General Electric Company

Ge Infrastructure Technology, LLC

Thomas Alan Mogle, Ii

Sandra Beverly Kolvick

Stuart Craig Hanson

Michael Alan Davi

Robert Joseph Rohrssen

John William Herbold

Robert Edward Huth

Kyle Joseph Conger

Eric Lynn Strunk

William Thomas Ordean

Daryl Paul Capriotti

Glen William Brooksby

James Bradford Holmes

James Scott Flanagan

Wayne David Sullivan

Adrian Adam Klejc

Lukasz Sajdak

Thomas Michael Merlau

Travis Edwin Lipstein

Christopher David Runkel

Andrew James Fisher

Jun Yang

Rubi Elizabeth Triana Zorsano

Troy Lee Smith

Loy Milton Miller, Jr

Taylor Janae Million

Gilberto Betancourt Salinas

Mark Andrew Haley

Marcus Nolan Adams

A guide for cutting a dowel pin of a rotor assembly is provided. The guide includes a catch basin, including a first catch basin portion and a second catch basin portion, and a shim. The first catch basin portion and the second catch basin portion form a cutting tool receiver. The shim extends from a first edge having a cross-section that is complementary to a surface of the rotor assembly. The first catch basin portion and the second catch basin portion form a receptacle that accommodates and retains portions of a dowel pin during and after removal of the dowel pin from the rotor assembly. The cutting tool receiver is defined by a receiver edge configured to guide a cutting surface of a cutting tool through a cross-section of a dowel pin.

Apparatus and method for guiding a cutting/drilling tool and capturing generated foreign material

A tooling assembly for installation relative to a first and second turbomachine component is provided. The tooling assembly includes an axial mounting portion removably couplable to the first turbomachine component. The axial mounting portion includes a first plate, a second plate spaced apart from the first plate, and at least one turnbuckle assembly that extends between, and is coupled to, the first plate and the second plate. At least one of the first plate and the second plate include a radial compression portion. The radial compression portion includes a compression bar radially movable relative to the axial mounting portion and configured to contact the second turbomachine component.

T-fairing installation tooling assembly

An apparatus configured to support a diffuser segment during removal from and installation into an assembly. The apparatus includes a body having two or more supports and at least two clamp rods. The clamp rods each extend from a first end to a second end. The body defines a pocket extending between the supports on a first side of the clamp rods. An end clamp releasably mates with the second end of each clamp rod. The end clamp has a foot extending into the first side of the clamp rod. A wheel is received within each support. The pocket and the foot of each end clamp releasably retain a diffuser segment and the wheels rotate to allow the diffuser segment to be removed without damaging a surface coating of the diffuser segment.

Method for removing or installing a diffuser segment of a turbine assembly

a tooling assembly for installation relative to a first and second turbomachine component is provided. The tooling assembly includes an axial mounting portion removably couplable to the first turbomachine component. The axial mounting portion includes a first plate, a second plate spaced apart from the first plate, and at least one turnbuckle assembly that extends between, and is coupled to, the first plate and the second plate. At least one of the first plate and the second plate include a radial compression portion. The radial compression portion includes a compression bar radially movable relative to the axial mounting portion and configured to contact the second turbomachine component.

Tooling assemblies and methods are provided. A tooling assembly includes a first plate, a second plate spaced apart from the first plate, and one or more members extending between the first plate and the second plate. The tooling assembly further includes a plurality of blocks mounted to the one or more members and arranged in one or more rows between the first plate and the second plate. The at least one block in the plurality of blocks defines an opening that corresponds with an exterior shape of a mounting portion of the rotor blade.

Tooling assembly and method for removal of a rotor blade

Apparatus and method for protecting a replacement part of a turbine assembly

The present disclosure is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner and a casing, with the casing including a flange spaced apart from the liner along an axial centerline of the combustor. Furthermore, the axial retention assembly may include a mounting plate having a first end removably coupled to the flange and a second end positioned inward from the casing in a radial direction. Moreover, the axial retention assembly may include a clamp removably coupled to the liner. Additionally, the axial retention assembly may include a tie rod coupled to the second end of the mounting plate and the clamp to reduce relative movement between the liner and the casing along the axial centerline.

Axial retention assembly for combustor components of a gas turbine engine

The present subject matter is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having include a liner defining a liner aperture extending therethrough. Additionally, the combustor may further include a sleeve defining a sleeve aperture extending therethrough, with the sleeve positioned radially outward from and at least partially circumferentially positioned around the liner. Furthermore, the axial retention assembly may include a frame having a mounting projection positioned within the sleeve aperture. Moreover, the axial retention assembly may include a clamp plate adjustably coupled to the frame. In addition, the axial retention assembly may include a clamp plate adjustment rod extending through the liner aperture and threadingly engaging the clamp plate such that relative movement between the liner and the sleeve along the axial centerline is reduced.

A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.

System and method for measuring eccentricity of turbine shell relative to turbine rotor

Methods of replacing flex seals in exhaust frames of turbine systems are disclosed. The method may include removing a section of an outer casing of an exhaust frame to form an opening within the outer casing. The section may be formed within a flow path of the exhaust frame. The method may also include removing the flex seal from the exhaust frame via the opening formed within the outer casing, inserting a distinct flex seal within the exhaust frame via the opening formed within the outer casing, and covering the opening formed within the outer casing of the exhaust frame.

Methods of replacing seals in exhaust frames of turbine systems and related components

This disclosure provides tools for installing and removing a combustion liner in a combustion casing. A mounting frame has fasteners positioned circumferentially around an end casing surface of the combustion casing and removably attaches the mounting frame to the combustion casing. A positioning member has pushing surfaces and pulling surfaces distributed circumferentially around the combustion liner. An axial positioning mechanism engages the mounting frame and the positioning member along a common axis. The axial positioning mechanism incrementally positions the positioning member relative to the mounting frame by adjusting a positioning distance between the mounting frame and the positioning member.

Combustion liner tool

Various embodiments include apparatuses for performing maintenance on a gas turbine (GT) nozzle, along with related methods. One apparatus can include: a nozzle engagement sled for releasably engaging the nozzle, the nozzle engagement sled including: a sled body; a locking member coupled with the sled body, the locking member sized to complement a slot in the nozzle; a sled slot within a side of the sled body, the sled slot for engaging a rail within the GT; and at least one wheel for transporting the sled body within the GT.

Nozzle maintenance apparatus and method

An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar having a handle at one end and a force applying member at an opposing end of the elongated bar. An attachment member is configured for attachment to a flange of the combustion case. The attachment member is also configured for pivotal attachment to the elongated bar. The apparatus is configured to apply a radially outward force on a downstream portion of the combustion liner when a radially inward force is applied to the handle.

Method and apparatus for servicing combustion liners

A combustor assembly alignment system comprises an alignment plate comprising a plurality of alignment plate holes that align with a plurality of combustor assembly flange holes, an alignment plate securement system configured to secure the alignment plate to a combustor assembly flange by passing through a first alignment plate hole of the alignment plate and a first combustor assembly flange hole of the combustor assembly flange, and an alignment tube that extends away from the alignment plate, wherein a hollow interior of the alignment tube aligns with a second combustor assembly flange hole when the alignment plate is secured to the combustor assembly flange.

Growing community of inventors

Simpsonville, SC, United States of America

Thomas Alan Mogle, Ii