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: A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.

Abstract: A fuel injector device includes a body having a leading edge and a trailing edge and defining a streamwise direction from the leading edge to the trailing edge. The fuel injector device body includes a first surface and a second surface opposite the first surface, each surface extending between and including the leading edge and the trailing edge, and the surfaces conjoining each other at the leading edge and the trailing edge. The trailing edge, when seen in the streamwise direction, undulates along a trailing edge mean line and, along its extent, deviates in opposite directions from the mean line and includes at least one inflection point along its extent.

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 method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

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: A component is disclosed, the component comprising a first material and a second material, wherein a second member made from the second material is embraced by a first member made from the first material. Further, a method is disclosed for manufacturing said component, the method comprising applying an additive manufacturing process, building up a first member from a first material by the additive manufacturing process, and adding a second member made from a second material during the additive manufacturing process and adding further first material to the first member thus embracing the second member.

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: 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.

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: an impingement sleeve and a wall exposed to a hot gas during operation, wherein the impingement sleeve is at least partly disposed in a plenum, and spaced at a distance from the wall to form a cooling flow path between the wall and the impingement sleeve such that compressed gas injected from the plenum through apertures in the cooling sleeve during operation impinges on the wall and flows as a cross flow towards an exit at a downstream end of the cooling flow path. Plural turbulators have a leading edge arranged on the wall. A center of at least one of the apertures is aligned along the longitudinal axis with the leading edge of at least one of a turbulators.

Abstract: Disclosed is an aerodynamically shaped body for use in a hot fluid flow. The body extends along a camber line from a leading edge to a trailing edge and includes at least one coolant supply plenum provided inside the body, wherein the coolant supply plenum is delimited by a body wall. The body wall extends from a first side of the camber line to a second side of the camber line and extends over the leading edge, thereby providing a leading edge wall section. At least one first leading edge cooling duct extends from an inner surface to an outer surface of the wall and is in fluid communication with the coolant supply plenum through an inlet opening and opens out onto the outer surface through a discharge opening.

Abstract: A fuel injector device includes a body having a leading edge and a trailing edge and defining a streamwise direction from the leading edge to the trailing edge. The fuel injector device body includes a first surface and a second surface opposite the first surface, each surface extending between and including the leading edge and the trailing edge, and the surfaces conjoining each other at the leading edge and the trailing edge. The trailing edge, when seen in the streamwise direction, undulates along a trailing edge mean line and, along its extent, deviates in opposite directions from the mean line and includes at least one inflection point along its extent.

Abstract: A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.

Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.

Abstract: A method for manufacturing an element by an additive manufacturing process is disclosed. The method comprises manufacturing the element such as to comprise a front face extending from the base side and into the buildup direction. The method further comprises manufacturing at least one bump structure on said front face by means of the additive manufacturing process, wherein a delimitation of said bump structure comprises at least one reclining ledge and at least one overhang ledge. The overhang ledges are manufactured such as to form an angle with the buildup direction being smaller than or equal to 70 degrees. Further, elements producible by the method are disclosed.

Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.