Abstract: An impeller is arranged to rotate about a central axis, and includes a disk-shaped portion arranged to extend radially with respect to the central axis, and a plurality of rotor blades arranged along a circumferential direction on one surface of the disk-shaped portion. Each rotor blade has one end arranged at an outer edge portion of the disk-shaped portion, and an opposite end arranged radially inward of the outer edge portion of the disk-shaped portion. The rotor blades include a plurality of first rotor blades each of which includes a first curvature portion and a plurality of second curvature portions. A center of the radius of curvature of the first curvature portion of each first rotor blade is arranged on a first side of the first rotor blade with respect to the circumferential direction. A center of the radius of curvature of each second curvature portion of each first rotor blade is arranged on a second side of the first rotor blade with respect to the circumferential direction.

Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).

Abstract: A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.

Abstract: An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.

Abstract: A method for manufacturing a turbine assembly, which includes at least two aerofoils arranged adjacent towards each other and embodied as a twin vane segment, is provided. The method includes: processing the turbine assembly with a first protection technique providing a first protection for the at least two adjacent aerofoils, wherein at least one region of one aerofoil remains unprocessed; pre-processing of the at least one region that will remain unprocessed or post-processing of the at least one region that remained unprocessed with a second protection technique to provide a second protection for the at least one region of the one aerofoil, wherein the first and the second protection techniques differ from one another.

Abstract: A capacitive sensor for measuring the clearance between the apex of the vanes of a rotor and the inner surface of an abradable coating covering the inner surface of a turbomachine casing, the clearance measuring capacitive sensor including a first electrode the material of which is abradable so as to get worn upon contacting an apex of a vane, the material of the first electrode having a degree of wear substantially identical to the degree of wear of the material of the abradable coating.

Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced from a trailing edge of the airfoil, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber extends from a fore section positioned proximal to one of a pressure side surface and a suction side surface of the airfoil to an aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber.

Abstract: A gas turbine module comprises a frame, a bearing support ring, a service line, and a scupper channel system. A service line is disposed through a radial passage of the frame and a service line port of the bearing support ring. The scupper line is disposed radially through a radial passage of the frame and is open to the scupper drain port. The scupper channel system is formed into a radially inner surface of the bearing support ring, and includes a collection portion in fluid communication with the scupper drain port.

Abstract: A gas turbine engine assembly includes a second module connected axially to a first module along a joint, and an annular cavity defined between the first module and the second module. The seal assembly is disposed proximate the cavity, and includes a seal support ring, a first finger seal, and a second finger seal. The support ring has a backing portion secured to a radial wall of to the first module, and a first seal land extending axially into the cavity away from the first module. The first finger seal has a free end adapted to contact an inner side of the first seal land. The second finger seal is adapted to seal a radially outer portion of the annular cavity.

Abstract: An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut.

Abstract: Submersible pump which comprises: a first motor provided with a first outlet shaft; a pumping body in which an impeller is housed that is fixed to the first outlet shaft of the first motor and drivable by the latter in order to pump a process fluid from a suction mouth to a delivery mouth of the pumping body itself; a support casing fixed to the pumping body and provided, at a lower end thereof, with an inlet opening through which a flow of the process fluid is susceptible to enter into the support casing itself; a dispersion head arranged at the lower end of the support casing and drivable in order to remove detrital material, which is conveyed by the flow of the process fluid into the inlet opening of the support casing.

Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.

Abstract: An article is disclosed including a manifold, an article wall, a post-impingement cavity and a plurality of post-impingement partitions. The manifold includes an impingement wall defining a plenum and a plurality of impingement apertures. The article wall includes a plurality of external apertures. The post-impingement cavity is disposed between the manifold and the article wall, and is arranged to receive a fluid from the plenum through the plurality of impingement apertures and exhaust the fluid through the plurality of external apertures. The plurality of post-impingement partitions divide the post-impingement cavity into a plurality of sub-cavities, and hermetically separate the plurality of sub-cavities from one another. The impingement wall, article wall and plurality of post-impingement partitions are integrally formed as a single, continuous article. The article may be an airfoil component.

Abstract: An exemplary pullable drawer is arranged for removably protruding in a radial direction into an outer housing of a turbine, in order to make mechanical contact with an inner carrier being concentrically arranged within the outer housing. The pullable drawer has an essentially cylindrical body, which extends along a longitudinal drawer axis. A mechanical decoupling is provided, as the pullable drawer is divided along the longitudinal drawer axis into at least separate first and second parts. The first and second parts are coupled with each other by means of a releasable mechanical joint.

Abstract: A rotor blade system includes a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast, a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly being positioned at a space relative to the first hub assembly, a torque splitter device engaged with both the first hub assembly and the second hub assembly, and a locking device operably associated with the torque splitter device. The method includes rotating the first hub relative to the second hub via the torque splitter until the first set of rotor blades align with the second set of rotor blade about a common horizontal axis.

Abstract: A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case.

Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.

Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.

Abstract: A ventilation assembly having a main housing that can be pre-installed in a wall or ceiling aperture. A fan assembly can be inserted through the aperture and releasably mounted within the main housing. The fan assembly can be removed from the main housing and replaced without removing the main housing from the wall or ceiling. An accessory component can be releasably mounted to the fan assembly either through the aperture when the fan assembly is mounted or prior to installation of the fan assembly.

Abstract: A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.