing process

A vane assembly () having: an airfoil () and a shroud () held together without metallurgical bonding there between; a channel () disposed circumferentially about the airfoil (), between the airfoil () and the shroud (); and a seal () disposed in the channel (), wherein during operation of a turbine engine having the vane assembly () the seal () has a sufficient ductility such that a force generated on the seal () resulting from relative movement of the airfoil () and the shroud () is sufficient to plastically deform the seal ().

Ductile alloys for sealing modular component interfaces

A component (A,B,C) has a core formed of a stack () of sheets () of material with cutouts (A) aligned to form passages () in the core. An outer casing () spans the stack axially (), brackets at least parts of opposed ends of the stack, and holds the sheets together in axial compression (). Respective cooperating elements () on the casing and the stack may register the casing with respect to the stack. Pins () in some sheets may engage holes () in adjacent sheets to register the sheets with each other. The casing may be segmented (A,B,C). A hoop () may be compressed around the segmented casing. A gas turbine fuel injector may be formed of a stack () with an inlet element () compressed () onto the stack by the casing ().

Product with internal passages made of stacked sheets with compressive casing

A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.

Method for repairing a component for use in a turbine engine

A pre-weld heat treatment of the nickel based superalloy including heating a nickel based superalloy (e.g., IN939) casting to 2120&#xb0; F. at a rate of 2&#xb0; F. per minute, and then soaking the casing for one hour at 2120&#xb0; F. The casting is then cooled in stages including slowly cooling the casting at a rate of 1&#xb0; F. per minute to about 1900&#xb0; F. and holding at that temperature for about 10 minutes. Then the casting is further slowly cooled at a rate of 1&#xb0; F. per minute to about 1800&#xb0; F. and holding at that temperature for about 10 minutes, and further slowly cooled to a temperature range of 1650&#xb0; F. to 1450&#xb0; F., and then fast cooled to room temperature. The pre-weld heat treatment may optionally include a step of heating the casting to about 1850&#xb0; F. at a rate of 50&#xb0; F. per minute before slowly heating to 2120&#xb0; F.

Pre-weld heat treatment for a nickel based superalloy

A structural layer () may be bi-cast onto ligaments () extending from a porous cooling construction (). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material () such as wax may be formed on the ligaments of the porous construction. A second fugitive material () such as ceramic may fill the remaining part of the porous construction. An investment casting shell () may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (), and the second fugitive material may be removed to provide coolant paths (). A second structural layer () may be bi-cast onto further ligaments () on a second side of the porous construction.

Bi-cast layered wall with a porous element for component cooling

Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component () and a preformed shroud heat resistant material () in a mold, wherein the airfoil component () and the shroud heat resistant material () each comprises an interlocking feature (); preheating the mold; introducing molten structural material () into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component () with respect to the preformed shroud heat resistant material () and is effective to provide structural support for the shroud heat resistant material (). Surfaces between the airfoil component () and the structural material (), between the airfoil component () and the shroud heat resistant material (), and between the shroud heat resistant material () and the structural material () are free of metallurgical bonds.

Multi-component assembly casting

Fabricating a core of a component (A,B,C) from a stack () of sheets () of material with cutouts (A) in the sheets aligned to form passages () in the core. A casing preform () is then fitted over the core. The preform is processed to form a casing () that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses () the sheets together. The preform may slide () over the core, and may be segmented (A,B,C) to fit over the core. A hoop () may be fitted and compressed around the segmented casing (A,B,C).

Hybrid manufacturing process and product made using laminated sheets and compressive casing

Bi-casting a platform () onto an end portion () of a turbine airfoil () after forming a coating of a fugitive material () on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (A,B) onto the end portion in opposite directions parallel to a chord line () of the airfoil or parallel to a mid-platform length () of the platform to form respective layers tapering in thickness from the leading () and trailing () edges along the suction side () of the airfoil.

Turbine airfoil to shroud attachment method

An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure.

Injection molded component

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Orlando, FL, United States of America

Allister William James