General Electric Company

Baker Hughes Corporation

General Electric Technology Gmbh

David Martin Johnson

Radu Ioan Danescu

Gary Martin Flood

Kenneth Damon Black

Iain Robertson Kellock

Sacheverel Quentin Eldrid

Albert Myers

Hans M Knuijt

Brendan F Sexton

Kyle E Coneybeer

Matthew Stephen Casavant

Bradley E Williams

Henry S Marek

Richard William Johnson

Bradley James Miller

Robert Joseph Iasillo

Friedel S Knemeyer

Christopher Paul Cox

Linda Jean Farral

Kevin Jon O'Dell

Gregory James Hampson

Howard Jay Kaplan

Erik O Einset

Mullahalli Venkataramaniah Srinivas

Rodney Jonathan Waters

Piotr Edward Kobek

Srinivasarao Pakkala

Christopher David Miller

Steven Patrick Junquera

Christopher Farral

Ozgur Bozkurt

David Francis Acquavella

Ronald Scott Bunker

Craig Hodges Cooley

Gregory Allen Boardman

Gilbert Otto Kraemer

Geoffrey David Myers

Frederic Joseph Klug

Ronald James Chila

Scott Robert Simmons

Donald Mark Bailey

Hasan Ul Karim

Scott Edmond Ellis

Byron Richard Collins

James Anthony West

Ian W Cunningham

Francis R Corrigan

Kenneth Edward Seitzer

Ibrahim Sezer

Joseph Vincent Citeno

Gregory Allan Crum

George Hanna Ghanime

Kenneth Neil Whaling

Nishant Govindbhai Parsania

John William Lucek

Bruce J Badding

John David Bibler

Arthur A Chaves

Stephen Robert Thomas

George Martin Gilchrist

Keith G Savas

Brett Darrick Klingler

Wolfgang Franz Dietrich Mohr

Donald Earl Floyd

Govindarajan Rengarajan

Mitchell Allan Merrill

John Clisby Blanton

William Andrew Parker

Ravi Shankar Venkata Kasibhotla

David M Schnell

Benjamin J Nash

Jason Ray Gregg

James Carlton Dudley

Kurt Rechsteiner

Eoin M O'Tighearnaigh

Gerald Wilson Grove

Mark David D'Ambruoso

Robert N Pittman

Stephen P Schrantz

Robert J Maffeo

Mir M Ali

Peter J R&ouml;hl

Julia A Wagener

Brett Darrick Klinger

Luther L White

Jon L Helgeland

Michael John Barno

Stephen Chiaco

Gregory Tempel

Kenneth Blank

Scott J Dennison

Kenneth D Black

Christopher William Kester

A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

Turbomachinery heat transfer system

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

A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.

Flow inducer for a gas turbine system

A system and method for active draft control through a combined cycle power plant (CCPP) can initiate a CCPP shutdown, activate the recirculated exhaust gas (REG) system for the turbomachine; measure a HRSG airflow through the HRSG; communicate the HRSG airflow to a controller configured to condition a control signal; and adjust a recirculated exhaust gas volume in accordance with the control signal.

Active draft control for combined cycle power plant shutdown

A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

Flow sleeve for thermal control of a double-walled turbine shell and related method

A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, an inner cavity disposed between the inner exhaust wall and an inner casing, and a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the inner cavity to the outer cavity.

Turbine exhaust section structures with internal flow passages

A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.

Helical seal system for a turbomachine

A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing.

Clearance control system for a rotary machine and method of controlling a clearance

Flow sleeve for thermal control of a double-wall turbine shell and related method

According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity.

Inducer guide vanes

A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.

System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines

Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.

Gas turbine thermal control and related method

A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.

Gas turbine casing thermal control device

A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.

Thermal isolation apparatus

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Simpsonville, SC, United States of America

David Martin Johnson