General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Daniel James Dorriety

Brian Leslie Henderson

Paul Albert Cook

Yan Cui

Mark Carmine Bellino

Lawrence James Whims

Kyle J Lewis

Caitlin Shea Lucking

Patrick Yerkes

Brian Lee Tollison

Steven Charles Woods

Shan Liu

Srikanth Chandrudu Kottilingam

Dechao Lin

Surinder Singh Pabla

Stanley Frank Simpson

Heath Michael Ostebee

Charles Van Buchan

Cem Murat Eminoglu

James Ryan Connor

Dennis William Cavanaugh

Robert Wade Clifford

Nuo Sheng

James Carroll Baummer

Gary Charles Shubert

Andrea Booher Kretschmar

Mustafa Yuvalaklioglu

Hai Buu Sam

Ryan T Smith

Alioune Dieng

Efe Bulut

Ravikumar Rayachuri

Abdul Rahman Shariff

Vinod P Pareek

A braze tape includes a first portion, a second portion, and a central portion located between and adjacent to the first portion and the second portion. The first portion includes a low melting temperature alloy material, the second portion includes a high melting temperature alloy material, and the central portion includes a mixture of the low melting temperature alloy material and the high melting temperature alloy material. The central portion may gradually change between the low melting temperature alloy material and the high melting temperature alloy material. A related method is also disclosed.

Braze tape with central region with low and high melting temperature alloy material, and related method

A turbine system component includes a body having an exterior surface, and a cooling passage defined in the body. The cooling passage has a first cross-sectional area in the body. The component also includes a hollow member defining a first exit opening at the exterior surface of the body and coupled in the cooling passage. The hollow member, at the first exit opening, has a second cross-sectional area that is less than the first cross-sectional area, creating an exit opening with a smaller dimension than the original cooling passage. The hollow member is made of a material having a melt temperature higher than an operating temperature of the turbine system. The hollow member(s) reduces the cooling capabilities of the cooling passage. A cooling profile of the component can be generated to identify those cooling passages having excess cooling so they can have their exit openings reduced in cross-sectional area.

Cooling passage exit opening cross-sectional area reduction for turbine system component

A method for redirection of coolant flow is provided. The method includes an identifying step that identifies a hot spot on an exterior surface of a body of a component of a turbine system. A first parameter of the component indicates that a temperature of the exterior surface in the hot spot exceeds a threshold value. Another identifying step identifies a cool spot on the exterior surface. A second parameter of the component indicates that the temperature of the exterior surface in the cool spot is below the threshold value. A reconfiguring step reconfigures a plurality of cooling passages of the component to direct a portion of a coolant from the cool spot to the hot spot.

Thermal profile based redirection of turbine system component coolant by targeted alteration of cooling passage exit opening cross-sectional area

A system for creating a braze joint within a component. The system includes an environment operable to reach a braze temperature sufficient to melt at least a portion of a braze material. The system also includes a component within the environment, the component including a base having a base surface, a recess depending from the base surface into the base to an inner edge, and a braze material within the recess and forming a cap above the base surface. The braze material fills the recess from the cap to the inner edge. The cap has an exposed braze surface. The system also includes an insulation layer that at least partially covers the exposed braze surface.

Braze joints for a component and methods of forming the same

A method of repairing a superalloy component includes subjecting the superalloy component, including a repair area, to a phase agglomeration cycle, which includes stepped heating and controlled cooling of the component. The method further includes applying weld material to the repair area to create a weld surface; and covering the weld surface with brazing material. The component is then subjected to a braze cycle to produce a brazed component. The brazed component is cleaned, and the cleaned component is subjected to a restorative heat treatment to restore the microcrystalline structure and mechanical properties of the component.

Method of repairing superalloy components using phase agglomeration

A method of brazing a treatment area of a load-bearing component includes applying a repair material over the treatment area of the component and positioning an induction brazing coil having a geometry corresponding to the treatment area over the repair material and the treatment area. The method further includes heating the repair material utilizing the induction brazing coil to a temperature sufficient to cause at least partial melting of the repair material, thereby effecting a brazed joint between the treatment area and the repair material.

Method of brazing a treatment area of a load-bearing component

A method for treating a turbine diaphragm and a treated turbine diaphragm are provided. The method includes the step of removing a portion of the turbine diaphragm. The method further includes the step of forming a coupon having a geometry that corresponds to the portion of the turbine diaphragm removed. The method further includes joining the coupon to the turbine diaphragm. At least a portion of the coupon is a pre-sintered preform. The treated turbine diaphragm includes a substrate and a coupon joined to the substrate, wherein at least a portion of the coupon is a pre-sintered preform.

Treated turbine diaphragm and method for treating a turbine diaphragm

A method of welding a superalloy component includes the following sequential steps. A welding step for welding a cavity using a filler metal in an inert atmosphere, where the cavity is located in the component. A covering step for covering the filler metal and a portion of the component with a weld filler layer in the inert atmosphere. The weld filler layer has a greater ductility than material comprising the component and/or material comprising the filler metal. A second covering step for covering the weld filler layer with a braze material, and subsequently performing a brazing operation. A heat treating step heat treats the component.

Method of welding superalloys

A fixture and method for resistance welding of at least one pad to at least one surface of an article is disclosed. The method includes mounting the article in the fixture, placing the at least one pad on the at least one surface of the article, positioning a first electrode of a resistance welding apparatus to the at least one pad and a second electrode of the resistance welding apparatus to the article, and applying pressure and electric current across the at least one pad and the at least one surface. The fixture includes a first, second and third support element, which, respectively, include a first, second and third contact surface being adapted and disposed to support a first, second and third portion of the article. The first, second and third contact surfaces are each inelastic and electrically insulating. The fixture is arranged and disposed to non-rotatably cradle the article.

Fixture and method for resistance welding of a pad to a surface

A method to repair an opening in a metallic device including:

System and method to locate and repair insert holes on a gas turbine component

The present application provides a method of repairing a turbine blade. The method may include the steps of removing an existing tip cap from the turbine blade in whole or in part, machining the turbine blade to form a machined groove, positioning an insert in the machined groove, welding the insert to the turbine blade, and brazing the turbine blade.

Systems and methods for deep tip crack repair

The present application provides a hole reducing tool. The hole reducing tool includes a punch with a conical tip and a pilot and a slide hammer assembly attached to the punch.

Hole reducing tool

According to one aspect of the invention, a method for servicing a combustor cap assembly of a turbine includes determining a defect is present in a center ring of the cap assembly, the center ring being disposed within a plurality of vanes, removing the center ring from the cap assembly. The method also includes placing a replacement center ring in the cap assembly, wherein dimensions of the replacement center ring are substantially the same as the center ring that has been removed and brazing the replacement center ring to the plurality of vanes.

Method for servicing a combustor cap assembly for a turbine

A method of fabricating a component and a fabricated component are disclosed. The method includes depositing a material to a component and manipulating the material to form a boundary region and a filler region for desired properties. The component includes the boundary region and the filler region, thereby having the desired properties.

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Travelers Rest, SC, United States of America

Daniel James Dorriety