Siemens Westinghouse Power Corporation

Westinghouse Electric Corporation

Siemens Energy, Inc.

Siemens Power Generation, Inc.

Other

David Marchant Parker

Rajeev Ohri

John C Groenendaal

William Richard Ryan

Weidong Cai

Stephen E Mumford

Arthur J Harris, Jr

Kristian I Wetzl

David J Amos

Daniel W Garan

David T Foss

Graydon Lane Whidden

Joseph Scott Markovitz

Susan M Parker

Walter Halberg

John A Moreci

George W Chang

Herbert C Reid

Wendel Zolyomi

Plum Boonsuan

Perry E Lowe

Margery Norcom Hilburn

A combustor liner () for a gas turbine engine combustor () comprises an inner wall (), an outer wall (), a cooling air flow channel () formed there between, and a flow control ring (). The flow control ring () is sealingly attached to the downstream ends of the inner wall () and the outer wall (), and comprises a plurality of holes () that, during gas turbine engine operation, may regulate a flow of cooling air that passes through the cooling air flow channel (). One or more surfaces may be coated with a thermal barrier coating () to provide additional protection from thermal damage.

Combustor liner for gas turbine engine

A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components.

Thermal shield at casing joint

A combustor liner () for a gas turbine engine combustor () comprises an inner wall (), an outer wall (), a flow channel () formed there between, and an end-capping ring (). The end-capping ring () is sealingly attached to the downstream end of the inner wall (). In operation air passes within the end-capping ring (), into the flow channel (), and through holes () disposed in the inner wall (). In some embodiments, an end-capping ring variation, a flow-diverting ring () comprises a plurality of holes () that, during gas turbine engine operation, may additionally dispense a flow of cooling air. One or more surfaces may be coated with a thermal barrier coating () to provide additional protection from thermal damage.

Combustor liner with reverse flow for gas turbine engine

A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas. The system delivers a secondary fuel/diluent mixture to a secondary combustion zone located along the length of the transition piece, while reducing the impact of elevated vibration levels found within the transition piece and avoiding the heat dissipation difficulties often associated with traditional vibration reduction methods.

Secondary fuel delivery system

Aspects of the invention relate to a system for attaching a fuel swirler assembly in a turbine engine combustor. According to embodiments of the invention, at least an axial upstream end of the fuel swirler assembly can be attached to a combustor support frame using one or more fasteners, such as bolts. The fuel swirler assembly can include a radial bracket provided on the swirler body to facilitate attachment. The axial downstream end of the fuel swirler assembly can be positioned within an opening defined in a swirler base plate or within an opening in a swirler support plate. Aspects of the invention can reduce the time and cost associated with installation and replacement of fuel swirlers in a combustor while avoiding concerns associated with known welded pin attachment systems.

Turbine engine combustor with bolted swirlers

A fuel/air mixing apparatus, such as a main swirler assembly () comprising a sleeve (), provides for additional air entry around the perimeter of a bore () through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (). In some embodiments, a plurality of gaps () exists between spaced apart tabs () along a downstream end () of the sleeve (). During gas turbine operation, air flows through both a flashback annulus () and the gaps (). In other embodiments, a plurality of holes are placed upstream and in line with the tabs () to supplement the air flow through gaps (). In yet other embodiments, rows () of holes () are provided to supplement the airflow. Downstream ends () may interface with a downstream-oriented lip () or with an upstream-oriented lip (). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.

Swirler assembly and combinations of same in gas turbine engine combustors

An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may include a cooling channel proximate to a point of attachment to the combustor basket.

Turbine spring clip seal

A barrier structure () blocks exit of spring clip fragments () that may break off from a spring clip assembly disposed between a gas turbine engine combustor () and a transition piece component (). The barrier structure () may additionally comprise an aspect () effective to restrict a spring clip's () radially inward compression, thereby reducing or eliminating damage to the spring clip () during shipping and handling. The barrier structure () additionally may comprise an aspect () to restrict access by a human hand to the free ends () of the spring clips (). This aspect () reduces or eliminates the undesired lifting of the compressor by grabbing the spring clips () during combustor transport, installation or removal. Accordingly, barrier structure embodiments are provided that reduce stress on spring clips, and that prevent the exit of spring clips from a containment space partly formed by the barrier structure.

Gas turbine combustor barrier structures for spring clips

A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.

Pilot nozzle heat shield having connected tangs

An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal is composed of inner and outer housings and a center sealing member disposed between the inner and outer housings. The center sealing member is flexible and prevents a fluid, such as air, from leaking through the seal. In operation, the center sealing member flexes and is sealed against the outer housing by a pressure differential that is created by the relatively higher pressure on the inner housing side and the relatively lower pressure on the outer housing side.

An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may include one or more tapered leaves forming a portion of the spring clip seal. At least one leaf may include a flared end for limiting gas from passing through the slots in the spring clip seal. In at least one embodiment, the turbine clip seal may include a center sealing member positioned between the inner and outer housings.

A gas turbine engine () having an active combustion control system () including a sensor element () positioned proximate the combustion chamber () as part of a sensor assembly () including a spring-action bellows (). The sensor assembly is installed through an opening () in the casing () of the engine to make contact with the combustor wall (). The bellows is compressed from its resting position by tightening mounting bolts () against a mounting flange () of the sensor assembly. The spring action of the bellows ensures contact between the sensing assembly and the combustor wall in spite of differential thermal growth between the casing and the combustor. The sensor element may be replaced by simply removing the mounting bolts without further disassembly of the engine.

Gas turbine with flexible combustion sensor connection

A turbo machinery assembly, having a natural frequency outside of the range of operational vibrational forces and further having increased damping capability, comprises a turbo machinery component and a plate having an elongated opening defining an inner surface. The turbo machinery component has a first end and a second end; the second end having an outer profile that extends inside the opening, contacting portions of the inner surface and extending peripherally to regions of clearance with the inner surface. The second end of the turbo machinery component may also extend beyond the inner surface. The turbo machinery component may further include a sleeve having a proximal end and a distal end. The second end of the turbo machinery component extends into the sleeve through the proximal end. The distal end of the sleeve defines the second end of the turbo machinery component extending inside the inner surface.

Swirler assembly with improved vibrational response

A support member for removably supporting a swirler on a basket frame of a combustion gas turbine engine includes a plug removably mounted on the basket frame and a pin fixedly mounted on the swirler. A mechanical lock detachably connects the plug and the pin with one another, and the mechanical lock may include cooperating threads or other appropriate structures. The swirler is removed from the basket frame by detaching the plug from the basket frame, disconnecting the plug from the pin, and sliding the swirler longitudinally along its own axis whereby the pin clears the mounting hole within which the plug was mounted.

Apparatus and method for replacement of combustor basket swirlers

A fuel filtering apparatus for use in a gas turbine fuel system is provided. The fuel filtering apparatus includes a removable filter housing which receives and maintains a filter element therein to filter a fuel flow when the filter housing is positioned on the apparatus. The fuel filtering apparatus is also provided with a casing which is installed in-line in a portion of the fuel system. The removable filter housing alleviates the need for removal of the casing when a filter element is inserted and removed for cleaning and other routine maintenance. The fuel filtering apparatus also reduces pressure disruption within the fuel system.

Growing community of inventors

Oviedo, FL, United States of America

David Marchant Parker