Abstract: The can combustion chamber includes a casing housing a plurality of cans. Each can includes a wall and a perforated cooling liner around the wall. Cooling liners of adjacent cans have staggered perforations.

Abstract: The invention relates to a transition piece assembly for a gas turbine. A transition piece having one end adapted for connection to a gas combustor and an opposite end adapted for connection to a first turbine stage. The transition piece having at least one external liner and at least one internal liner. The internal liner forms the hot gas flow channel. A first section of the transition piece assembly upstream of a first turbine stage has a plurality of cooling apertures. Cooling medium through the cooling apertures enters the plenum, which is created between external and internal liners and a cooling medium flows along at least the first section of the transition piece assembly. At least one second section upstream of the first section with respect to the hot gas flow has at least one additional air inlet system.

Abstract: An impingement cooled wall arrangement includes a flow diverter arranged in the cooling flow path between the cooled wall and a sleeve to divert a cross flow away from a second aperture. The flow diverter extends in downstream direction of the cross flow beyond the second aperture with a first leg extending along one side of the second aperture in downstream direction of the cross flow and a second leg extending along the other side of the second aperture. No impingement cooling aperture is arranged in a first convective cooling section of the wall between the upstream end and downstream end of the flow diverter outside the section shielded by the diverter.

Abstract: The invention refers to a combustion chamber having a sleeve section which is at least partly enclosing a duct wall for guiding a cooling gas in a channel between the sleeve section and the duct wall along the outer surface of the duct wall. The sleeve section has one main inlet opening facing away from the duct wall wherein the cross sectional area of the main inlet opening is larger than 70% of the sum of the cross sections of all cooling openings to the sleeve section. The disclosure further refers to a gas turbine comprising such combustion chamber.

Abstract: The present disclosure refers to an impingement cooling arrangement for cooling a duct wall of a duct guiding a hot gas flow. The impingement cooling arrangement includes an impingement sleeve which is at least partly disposed in a compressed air plenum, and spaced at a distance to the duct wall to form a cooling flow path between the duct wall and the impingement sleeve such that cooling air injected from the compressed air plenum through apertures in the sleeve impinges on the duct wall. At least one flow diverter is arranged in the cooling flow path to divert the cross flow away from at least one aperture. Besides the impingement cooling arrangement a gas turbine with such an arrangement as well as a method for cooling a duct wall are provided.

Abstract: The invention refers to a transition piece of a combustor of a gas turbine including an impingement cooling zone, a sequential disposed liner having at least one cooling arrangement and a closing plate with respect to the sequential disposed liner. The sequential disposed liner has a cooling channel structure. The cooling channel structure forms a closed loop cooling scheme or a quasi-closed loop cooling scheme. The cooling channel structure is operatively connected to a cooling medium to cool at least one part of the sequential disposed liner.

Abstract: A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed.

Abstract: A gas turbine combustor part of a gas turbine includes a wall, containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction. The near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air. The inlets open into a common feeding channel for cooling air supply, and the outlets open into a common discharge channel for cooling air discharge. The feeding channel and the discharge channel extend in the second direction.