Siemens Westinghouse Power Corporation

Siemens Power Generation, Inc.

Gary W Swartzbeck

Paula D Freyer

Michael Anthony Burke

Brij B Seth

Thomas Walter Zagar

Mohan A Hebbar

Greg P Wagner

A tooling for affecting the repair of turbine blade tips which generates bond line loads as a result of differential thermal expansion between the work piece and the fixture. The fixture accommodates multiple work pieces of different sizes to facilitate a batch repair process and compressive load limits are established by insertion of deformable compression rings.

Bonding fixture

High efficiency, thin-walled turbine components such as turbine blade airfoils comprise a superalloy substrate covered by a thin skin. The thin skin may be bonded to the inner spar structure of a turbine blade airfoil by a transient liquid phase bonding process. The inner spar preferably comprises a cast single crystal nickel base superalloy. The thin skin may comprise a single crystal or polycrystalline nickel base superalloy or the like.

Turbine components comprising thin skins bonded to superalloy substrates

A method of repairing gas turbine engine components is provided. The method includes removing the damaged portion and fabricating an insert to match the removed portion. The insert is precision machined and crystallographically matched to the original component, and then bonded to this component using transient liquid phase bonding techniques and suitable heat treatment.

Transient liquid phase bonding repair for advanced turbine blades and vanes

A method of consolidating or repairing turbine component parts, such as turbine blades ( ), requires providing a turbine component part ( ), establishing a contact pressure between the opposing surfaces ( ), where, optionally, fine particles may be present between such surfaces ( ), and then generating an electrical field to provide heat, and applying pressure on the opposing surfaces, resulting in high temperature spark plasma sintering to provide a consolidated turbine blade ( ).

Repair and fabrication of combustion turbine components by spark plasma sintering

Large gas turbine blades made from separate cast segments of superalloys are disclosed. The turbine blade is designed such that bond lines between adjacent segments are placed in low stress regions of the blade. The cast superalloy segments of the blades are aligned and fitted together with specified tolerances. The turbine blade segments are then joined by transient liquid phase bonding, followed by a controlled heat treatment which produces the desired microstructure in the bond region. The method allows for the production of large, high quality turbine blades by joining small, high quality cast superalloy sections, in comparison with prior attempts to cast large turbine blades as single pieces which have produced very low yields and high individual component costs.

Turbine blades made from multiple single crystal cast superalloy segments

A method of bonding cast superalloys is disclosed. The method includes the steps of casting separate superalloy component parts, machining the mating surfaces of the separate parts in a controlled manner to avoid recrystallization of the material and to ensure a tight fit between the parts, bonding the parts together, and thermally treating the bonded component. In a preferred embodiment, the component is a turbine blade for a land-based gas turbine.

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North Huntingdon, PA, United States of America

Gary W Swartzbeck