Abstract: A combustion chamber of a gas turbine, wherein downstream of the combustion chamber an expansion turbine with a turbine inlet is arranged. The combustion chamber has an annular design with a component, which has a chamber wall and an end wall arranged next to the turbine inlet and a corner as connection of the chamber wall and the end wall. To increase the cooling performance the component further has an air guidance piece arranged at a distance from the chamber wall with a cooling channel in-between. Further, the corner is fluid tight, wherein the distance of the air guidance piece to the end wall is at least 0.5-times and at most 2-times the lowest width of the cooling channel.

Abstract: A combustor arrangement, the combustor arrangement being annular and being arranged about an axis, the axis defining an axial direction, having an annular housing to house a plurality of burners and an annular combustion chamber, the burners arranged circumferentially about the axis inside the annular housing, wherein an annular space is defined between the housing, the burners and the annular combustion chamber, the annular space arranged to guide a compressed fluid. A plurality of stiffening plates, each arranged within the annular housing, wherein two adjacent ones of the burners are separated by one of the stiffening plates. A combustor separating wall arrangement separates the annular space from the annular combustion chamber provides openings for the burners. The stiffening plates are arranged angled and connected to the combustor separating wall arrangement and two boundary walls of the housing, and further plates extend into the annular space.

Abstract: A turbomachine component, gas turbine combustor component, or burner component, including a body with a first, second and third section, the sections being integrally formed with another and built from a same material, and an end face of the first section of the body. The end face, during operation, is exposed to a first temperature higher than a second temperature of a cooling fluid. The second section is located between the first and third section and is formed in parts as a lattice structure. The lattice structure has a plurality of rod-shaped struts, wherein each of a first set of the plurality of struts has a first end, the first end being connected to the first section, and a void penetrated by the plurality of struts, the void providing at least one fluid passage via which the cooling fluid is guidable through an interior of the second section during operation.

Abstract: A rotating machine component, particularly a gas turbine combustion component, having at least one part built from a porous material with a plurality of pores, wherein at least a subset of the plurality of pores is at least partly filled with a gas with a composition different from air and/or with a powder, wherein the porous material is a laser sintered or laser melted material in which void local regions form the plurality of pores. The component counter-acts vibrations. A rotating machine or gas turbine engine may have such a component.

Abstract: A combustor arrangement, the combustor arrangement being annular and being arranged about an axis, the axis defining an axial direction, having an annular housing to house a plurality of burners and an annular combustion chamber, the burners arranged circumferentially about the axis inside the annular housing, wherein an annular space is defined between the housing, the burners and the annular combustion chamber, the annular space arranged to guide a compressed fluid. A plurality of stiffening plates, each arranged within the annular housing, wherein two adjacent ones of the burners are separated by one of the stiffening plates. A combustor separating wall arrangement separates the annular space from the annular combustion chamber provides openings for the burners. The stiffening plates are arranged angled and connected to the combustor separating wall arrangement and two boundary walls of the housing, and further plates extend into the annular space.

Abstract: A turbomachine component, gas turbine combustor component, or burner component, including a body with a first, second and third section, the sections being integrally formed with another and built from a same material, and an end face of the first section of the body. The end face, during operation, is exposed to a first temperature higher than a second temperature of a cooling fluid. The second section is located between the first and third section and is formed in parts as a lattice structure. The lattice structure has a plurality of rod-shaped struts, wherein each of a first set of the plurality of struts has a first end, the first end being connected to the first section, and a void penetrated by the plurality of struts, the void providing at least one fluid passage via which the cooling fluid is guidable through an interior of the second section during operation.

Abstract: A rotating machine component, particularly a gas turbine combustion component, having at least one part built from a porous material with a plurality of pores, wherein at least a subset of the plurality of pores is at least partly filled with a gas with a composition different from air and/or with a powder, wherein the porous material is a laser sintered or laser melted material in which void local regions form the plurality of pores. The component counter-acts vibrations. A rotating machine or gas turbine engine may have such a component.

Abstract: A turbomachine component, particularly a gas turbine engine component, has at least one part built in parts from a curved or planar panel, particularly a sheet metal, the part having a plurality of cooling channels via which a cooling fluid, particularly air, is guidable, wherein at least one of the plurality of cooling channels has a continuously tapered section. The at least one of the plurality of cooling channels has a single inlet port from a first surface of the panel and a single outlet port for the cooling fluid to another surface, particularly a surface opposite to the first surface, or to the first surface. Further the panel is built via laser sintering or laser melting or direct laser deposition. A gas turbine engine is equipped with such a component. A method of manufacturing includes incorporating cooling channels having a continuously tapered section.