Abstract: A cooled machine component having a body with at least one integrated cooling channel having a lattice structure for guiding a cooling fluid through an interior, the lattice structure arranged as a void space penetrated by a plurality of hollow or solid struts. The lattice structure has an inlet for providing the cooling fluid to be guided through the void space of the lattice structure, and has an outlet for receiving the cooling fluid, the outlet being fluidically connected to a hollow interior of at least one of the plurality of hollow struts. At least a subset of the hollow struts provides a fluidic connection for cooling fluid from the outlet to a plurality of further downstream discharge ports. Walls of the body surrounding each of the plurality of further downstream discharge ports are physically connected to corresponding jackets of the at least one of the plurality of hollow struts.

Abstract: A cooled machine component having a body with at least one integrated cooling channel having a lattice structure for guiding a cooling fluid through an interior, the lattice structure arranged as a void space penetrated by a plurality of hollow or solid struts. The lattice structure has an inlet for providing the cooling fluid to be guided through the void space of the lattice structure, and has an outlet for receiving the cooling fluid, the outlet being fluidically connected to a hollow interior of at least one of the plurality of hollow struts. At least a subset of the hollow struts provides a fluidic connection for cooling fluid from the outlet to a plurality of further downstream discharge ports. Walls of the body surrounding each of the plurality of further downstream discharge ports are physically connected to corresponding jackets of the at least one of the plurality of hollow struts.

Abstract: A burner of a turbomachine has an upstream burner section providing a first fuel and an oxygen containing fluid to an upstream end of a burner interior, a downstream burner section for providing a second fuel to a downstream end of the burner interior, and an intermediate burner section between the two sections. The intermediate burner section has an annular wall surrounding a mid-section of the burner interior. The annular wall has an annular cooling fluid passage, for guiding the oxygen containing fluid, and an annular fuel passage for guiding the second fuel to the downstream burner section, the annular fuel passage being more distant to the burner interior than the annular cooling fluid passage. Two annular slots are incorporated into the annular wall. The upstream burner section has at least one integrated fuel tube through a body of the upstream burner section, configured to feed the annular fuel passage.

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 burner of a turbomachine has an upstream burner section providing a first fuel and an oxygen containing fluid to an upstream end of a burner interior, a downstream burner section for providing a second fuel to a downstream end of the burner interior, and an intermediate burner section between the two sections. The intermediate burner section has an annular wall surrounding a mid-section of the burner interior. The annular wall has an annular cooling fluid passage, for guiding the oxygen containing fluid, and an annular fuel passage for guiding the second fuel to the downstream burner section, the annular fuel passage being more distant to the burner interior than the annular cooling fluid passage. Two annular slots are incorporated into the annular wall. The upstream burner section has at least one integrated fuel tube through a body of the upstream burner section, configured to feed the annular fuel passage.

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.