General Electric Company

General Electric Technology Gmbh

Brett Darrick Klingler

Matthew Stephen Casavant

David Martin Johnson

Kenneth Damon Black

James Bradford Holmes

Scott Edmond Ellis

Stuart Craig Hanson

Henry Grady Ballard, Jr

Wayne David Sullivan

Christopher Paul Cox

George Martin Gilchrist

Thomas Michael Merlau

Bradley Edwin Wilson

Gregory Tempel

Kenneth Blank

Kenneth D Black

A system is provided, including a heat management system. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a first zone of a turbomachinery, and a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the first zone, to minimize or to eliminate positional changes, structural changes, or a combination thereof, in one or more components of the turbomachinery due to thermal energy.

Turbomachinery heat management system

An apparatus for lifting an inner casing of a turbine includes a base, an arm, a guide roller, and an adjustment system. The arm has a first end and a second end, and is pivotally connected to the base intermediate the first end and the second end. The guide roller is operatively coupled to the first end of the arm to rotatably engage an exterior surface of the inner casing, and an adjustment system extending from the base and engaging the arm to change an angular position of the arm relative to the base and adjust a position of the guide roller relative to the exterior surface of the inner casing.

Turbine casing jack

A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor.

System and method for blade tip clearance control

A system for reducing leakage between static and rotating components within a turbine includes a static structure that is disposed radially outward from a tip of a rotating component. The static structure includes a seal assembly slot formed therein. A seal assembly includes a support block that is disposed within the seal assembly slot. A sealing material is disposed along a bottom portion of the support block and a tip slot is formed within the sealing material. The support block includes a forward portion that is slideably engaged with a forward inner surface of the seal assembly slot and an aft portion that is slideably engaged with an aft inner surface of the seal assembly slot. The system further includes a spring that extends axially between an aft wall of the seal assembly slot and an aft wall of the support block.

Turbine sealing system

An article of manufacture includes a first member configured to be attached to a first support structure, a second member configured to be attached to the first member, and an externally threaded dowel configured to engage an internally threaded hole in the second member. The externally threaded member is also configured to contact the first member. Rotation of the externally threaded dowel adjusts a distance spanned by the first member and second member.

Adjustable gib shim

A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly.

Method and system for assembling and disassembling turbomachines

A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore.

Compression sleeve seal

According to one aspect of the invention, a turbine assembly includes a first static structure and a second static structure radially outward of the first static structure. The assembly also includes a support member placed in a recess of the second static structure, wherein the support member includes first and second curved surfaces to contact the first and second static structures, respectively, and wherein the support member includes a biasing structure to retain the support member in the recess.

Growing community of inventors

Greenville, SC, United States of America

Brett Darrick Klingler