General Electric Company

Dresser-rand Company

Graham David Sherlock

Paul Lawrence Kalmar

Christopher Edward Thompson

Lynn Charles Gagne

Benjamin Erick Baker

Brian Peter Arness

Daniel Anthony Nowak

Thomas Robbins Tipton

Joseph Leonard Moroso

Timothy R Griffin

Kelvin Rono Aaron

Anshuman Singh

Stephen Joseph Balsone

Paul V Sickles

Stewart William Beitz

Todd Moran

Nicholas Vachon

Patrick Mohr

Francis Edward Nimmons

Atif Muhammad Aliuddin

Graydon Wayne Peters

Dillon R Jourde

Larry Paul Wencil

J David Mays

Americo Zapata

David L Sanchez

David L Bollinger

Greg T Snyder

Justin C Armstrong

Francis E Nimmons

Paul L Kalmar

Turbine blade for a turbine blade attachment assembly

A system and method for repairing a turbine. The method includes applying a coating on an outer surface of a tenon that extends from a stator vane. The tenon may be inserted at least partially into an opening defined by an inner shroud segment of the turbine. A bushing may be inserted at least partially into the opening in the inner shroud segment of the turbine such that the tenon becomes at least partially disposed within an opening defined by the bushing. A bolt may be inserted through the opening in the bushing and at least partially into an opening defined by the tenon. The bolt may be threadably engaged with the tenon.

F-class gas turbine compressor exit guide vane repair

A turbomachine diaphragm includes a sealing section having a first end portion that extends to a second end portion through an intermediate portion. At least one rail member includes a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section. The second end section includes a machined surface having a repair coupon mounting element. A repair coupon is mounted at the repair coupon mounting element and operatively connected to the at least one rail member. A method of repairing a turbomachine diaphragm is also disclosed herein.

Turbomachine diaphragm and method of repairing a turbomachine diaphragm

A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.

Methods and apparatus for fabricating a turbine nozzle assembly

An apparatus and method are provided for removing a blade from a dovetailed slot in a wheel of a rotating machine. At least one device is adapted to apply a pushing force on a first surface of a blade. A turntable for supporting the wheel has indexing capability to advance the wheel by a predetermined amount. The device can be used to remove one or more blades from the wheel.

Apparatus and method for removing compressor blades

A method for forming an opening in two different turbine components is provided. The method includes coupling a clamp to a base and coupling the clamp to a clamp bar, wherein the clamp bar is moveable with respect to the base. A first bushing plate is selected based on a first turbine component being drilled and is removably coupled to the base. A bushing is removably coupled to at least one aperture extending through the first bushing plate. An opening is formed in the first turbine component. A second bushing plate is selected based on a second turbine component being drilled. The second turbine component is different from the first turbine component. The second bushing plate is removably coupled to the base. An opening is formed in the second turbine component.

Method and apparatus to secure a component in position for fabrication

A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.

Method and apparatus for assembling blade shims

An assembly is provided for cropping the trailing edge tip of a stator zero blade in-situ. The cropping assembly includes a base plate that is secured to the end of the compressor stator blade to be cropped; a removable, rotational guide block; and a drill that is mounted to the guide block and rotatable relative to the base plate to crop the trailing edge tip of a stator blade.

In-situ compressor blade tip cropping assembly and method

An inspection tool for a turbine bucket shroud includes: a clamp device for clamping a dovetail portion of a turbine bucket; a template plate provided with an aperture defined by a edge shaped to conform to a specified shape of the turbine bucket shroud, wherein the template is moveable to a location over the turbine bucket shroud in a direction toward the clamp device, and wherein, at the location, the aperture represents a design specification location for the turbine bucket shroud relative to the dovetail portion of the bucket. A measurement gauge is provided for measuring gaps between edges of the shroud and edges of the template aperture.

Inspection tool for measuring bucket Z notch position

A tool capable of removing material is applied to a turbine wheel cooling slot. Material is removed from a selected portion of the cooling slot with the tool. And, stress concentrations are reduced within the slot through the removal of material.

Apparatus to remove material from a turbine wheel in-situ

A measuring tool measures a trailing edge position of gas turbine nozzle. The tool includes a frame member attachable to at least one predefined reference point on the nozzle. At least one sliding member is slidable relative to the frame member and includes a measuring point engageable with the trailing edge. A position of the sliding member relative to the frame member is determinative of the trailing edge position.

Nozzle trailing edge position measurement and marking

A method for inspecting a turbine nozzle segment includes positioning the turbine nozzle segment on a base of a tool, with the outer forward face and the inner forward face of the turbine nozzle segment contacting a surface of the base. The outer wall is positioned between a first pedestal outer stand and a second pedestal outer stand of the tool, and the inner wall is positioned between a first pedestal inner stand and a second pedestal inner stand of the tool. At least one of a position, a depth and a width of a seal slot formed in a side edge of the outer wall and/or the inner wall is measured. At least one axial dimension of the turbine nozzle segment and at least one radial dimension of the turbine nozzle segment are measured.

Method and apparatus for inspecting turbine nozzle segments

A tip cap for use in a turbine bucket. The tip cap may include a shield of an oxidant resistant material and a cap positioned within the shield of a high strength material.

Bi-layer tip cap

A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.

Growing community of inventors

Greenville, SC, United States of America

Graham David Sherlock