Alstom Technology Limited

General Electric Company

Abb Research Ltd.

General Electric Technology Gmbh

Fulvio Magni

Ewald Freitag

Frank Grimm

Simone Roberto Walter Camponovo

Dariusz Nowak

Bruno Schuermans

Madhavan Narasimhan Poyyapakkam

Douglas Pennell

Andre Theuer

Klaus D&ouml;bbeling

John Philip Wood

Weiqun Geng

Vladimir Vassiliev

Martin Andrea Von Planta

Gerhard M&uuml;ller

Victor Vladimirovich Odinokov

Rohit Madhukar Kulkarni

Martin Zajadatz

Mischa Schaerer

Tomasz Dobski

Rafal Slefarski

Nadir Ince

Adrian Schneider

Geoffrey Engelbrecht

Sergey Anatolievich Chernyshev

Douglas Anthony Pennell

Rohit Kulkarni

The present application provides a variable frequency Helmholtz damper system for use with a combustor of a gas turbine engine. The variable frequency Helmholtz damper system may include one or more Helmholtz dampers and a purge medium temperature control unit for providing a flow of purge medium to the Helmholtz dampers. The purge medium temperature control unit may be in communication with a temperature control fluid flow such that the purge medium temperature control unit may vary the temperature of the flow of purge medium.

Variable frequency Helmholtz dampers

A burner for a combustor includes (a) a swirl generator enclosing a burner interior on an inlet side and including a tangential air inlet relative to a longitudinal center axis; (b) a mixing chamber enclosing the burner interior on an outlet side and defining a burner outlet fluidly connecting the burner interior with a combustion chamber; and (c) a lance arranged coaxially with the longitudinal center axis. The lance introduces fuel through a nozzle tip at or near the burner outlet into the combustion chamber. The nozzle tip includes a cartridge defining a center fuel passage; fuel swirl vanes within the center fuel passage at an outlet end of the nozzle tip; a first tube surrounding the center fuel passage and defining a first fluid passage; a second tube surrounding the first tube and defining a second fluid passage; and air swirl vanes in the second fluid passage.

Pilot nozzle tips for extended lance of combustor burner

A burner for a combustor of a turbomachine includes a pilot nozzle with inline premixing. The pilot nozzle is formed in an aft end of the burner. An air inlet is formed in a forward end of the burner in fluid communication with the pilot nozzle. A mixing channel extends along the axial direction between the air inlet and the pilot nozzle such that the air inlet is in fluid communication with the pilot nozzle via the mixing channel. An annular fuel plenum extends along the circumferential direction. A fuel port is in fluid communication with the annular fuel plenum and the mixing channel, the fuel port includes an outlet configured to inject fuel into the mixing channel such that a shear flow is induced.

Pilot nozzle with inline premixing

A seal arrangement for a silo combustor includes a first casing and a second casing each forming a passageway for a gas, an end portion of the first casing being disposed radially inside an end portion of the second casing such that the first and the second casing form an overlapping region having a radial gap. A segmented seal has at least two adjacent segments disposed in the overlapping region so as to seal the radial gap, wherein the first casing includes at least one opening disposed in a region between the at least two adjacent segments.

Seal arrangement

A premix burner is provided for a gas turbine, in the form of a double-cone burner, which has two partial cone shells which are arranged nested one inside the other, forming air inlet ducts between them, through which combustion air from the outside flows into a conical inner space of the premix burner. Linear rows of holes of injection openings, which extend transversely to the flow direction of the combustion air, are arranged on the outer walls of the air inlet ducts and through which a gaseous fuel is injected into the combustion air which flows past transversely to them. A method for reworking such premix burners is also provided.

Premix burner for a gas turbine

A Helmholtz damper for a combustor of a gas turbine includes first and second damping volumes. The combustor has a combustion chamber disposed in a housing and closed off by a front plate at which a plurality of burners are exchangeably fastened. The burners are supplied with fuel via fuel lances which extend from outside the housing through a bushing of the housing to the associated burner. The first damping volume has a first end and a second end, the first end of the first damping volume being configured to attach a connecting passage extending to a front panel such that the Helmholtz damper is connectable with the front plate of the combustion chamber in place of one of the burners. The second damping volume has a first end and a second end and is arranged in series with the first damping volume along an axis of the Helmholtz damper with the first end of the second damping volume being detachably connected to the second end of the first damping volume so as to form a combined larger damping volume. The second end of the second damping volume is configured to attach a connecting tube extending from the second damping volume and through the bushing in place of a respective one of the fuel lances.

Helmholtz damper for a combustor of a gas turbine and a method for installing the helmholtz damper

An injection nozzle (), especially for injecting liquid fuel, preferably crude oil, into the combustion chamber of a gas turbine, includes an inner chamber () which extends along a nozzle axis (), conically tapers to a concentric nozzle orifice (), and to which the medium which is to be injected is fed from outside through a plurality of inlet ports () which are arranged in a distributed manner around the nozzle axis (). The inlet ports () are oriented perpendicularly to the nozzle axis () and each lead tangentially into the inner chamber (). With such an injection nozzle, an improved spray cone is achieved by the fact that a pin (), which extends in the axial direction, is concentrically arranged in the inner chamber () and passes through the region of the mouths of the inlet ports () and extends right into the nozzle orifice ().

Injection nozzle having constant diameter pin and method for operating the injection nozzle

A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combustion chamber, has a combustion chamber wall edge which freely terminates in the axial flow direction of the hot gases. The combustion chamber wall edge is formed with a profile which blocks or at least inhibits a diffuser effect when a cooling air flow, which is guided axially through the flow passages into the annular spatial area, flows over the combustion chamber wall edge.

Combustion chamber arrangement for operating a gas turbine

In a method for reliably removing liquid fuel from the fuel system of a gas turbine after shutting down the same, in the case of which fuel system liquid fuel is fed via at least a first feeder line in normal operation of the gas turbine to a burner and injected there into a combustion chamber via fuel nozzles, a high reliability against explosion and coking is achieved in a simple way by virtue of the fact that the liquid fuel is flushed from the fuel system by the use of an inert auxiliary medium.

Method for reliably removing liquid fuel from the fuel system of a gas turbine, and a device for carrying out the method

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Nussbaumen, Switzerland

Fulvio Magni