Alstom Technology Limited

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Nicolas Noiray

Bruno Schuermans

Andreas Huber

Mirko Ruben Bothien

Urs Benz

Diane Lauffer

Jaan Hellat

Michael Düsing

Felix Michael Reinert

Alexander Schnell

Hanspeter Zinn

Yang Yang

Ghislain Singla

Marta De La Cruz Garcia

Danda-Raj Pahari

Dejan Rajkovic

Adrian Glauser

Bruno Schürmans

The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes.

Simultaneous broadband damping at multiple locations in a combustion chamber

A fuel injection device for a gas turbine can include streamlined bodies arranged adjacent to one another in a circumferential direction. Each streamlined body can have a fuel nozzle on its trailing edge. The streamlined bodies can be split into at least a first group of streamlined bodies and a second group of streamlined bodies. All the streamlined bodies in the first group being the same and being different from the streamlined bodies in the second group. The first group of streamlined bodies includes at least two streamlined bodies adjacent to one another. Alternatively, the streamlined bodies are clustered in sets of two adjacent streamlined bodies. As yet another alternative, the streamlined bodies can be arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in the plane perpendicular to the central axis.

Fuel injection device for a gas turbine having streamlined bodies with lobe structure

The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.

Damper for gas turbine

Gas turbine damper with inner neck extending into separate cavities

A combustion device () for a gas turbine includes portions () having an inner and an outer wall () with an interposed noise absorption plate () having a plurality of holes (). The combustion device () further has first passages () connecting zones between the inner wall () and the plate () to the inside of the combustion device () and second passages () for cooling the inner wall (). The portions () also have an inner layer () between the inner wall () and the plate () defining inner chambers (), each connected to at least a first passage (), and an outer layer () between the outer wall () and the plate () defining outer chambers () connected to the inner chambers () via the holes () of the plate ().

Combustion device for a gas turbine

The invention relates to a damper for reducing the pulsations in a combustion chamber of a gas turbine. The damper includes a resonator cavity with an inlet and a neck tube in flow communication with the interior of the combustion chamber and resonator cavity, and a compensation assembly pivotably connected with the neck tube. The compensation assembly is inserted between the resonator cavity and the combustion chamber to permit relative rotation between the combustion chamber and the resonator cavity. With the damper according to the present invention, by way of providing the compensation assembly, it is assured the relative rotation between the combustion chamber and the resonator cavity is compensated, hence operation life is elongated.

Damper for gas turbines

A probe is provided for measuring high frequent pressure oscillations of hot gases that combines redundancy of the output signals with high quality of the output signals.

Probe for measuring pressure oscillations in the combustor of a gas turbine

Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations

A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages.

Combustion device with a layered wall structure for a gas turbine

A combustion device includes a plurality of mixing devices into which a fluid containing oxygen and a fuel are introduced and mixed to form a mixture. The combustion device also includes a combustion chamber in which the mixture formed in the mixing devices is burnt. Each mixing device has a conical body with a lance projecting into the conical body, where the fuel is injectable into the conical body. Tips of the lances of different mixing devices have different distances from corresponding open ends of the respective conical bodies.

Combustion device

A damper arrangement () has a first Helmholtz damper () connected in series to a second Helmholtz damper (). The resonance frequency of the first Helmholtz damper () and the resonance frequency of the second Helmholtz damper () are shifted from one another in an amount producing a synergic damping effect.

Damper arrangement and method for designing same

A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.

Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators

A Helmholtz damper, including an enclosure, a neck extending from the enclosure, and a pipe for inserting into the neck. The portions of the pipe inserted into the neck is adjusted to regulate a resonance frequency of the Helmholtz damper.

Growing community of inventors

Bern, Switzerland

Nicolas Noiray