Abstract: A turbine debris filter apparatus for preventing clogging of cooling holes of a turbine vane, the apparatus including a filter having non-planar geometry configured to be disposed upon a shroud of the turbine vane and a support including an interface to which the filter is attached and an opening for allowing air flow, wherein the interface is configured to receive and support the non-planar geometry and the opening is configured to align with an air inlet of the shroud.

Abstract: Composite suction liners and associated centrifugal pump architectures are described herein which, in some embodiments, provide enhanced operating lifetimes under abrasive slurry conditions. For example, a composite suction liner includes a suction liner substrate and a monolithic cladding metallurgically bonded to a face of the suction liner substrate, the monolithic cladding comprising metal matrix composite including a hard particle phase dispersed in matrix metal or alloy.

Abstract: Flow path assemblies and methods for assembling such assemblies are provided. For example, a flow path assembly comprises a turbine nozzle segment including an airfoil extending axially between leading and trailing edges, an inner band defining a portion of a flow path inner boundary, and an outer band defining a portion of a flow path outer boundary. The airfoil includes a trailing edge portion defining the trailing edge and extending axially beyond the inner and outer bands such that the trailing edge is defined axially aft of the inner and outer band aft ends. The flow path assembly further comprises a shroud having a forward portion that extends axially along the trailing edge portion such that the forward portion defines the flow path outer boundary at the trailing edge portion. Methods of assembling flow path assemblies having a turbine nozzle assembly and inner and outer members also are provided.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: A high pressure compressor rotor stack includes a bore basket that includes a bore basket internal passage. A first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket. A second plurality of rotor stages at least partially defines an aft rotor bore with an aft hub structure and the bore basket.

Abstract: The present disclosure relates to a variable compressor that may include a housing, a recirculation slit, a bladder, and a pressure providing device. The recirculation slit is formed in an inlet port of the compressor housing so as to discharge a portion of a fluid flowing into the inlet port to the outside of the inlet port and then reintroduce the portion of the fluid into the inlet port. The bladder is installed to expand and contract so as to change a cross-sectional area of the recirculation slit. The pressure providing device is disposed to expand and contract the bladder.

Abstract: A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is upstream in the cooling fluid and the minor diameter is less than the major diameter.

Abstract: A propeller blade comprises a fibre reinforced blade structure spar having a blade retention section formed at one end thereof, and at least one metallic formation spray deposited onto said blade retention section.

Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.

Abstract: A device for controlling clearance at the tops of turbine rotating blades. The device comprises shroud supporting rings, abradable ring sectors, elastic centering elements, and a shroud supporting ring sectors inserted radially to the supporting shroud, between the elastic elements and the abradable ring sectors, which are attached to said supporting shroud, which has a volume varying according to temperature, due to the action of fluid supply elements.

Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion.

Abstract: An anti-icing wind power blade, consisted of a wind turbine blade, wherein the wind turbine blade is provided with an anti-icing heating device, and wherein the anti-icing heating device consists of an air heating system and an electric heating system, wherein the two systems are independent from each other, without mutual interference, and heat the wind turbine blade separately or simultaneously.

Abstract: Wind turbine blade having at least one longitudinal hollow element that defines an aerodynamic outer surface and an inner cavity having an inner surface. The blade also comprises at least one spar (1), disposed in the inner cavity and bonded to the inner surface by at least two bonding surfaces (13) located on bonding surfaces (2) of the spar (1). The spar (1) comprises, on at least one bonding zone (2), at least three fibre fabric layers (3) and at least one central core (4) and at least one lateral core (5) disposed between the at least three fibre fabric layers (3). This makes it possible to increase the resistance to shear stresses in the adhesive bond of the spar (1) to the inner surface of the longitudinal hollow element and decrease the required amount of adhesive.

Abstract: A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a downstream cover plate and a downstream angel wing that extends axially from the downstream cover plate. A portion of the downstream cover plate radially outward of the downstream angel wing defines an approximately linear profile. The turbine blade also includes a dovetail region that extends radially inwardly from the shank. A profile of a portion of the downstream cover plate radially inward of the downstream angel wing is recessed relative to the linear profile.

Abstract: An impeller includes a back cover plate, and vanes and a hub disposed on the back cover plate. The impeller further includes a sealing ring disposed on one end of the impeller away from the back cover plate. A pump using the impeller includes a volute housing and a driving device. The volute housing includes a diffusor chamber, an inlet pipe and an outlet pipe. The impeller is rotatably received in the diffusor chamber and connected to the driving device. A baffle portion is disposed on an end wall in the diffusor chamber adjacent the inlet pipe. The baffle portion engages with the sealing ring to prevent back flow of the fluid. The pump has enhanced fluid delivery efficiency. The back cover plate may further define arc strip-shaped balance holes for reducing an axial force applied to the impeller, such that rotation of the impeller is more stable.

Abstract: A bottom abutment device for a rotor having a plurality of lift assemblies. The bottom abutment device comprises at least one abutment track per lift assembly. The bottom abutment device comprises a plate with a ring and one branch per lift assembly. The bottom abutment device has a plurality of supports, each support fastenable to a rotary member of the rotor, each support extending in part in an opening in a branch, the supports giving the plate a restricted degree of freedom to move in translation, the supports giving the plate at least one restricted degree of freedom to move in rotation about the axis of symmetry.

Abstract: A housing element (12) for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element (12) being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element (12) having a planar form and, relative to the radial outer side (16) thereof, a plurality of depressions (18c), is provided. On the radial inner side (32, 34) thereof, the housing element (12) has at least one recess (26) that is configured outside of the regions in which depressions (18c) are formed on the radial outer side (16).

Abstract: An airfoil includes an endwall section and an airfoil section that defines, at least in part, an airfoil profile. At least one of the airfoil section or the endwall section includes a seal cavity, and a seal is disposed in the seal cavity.

Abstract: A transmission device of a fan is provided. A central axis and an eccentric position of the transmission device are connected with a spindle and a connecting rod, respectively. The spindle is connected with a motor through gears. A first casing and a second casing of the transmission device are pivotally connected to each other. An accommodation hole of the second casing is provided with an elastic member and a press member to engage with an engaging recess of the first casing, such that the fan can be swung. When the user applies a force to change the angle of the fan, the press member is pressed by two press portions of the first casing to disengage from the engaging recess, such that the second casing can be turned relative to the first casing to prevent gear slipping or gear jumping of the motor, the gears, and the spindle.

Abstract: Disclosed herein is a cooling apparatus of a gas turbine including a compressor disk unit mounted in a gas turbine and provided with compressor cooling passages; the torque tube units provided in an adhering state to each other while being adjacent to the compressor disk unit and provided with a cooling air supply passage communicating with the compressor disk cooling passage; and a turbine disk unit provided with a turbine disk cooling passage communicating with the cooling air supply passage of the torque tube unit, in which the torque tube units are disposed between the compressor disk unit and the turbine disk unit and coupled therewith in an adhering state to each other along an axial direction of a rotation shaft mounted in the gas turbine and the cooling air supply passage is open in horizontal direction along the axial direction from an edge of the torque tube unit.