Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: A method of altering the frequency of blades (1) having an airfoil (2) with a suction side (6), a pressure side (5), a leading edge (10), a trailing edge (7) and a blade tip (9), and including a blade root (3), in particular turbine blades, for thermal fluid-flow machines. A metallic coating (8) formed of a material identical to the parent material is applied to the blade (1), already ready for use, in the region of the blade tip (9), the thickness of the coating (8) tapering continuously at the trailing edge (7) and in the radial direction toward the blade root (3).

Abstract: A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.

Abstract: The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.

Abstract: A device for producing a soldered joint between two joining partners which can be joined via a common contact surface (7), using a solder material which can be introduced between the two joining partners. At least one joining partner (1), in the region of the contact surface (7), provides at least one recess, known as a solder reservoir (3), which faces the contact surface and into which the solder material can be introduced, and the solder reservoir (3) is completely delimited and surrounded by the contact surface (7).

Abstract: The invention relates to a gap seal in a gas turbine for sealing off a cooling space (6), formed between a heat shield (4) and a heat shield carrier (5), from a hot gas space (7) of the gas turbine. A sealing body (10) is retained in a movable manner on the heat shield (4), on the one hand, and on a blade carrier (2), on the other hand, adjacent to the heat shield carrier (5).

Abstract: A platelike projecting component portion of a component used in gas turbines or other similar applications includes a surface upon which hot gas acts and cooling bores through which a cooling medium is capable of flowing. Effective cooling is achieved by providing at least one plenum assigned solely to the component portion. The plenum is arranged so as to be directly adjacent to the surface upon which hot gas acts and through which the cooling medium is capable of flowing to provide convective heat transfer. The cooling bores are designed as blow-out orifices which emanate from the plenum and issue the cooling medium onto the surface upon which hot gas acts, thereby forming a cooling film.

Abstract: The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.

Abstract: The invention describes a device for producing a soldered joint between two joining partners which can be joined via a common contact surface (7), using a solder material which can be introduced between the two joining partners.

Abstract: A platelike projecting component portion (1) of a gas turbine or the like, with a surface (2) upon which hot gas acts and with cooling bores (12) through which a cooling medium is capable of flowing. Effective cooling is achieved in that at least one plenum (10; 30; 50) assigned solely to the component portion (1) is provided, which is arranged so as to be directly adjacent to the surface (2) upon which hot gas acts and through which the cooling medium is capable of flowing convectively, and in that, to form a cooling film, the cooling bores are designed as blow-out orifices (12; 52) which emanate from the plenum (10; 30, 50) and which issue on the surface (2) upon which hot gas acts.