Alstom Technology Limited

Asea Brown Boveri Ag

8 Rivers Capital, LLC

Siemens Energy, Inc.

Alstom (switzerland) Ltd

Abb Management Ag

Stefan Tschirren

Jaan Hellat

Frank Reiss

Peter Graf

Helmar Wunderle

Jeremy Eron Fetvedt

Xijia Lu

Christian Steinbach

Brent Gregory

James E Lenertz

Daniel Burri

Andreas Abdon

Chris Bonilha

Hassan Abdulsater

Ching-Pang Lee

Christian Oliver Paschereit

Rolf Dittmann

Peter Stuber

Pirmin Schiessel

Ryan Sadao Yamane

Gerhard M&uuml;ller

Eric C Berrong

Leonard J Meyer

Akash Bhatia

Ola Claesson

Werner Kessler

Wilfried Strittmatter

The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.

System and method for combustion of non-gaseous fuels and derivatives thereof

A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.

Ring segment with forked cooling passages

A combustion chamber of a combustion system has a combustion space, a support structure, a support element, and a heat shield. The heat shield has at least two segments, and each segment includes a liner element facing the combustion space and has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The retaining device fixes the respective liner element on the support structure via the support element and forms a flange region that fits over the edge region of the respective liner element. The retaining device forms a first cooling passage with the support element and has at least one through-opening in the flange region. A cooling gas flows through the through.opening from the first cooling passage to the edge region.

Combustion chamber of a combustion system

A combustion chamber of a combustion system comprises a combustion space, a support structure, a heat shield, and at least one through-opening. The heat shield has at least two segments, and each segment has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The adjacent segments include a support element disposed in a bottom region of the gap. The retaining device fixes the respective liner element on the support structure via the respective support element. The at least one through-opening communicates with the gap so as to enable a cooling gas to flow through the through-opening. The at least one through-opening is disposed in at least one of the respective edge region and the support element at the bottom region of the gap.

The invention relates to an annular combustor () for a gas turbine (), into which combustor () burners () open on an inlet side, and which combustor () extends in the axial direction from the inlet side to an outlet side () and is lined on the insides with cooled liner segments () for protection from the hot gases. In such a combustor, increased mechanical stability and flexibility in design and also simplification in manufacture and fitting are achieved by the liner segments () being subdivided in the axial direction into a plurality of parts () arranged one behind the other.

Annular combustor for a gas turbine

At least one Helmholtz damper is arranged at a combustion chamber for a gas turbine in order to damp thermoacoustic oscillations; the damping volume of this Helmholtz damper is in communication with the combustion chamber via a connecting passage. Optimum damping is achieved in a simple way by virtue of the Helmholtz damper being designed in such a manner that its damping frequency is adjustable.

Combustion chamber for a gas turbine

A gas turbo group has a combustion chamber comprising a catalytic burner stage (), a preburner stage () located upstream from the catalytic burner stage, as well as a non-catalytic burner stage () located downstream from the catalytic burner stage. The preburner stage serves to always maintain a temperature (T) at the inlet into the catalytic stage that corresponds at least to a minimum temperature (T) necessary for operating the catalytic burner stage. According to the invention, the gas turbo group is operated so that the burner stage located downstream from the catalytic combustion chamber is taken into operation only when the temperature (T) at the outlet from the catalytic stage has reached an upper limit in the presence of a maximum combustion air mass flow.

Method for operating a gas turbo group

In a burner arrangement for the annular combustion chamber of a gas turbine, a plurality of burners are arranged above one another, in each case in pairs in the radial direction, on concentric rings. In a burner arrangement of this type, the mechanical integrity of the turbine casing is increased and operation of the combustion chamber is optimized by virtue of the two burners in a pair of burners being oriented out of the parallel position, in such a manner that their burner axes converge in the direction of flow.

Burner arrangement for the annular combustion chamber of a gas turbine

Damper arrangement for reducing combustion-chamber pulsations

In a method of operating a gas turbine, in which a gaseous fuel is burned in a combustion chamber and the hot combustion gases which are produced in the process are directed through the gas turbine, and in which method the gaseous fuel is fed to the combustion chamber via a plurality of controllable burners, working in parallel and arranged on one or more concentric, essentially circular rings, and is sprayed into the combustion chamber via fuel holes, high safety and availability within various operating ranges is achieved in a simple manner owing to the fact that the burners are divided into at least two groups ( ) of burners, these groups in each case include the burners of one of the rings, and these groups are individually activated as a function of the operating state of the gas turbine.

Method of operating a gas-turbine chamber with gaseous fuel

In a gas turbine (,) with a plurality of individual burners (B,, . . . , B,; Bn) which are connected to a fuel distribution system (,) and are supplied with fuel from a common fuel feed (,) via the fuel distribution system (,), there being provided, within the fuel distribution system (,), means by which the fuel mass flows to the individual burners (B,, . . . , B,; Bn) can be varied in order to improve the operating parameters of the gas turbine (,), an improvement in the operating parameters is achieved in a simple way in that a fixed throttle member, determining the fuel mass flow to at least one of the burners (B,, . . . , B,; Bn), is arranged in the fuel distribution system (,) upstream of the at least one burner, and in that the reduction in cross section of the throttle member is selected in such a way that existing inequalities in the fuel distribution system (,) as regards the fuel mass flows to the individual burners (B,, . . . , B,; Bn) are reduced.

Gas turbine with a plurality of burners and a fuel distribution system, and a method for balancing a fuel distribution system

In a method for cooling a thermally loaded component (1) with a plate-type outer wall (2), in which method cooling air is supplied, in a first cooling section (A) of the component (1), through a cooling air supply (5) in the direction towards the outer wall (2) and is deflected laterally before the outer wall (2) and in a second cooling section (B) is further guided parallel to the outer wall (2) in a laterally adjoining cooling air duct (3) for the purpose of further cooling, homogenization of the cooling is achieved wherein, in order to reduce the impingement cooling in the first cooling section (A), the cooling airflow coming from the cooling airsupply (5) is subdivided into a main flow and a by-pass flow, the main flow is guided directly along the outer wall (2) of the component (1) to the cooling air duct (3), the by-pass flow is guided to the cooling air duct (3) without contacting the outer wall (2) and both partial flows are recombined at the inlet to the cooling air duct (3).

Method for cooling a component and appliance for carrying out the method

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Nunningen, Switzerland

Stefan Tschirren