General Electric Company

Clement Gazzillo

John Thomas Murphy

Robert James Bracken

Stephen Roger Swan

Jeffrey Robert Simkins

Ronald Wayne Korzun

Rex Allen Morgan

Michael Alan Davi

David Orus Fitts

Norman Arnold Turnquist

Harold Lamar Jordan, Jr

Biao Fang

Bernard Arthur Couture, Jr

Mehmet Demiroglu

Hamid Reza Sarshar

William Thomas Parry

Edip Sevincer

Mark William Kowalczyk

Nestor Hernandez

John Cleland Lavash

Harold Lamar Jordan

Michael Joseph Boss

San-Dar Gau

Karen J Tyler

Denise Marie Parent

Steven John Croft

A turbine engine includes a turbine, a compressor for compressing air and a combustor for receiving the compressed air through an inlet passage and operable to burn fuel therewith to deliver hot exhaust gas to the turbine. Also included is a wheel space defined proximate to the combustor. Further included is a cooling air passage extending between the compressor and the wheel space. Yet further included is a valve assembly having a valve member disposed in the cooling air passage and operable to admit a cooling air to the wheel space in response to a condition therein.

Method and apparatus for gas turbine engine temperature management

A cooling system for a turbine engine, as well as a methodology for controlling the cooling system, is described. A valve member is disposed between a cooling fluid passage and a wheel space of the turbine engine and operates to admit cooling fluid to the wheel space for cooling thereof. The valve assembly is responsive to a condition in the wheel space and varies the flow of additional cooling fluid to the wheel space based on that condition.

A method of fabricating a turbine rotor is provided. The method includes fabricating a plurality of substantially cylindrical disks. Fabricating each disk includes fabricating a substantially cylindrical body and extending a bore substantially concentrically through the body. The method also includes coupling at least two of the plurality of disks together to form a rotor having a bore extending axially therethrough.

Methods and apparatus for fabricating a rotor for a steam turbine

A cooling system for a turbine with a first section and a second section. The first section may include a first line for diverting a first flow with a first temperature from the first section, a second line for diverting a second flow with a second temperature less than the first temperature from the first section, and a merged line for directing a merged flow of the first flow and the second flow to the second section.

Turbine systems and methods for using internal leakage flow for cooling

Disclosed herein is a rotor assembly for a steam turbine. The steam turbine includes a retention portion having a stacked rotor section. The steam turbine further includes a first shaft end disposed at a first end of the retention portion. The steam turbine yet further includes a second shaft end disposed at a second end of the retention portion that is opposite to the first end of the retention portion.

Stacked reaction steam turbine rotor assembly

Disclosed herein is a stator assembly for a steam turbine. The stator assembly includes a stacked stator section and a retention device. The stacked stator section has a plurality of adjacently disposed stator plates. The retention device retains the adjacent stator plates proximate to each other.

Stacked reaction steam turbine stator assembly

Disclosed herein is a rotor assembly for a steam turbine including a stacked rotor section having rotor plates. The rotor plates include a main body portion having a plate shape and a first axial face and a second axial face opposite to the first axial face. The rotor plates also include an airfoil base surface at an outer radial edge of the main body portion. The rotor plates further include buckets which extend radially outward from the airfoil base surface. And the rotor plates yet further include a seal disposed to prevent steam exposure to the first and second axial faces.

Axial and circumferential seal for stacked rotor and/or stator assembly

An apparatus for providing active clearance control between blade tips and seals in a turbomachine comprising: a first stator carrier segment, with stator seals centripetally disposed on it; a second stator carrier segment located along a same circumference as the first stator carrier segment, also with stator seals centripetally disposed on it; a shell that adjustably houses the first stator carrier segment and the second carrier segment; at least one displacement apparatus in operable communication with at least one stator carrier segment and configured to position the at least one stator carrier segment to provide active clearance control to the stator seals disposed on the at least one stator carrier segment.

Method and apparatus for turbomachine active clearance control

A method and apparatus for fabricating a rotor assembly for a turbine is provided. The method includes forming a cover on each bucket radial tip wherein the cover includes a leading edge side in a direction of rotation, and a trailing edge side in the direction of rotation wherein the leading edge and trailing edges are parallel with respect to each other, and wherein the leading edge and trailing edges are skewed with respect to the axis of rotation. The method includes forming an extension in the cover leading edge side, forming a groove in the cover trailing edge side, and attaching each bucket to the radially outer rim, such that the extension in the cover leading edge side of one cover is in mating engagement with the groove in the cover trailing edge side of an adjoining cover.

Methods and apparatus for integral radial leakage seal

A gas turbine rotor steam gland includes a steam inlet supply scroll for supplying steam through radial slots to an axially extending passage in the rotor for steam cooling of hot gas path component parts. The scroll decreases in diameter in the circumferential direction of cooling medium flow to match its velocity with the surface speed of the rotor. An aft labyrinth seal is provided about the rotor. Forwardly of the scroll, a plurality of labyrinth-type seals are interspersed with extraction ports. The extraction ports, except for the final forwardmost extraction port, are maintained at a pressure below the pressure of the inlet supply steam whereby steam leakage past the seals flows into the extraction ports for removal. The final forward extraction port is maintained at sub-ambient pressure such that final steam leakage past the forward seals and ambient air leakage past the forwardmost seal combine and are extracted from the steam gland.

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Schenectady, NY, United States of America

Clement Gazzillo