Ansaldo Energia Switzerland Ag

General Electric Company

General Electric Technology Gmbh

Stobag Ag

Ansaldo Energia IP UK Limited

Jost Imfeld

Urs Benz

Bruno Schuermans

Mirko Ruben Bothien

Andre Theuer

Paul Marlow

Dariusz Oliwiusz Palys

Hans-Christian Mathews

Oliver Konradt

Naresh Aluri

Wilhelm Reiter

Jeffrey Alan De Jonge

Alen Markovic

Marcos Escudero-Olano

Roger Ernst

Igor Bizic

Laurent Fabien Laville

Raphael Flaig

Vedran Druzak

Giancarlo Ruggieri

Slawomir Swiatek

Fabian Hasler

Josua Furrer

Stefan Hippenmeyer

Joel Andermatt

The invention relates to a shading device comprising a cloth that can be spread out in a cloth plane and is connected to a lead bar that is slidably guided in guides. The guides run horizontally or at a slight inclination to a horizontal. A blocking device has a displaceable stop part which can be displaced between a stop position, in which it can be brought into contact with the lead bar, and a release position. The blocking device is arranged below the cloth plane and below the lead bar and has a displaceably mounted switching part which can be displaced by means of the lead bar, the switching movement of which switching part can be conveyed to the stop part by means of a transmission device in order to adjust said stop part between the stop position and the release position.

Shading device

Combustor device having a twin-shell tubular casing including: an inner tubular member which extends roughly coaxial a longitudinal axis of the combustor device, delimits the combustion chamber and surrounds the burner; and an outer tubular housing which extends roughly coaxial outside of the inner tubular member. An intermediate supporting structure includes an outer annular supporting member, an inner annular supporting member, and a series of three or more oblong connecting beams angularly staggered about the longitudinal axis of combustor device in cantilever manner to stably connect the inner and outer annular supporting members.

Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

An annular Helmholtz damper for a gas turbine can combustor, the annular Helmholtz damper having an axis; an inner wall and an outer wall concentrically arranged with respect to the axis to define an annular damping volume arranged around a can combustor; a front and rear circumferential plates for closing the annular damping volume upstream and downstream; at least one intermediate circumferential plate arranged between the front and the rear plates for dividing the annular damping volume in a main and a secondary volume; and a plurality of intermediate drain holes passing the intermediate circumferential plate and configured for draining collected liquid from the main volume to the secondary volume.

Annular Helmholtz damper for a gas turbine can combustor

A burner assembly of a gas turbine comprising: a tubular body defining the flow path for the hot gas of the combustion during the turbine operation; an aperture for a fuel lance; a wearing ring of a sacrificial material configured to correspond to the edge of the aperture; a contacting leg extending from the wearing ring on the tubular body; a pre-tension system configured to contact the contacting leg in order to provide a pre-tension force on the ring.

Burner assembly for a burner of a gas turbine

A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first and said second tubular members.

A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.

Sealing arrangement on combustor to turbine interface in a gas turbine

A sealing arrangement is provided at the interface between a combustor and a turbine of a gas turbine. The turbine includes guiding vanes at its inlet. The guiding vanes are each mounted within the turbine at their outer diameter by means of rear outer diameter vane hook and are each at their inner diameter in sealing engagement by means of a front inner diameter vane tooth with a honeycomb seal arranged at the corresponding inner diameter part of the outlet of said combustor. The rear outer diameter vane hook allows a relative movement of the guiding vane in form of a rotation around the rear outer diameter vane hook. The sealing adapts the front inner diameter vane tooth and the corresponding honeycomb seal in their configuration to the rotating relative movement of the guiding vane, such that the compression of said honeycomb seal through transients of the gas turbine is reduced.

Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement

A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor inner liner. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is greater than or equal to the axial dimension.

System and apparatus for gas turbine combustor inner cap and resonating tubes

A method of making a combustor cap assembly uses an additive manufacturing process of consecutively adding material in layers along an upstream axial build direction starting from a base side positioned transverse to the upstream axial build direction. The base side has at least one acoustic port. A bump side extends from the base side in the upstream axial build direction and has at least one damper projecting from the bump side. The damper has at least one inclined face forming an angle with the upstream axial build direction of less than or equal to 45 degrees. The resulting cap assembly includes a hot side with an acoustic port and a cold side with at least one damper with an inclined face and a damper chamber in communication with the acoustic port.

Method and apparatus for gas turbine combustor inner cap and high frequency acoustic dampers

A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one extended resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one extended resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is less than the axial dimension.

System and apparatus for gas turbine combustor inner cap and extended resonating tubes

The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing.

Device and method for mounting or dismantling, replacement and maintenance of a can-combustor

A centering arrangement includes a ring-like inner part and a ring-like outer part, whereby the outer part surrounds the inner part in a concentric arrangement and with an interspace established between the outer part and the inner part, and whereby the outer part and the inner part are subject to a differential radial expansion. A centering contact element, procures a centering mechanical contact between the outer part and the inner part at a plurality of circumferentially distributed contact points, and is able to deform in order to compensate for differential radial expansion.

Centering arrangement of two parts relative to each other

The present disclosure relates to gas turbines and to a damper assembly for a combustion chamber of a gas turbine. A damper assembly as disclosed herein may be adjusted to different frequencies during operation and/or deactivated for different operation regimes.

Growing community of inventors

Scherz, Switzerland

Jost Imfeld