General Electric Company

Other

David Orus Fitts

Robert James Bracken

Ronald Wayne Korzun

John Thomas Murphy

Stephen Roger Swan

Guy Wayne DeLeonardo

William Theodore Bechtel

Jeffrey Robert Simkins

William Edward Adis

Bernard Arthur Couture, Jr

Warren James Mick

Clement Gazzillo

Mark William Kowalczyk

Laurence Scott Duclos

Michael B Sciocchetti

Neil S Rasmussen

John S Haydon

Christopher Walter Sullivan

Sterling Hathaway

Lewis Berkley Davis, Jr

David Robert Schumacher

Douglas Marti Fortuna

Daniel Mark Brown

William C Lippmeier

Stephen Hugh Black

Richard E Stenger

Mitchell R Cohen

James David Schuhl

Gregory Lee Landry

David Bruce Knorr

Anand Aravindrao Kulkarni

Keith A Williams

Malachi Lawrence, Jr

Joseph S Alford

L Berkley Davis, Jr

Larry Duclos

Ron W Korzun

A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.

Methods and systems for securing turbine nozzles

A rotary machine includes a rotor, a stationary machine casing extending around the rotor, and a bling assembly extending between the casing and the rotor. The machine also includes at least one rotor tip seal assembly and at least one shaft seal assembly. The seal assemblies have a groove configured to receive at least one seal ring band. A method of assembling a rotary machine is also provided. The method includes fabricating the bling assembly by providing two identical members comprising a mating surface and having a semi-circular profile. The method also includes coupling the two members together at their mating surfaces such that a circular ring is formed and such that the mating surfaces define a horizontal joint. The method further includes machining concentric, circular and annular radially inner and outer and airfoil portions within predetermined radial portions of the bling assembly. The method also includes forming at least one abradable layer over a plurality of seal ring bands and inserting the plurality of seal ring bands into the rotor tip and shaft seal ring grooves.

Rotary machines and methods of assembling

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

The turbine includes a diaphragm having a seal carrier mounted in opposition to seal teeth carried by the rotary component. The seal carrier includes a seal face having a coating of abradable material enabling the rotary component to abrade the material from the seal face. The seal carrier is removable from the diaphragm and is carried by an axial extension integral with or removable from the outer diaphragm ring. A spring may be interposed between the seal carrier and the stationary component.

Removable abradable seal carriers for sealing between rotary and stationary turbine components

The steampath for a steam turbine includes stacked stator rings each mounting inwardly directed nozzles and stacked rotor wheels each mounting outwardly directed buckets mounting blades. By alternately stacking the stator rings and rotor wheels, the nozzles and buckets of the various stages are interdigitated to form a steampath. Each bucket includes a blade and a root received in a generally complementary shaped groove on a wheel.

Stacked steampath and grooved bucket wheels for steam turbines

A wedge-like nozzle radial loading pin, preferably formed from steel, that contacts the bottom of a reaction nozzle along a graduated, that is inclined or stepped, surface. This contact will secure the reaction nozzle radially inward against the retaining surface of the carrier dovetail with sufficient force to maintain the designed airfoil pre-twist.

Method of installing stationary blades of a turbine and turbine structure having a radial loading pin

A loading spring segment for radially loading a turbine bucket within a turbine rotor groove includes a substantially circular metal sheet with a gap between opposed edges of the sheet, the sheet defining an arcuate segment in an arcuate length direction of the spring segment; and a plurality of radial slots in the sheet, spaced along the arcuate length direction to thereby create a plurality of individual springs within the arcuate segment.

Continual radial loading device for steam turbine reaction type buckets and related method

Nozzles for a turbine have dovetail-shaped bases for reception in corresponding dovetail-shaped grooves in the carrier halves of a turbine. The nozzles at each of the horizontal joint faces of each carrier half have notches formed along their bases including an abutment face. Key slots are formed in the horizontal joint faces and receive keys bearing against the abutment faces. The keys are peened or screwed into the carrier half at the horizontal joint faces. Radial loading pins engage the end nozzle bases to bias the end nozzles radially inwardly without interfering with the keys retaining the nozzles in the grooves.

Turbine nozzle retention apparatus at the carrier horizontal joint face

A combustor for a turbine includes a combustor liner; a first flow sleeve surrounding the liner, the flow sleeve having a plurality of rows of cooling holes formed about a circumference of the flow sleeve; and a transition piece connected to the combustor liner and the flow sleeve and adapted to carry hot combustion gases to a stage of the turbines. The transition piece is surrounded by a second flow sleeve which directs cooling air to the transition piece. One of the plurality of rows of cooling holes in the first flow sleeve is located adjacent the transition piece, and cooling conduits are mounted in the cooling holes of at least the first of the plurality of rows of cooling holes to direct impingement cooling air against the surface of the liner while diverting crossflow cooling air around the impingement cooling air. A related method of cooling a combustor liner of a gas turbine combustor with a flow sleeve surrounding the liner in substantially concentric relationship therewith includes the steps of a) providing a plurality of axially spaced rows of cooling holes in the flow sleeve, each row extending circumferentially of the flow sleeve, a first of the rows adjacent a forward or downstream end of the flow sleeve; b) locating a plurality of cooling conduits in the cooling holes of at least the first of the rows, the cooling conduits extending radially towards, but not engaging, the liner; and c) supplying cooling air to the annulus such that the cooling conduits direct the cooling air against the liner.

Combustor liner cooling thimbles and related method

A diffusion flame nozzle gas tip is provided to convert a dual fuel nozzle to a gas only nozzle. The nozzle tip diverts compressor discharge air from the passage feeding the diffusion nozzle air swirl vanes to a region vacated by removal of the dual fuel components, so that the diverted compressor discharge air can flow to and through effusion holes in the end cap plate of the nozzle tip. In a preferred embodiment, the nozzle gas tip defines a cavity for receiving the compressor discharge air from a peripheral passage of the nozzle for flow through the effusion openings defined in the end cap plate.

Gas only nozzle

A diffusion flame nozzle gas tip is provided to convert a dual fuel nozzle to a gas only nozzle. The nozle tip diverts compressor discharge air from the passage feeding the diffusion nozzle air swirl vanes to a region vacated by removal of the dual fuel components, so that the diverted compressor discharge air can flow to and through effusion holes in the end cap plate of the nozzle tip. In a preferred embodiment, the nozzle gas tip defines a cavity for receiving the compressor discharge air from a peripheral passage of the nozzle for flow through the effusion openings defined in the end cap plate.

Method of cooling gas only nozzle fuel tip

Gas only nozzle fuel tip

A fuel nozzle for a gas turbine includes a nozzle body having a tip portion, the nozzle body including an inner tube defining an axially extending air passage; an intermediate tube concentrically arranged and radially spaced from the inner tube and defining a diffusion fuel passage therebetween; and an outer tube concentrically arranged and radially spaced from the intermediate tube and defining a premix fuel passage therebetween. The outer tube has a plurality of radially extending injectors in communication with the premix fuel passage. The premix fuel passage is further defined in part by an outer tube wall portion formed with at least one weakened region adapted to burn through in the event of a flashback, thereby causing a substantial portion of premix fuel to bypass the injectors and to exit the nozzle body at the at least one weakened region. A related method is also disclosed.

Diffusion-premix nozzle for a gas turbine combustor and related method

A method of operating a combustor for a turbine includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and a premixed mode of operation, during the transition and during the premixed mode of operation. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise while achieving low emission operation in the premixed mode.

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Ballston Spa, NY, United States of America

David Orus Fitts