A turbine housing assembly can include a turbine housing that defines a rotational axis for a turbine wheel; and a cartridge receivable by the turbine housing, where the cartridge includes a nozzle wall component with an upper nozzle surface and a plate component with a lower nozzle surface, where the upper nozzle surface and the lower nozzle surface define a nozzle space, and vanes positioned in the nozzle space, where the vanes are pivotable between a closed vanes position of 0 percent open and a fully open vanes position of 100 percent open, and where, for a vanes position of at least 50 percent open and less than 75 percent open, an axial dimension of the nozzle space increases with respect to decreasing radius as measured from the rotational axis.

The present technique presents a gas turbine blade for re-using cooling air, a turbomachine assembly having the blade, and a gas turbine having the turbomachine assembly. The blade includes a platform and an airfoil extending from the platform. The airfoil includes a pressure surface, a suction surface, a leading edge and a trailing edge. The platform includes a pressure side, a suction side, a leading-edge side and a trailing-edge side, disposed towards the pressure surface, the suction surface, the leading edge and the trailing edge of the airfoil, respectively. The suction side of the platform includes a part of the upper surface and a suction-side lateral surface of the platform. At least a part of an edge between the suction-side lateral surface and the upper surface of the platform comprises a chamfer part.

The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components.

A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

A turbine rotor blade (26) for a turbine includes an airfoil portion (30) having an airfoil formed by a pressure surface (31) and a suction surface (32); and at least one squealer rib (40, 42, 44) disposed on a tip surface (35) of the turbine rotor blade so as to extend from a leading-edge side (33) toward a trailing-edge side (34). At least one (42) of the at least one squealer rib has a ridge (43) extending in an extending direction of the squealer rib. A clearance (100) between the tip surface and an inner wall surface of a casing of the turbine, the inner wall surface facing the tip surface, has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

A guide vane (10, 10′) according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate (12) for its support on an inner ring (20). The guide vane plate has a cover surface (14) facing the vane element, a base surface (17) lying opposite to the cover surface, and an edge surface (15) joining the cover and base surfaces. In a first region (B.sub.1), the edge surface forms a chamfer (16) of the vane plate, and in a second region (B.sub.2), which forms the edge of a sector of the guide vane plate that is different from that of the first region (B.sub.1), the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes (10, 10′) according to the invention into respective uptakes (21) in an inner ring (20).

A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H.sub.1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone by electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A guide vane according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate for its support on an inner ring. The guide vane plate has a cover surface facing the vane element, a base surface lying opposite to the cover surface, and an edge surface joining the cover and base surfaces. In a first region, the edge surface forms a chamfer of the vane plate, and in a second region, which forms the edge of a sector of the guide vane plate that is different from that of the first region, the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes according to the invention into respective uptakes in an inner ring.

A sealing assembly for sealing a gap between a first component and a second component is provided. The sealing assembly includes a sealing body disposed between the first component and the second component and a pressing member disposed between the sealing body and the second component, configured to press the sealing body toward the first component, and configured to extend and compress in a circumferential direction of the first component.