Abstract: The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.

Abstract: A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.

Abstract: A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.

Abstract: The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.

Abstract: A cooling passage arrangement is provided inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium. The flow region is divided in the flow direction into two cooling passages by at least one rib line which is connected to the two cast-part walls. At least one gap is provided along the at least one rib line. At the least one gap, two rib ends are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section”.

Abstract: A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud.

Abstract: A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.

Abstract: A blade for a gas turbine includes an airfoil extending in a longitudinal direction and extending transversely to the longitudinal direction between a leading edge and a trailing edge. The airfoil has a pressure side, a suction side, and a slot-like cooling medium outlet extending along the trailing edge. The cooling medium outlet is configured to discharge cooling medium supplied from an inner space of the blade. A platform extends transversely to the longitudinal direction. An end of the airfoil merges into an underside of the platform and has a transition from the airfoil to the platform at the trailing edge of the airfoil that increases in thickness in a direction toward the underside of the platform. The cooling medium outlet extends into the platform so as to reduce an operating temperature in a region of the transition from the blade airfoil to the platform.

Abstract: A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.

Abstract: A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud, thereby extending the service life of the stator blade.

Abstract: Described is a cooling passage arrangement inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium (K), which flow region is divided in the flow direction into two cooling passages (7) by at least one rib line (6) which is connected to the two cast-part walls. The invention is characterized in that provision is made along the at least one rib line (6) for at least one gap (13), at which two rib ends (61, 62) are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section” (14).

Abstract: The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.

Abstract: The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.