Abstract: The invention refers to a method for producing a near-surface cooling passage in a thermally highly stressed component, which includes: a) providing a component which has a surface on a hot side in a region which is to be cooled; b) letting a channel into the surface; c) inserting a cooling tube into the channel; d) filling the channel, with the cooling tube inserted, with a temperature-resistant filling material in such a way that the inserted cooling tube is embedded into the filling material, leaving free an inlet and an outlet; and e) covering the channel, with the cooling tube embedded, with an anti-oxidation, temperature-stable cover layer. The method is inexpensive and can be used in a flexible manner in the most diverse situations in order to save cooling medium or to reduce the thermal load.

Abstract: The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.

Abstract: An insert element for closing an opening inside a wall of a hot gas path component of a gas turbine includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).

Abstract: A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages.

Abstract: The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.

Abstract: The invention refers to a method for producing a near-surface cooling passage in a thermally highly stressed component, which includes: a) providing a component which has a surface on a hot side in a region which is to be cooled; b) letting a channel into the surface; c) inserting a cooling tube into the channel; d) filling the channel, with the cooling tube inserted, with a temperature-resistant filling material in such a way that the inserted cooling tube is embedded into the filling material, leaving free an inlet and an outlet; and e) covering the channel, with the cooling tube embedded, with an anti-oxidation, temperature-stable cover layer. The method is inexpensive and can be used in a flexible manner in the most diverse situations in order to save cooling medium or to reduce the thermal load.

Abstract: A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.

Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.

Abstract: The invention refers an insert element for closing an opening inside a wall of a hot gas path component of a gas turbine. The insert includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).

Abstract: A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage.

Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.

Abstract: A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.