Abstract: A rotor hub maintenance system and method is disclosed. The system includes at least a rotor hub, a plurality of appendages that are operatively connectable to the hub, and a plurality of support members. The preferred embodiment provides that the support members simultaneously secure the hub and appendages a predetermined height above a reference surface and provide the only support for the hub and appendages.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Abstract: A blade for a rotor of a turbine includes an airfoil, a shroud and a platform. The platform includes a top plate, a shank and a fixing part. An upstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the upstream wall at least partially covering an upstream side of the shank. A downstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the downstream wall at least partially covering a downstream side of the shank. A recess is disposed in at least one of the upstream wall and the downstream wall. The recess has an open side facing in a same direction as a respective one of the upstream wall and the downstream wall, in which the recess is disposed, is projecting.

Abstract: A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.

Abstract: An annular seal is provided for use in a turbomachine. The annular seal may form a generally rectangular cross-section and may include an outer radial surface forming an outer sealing surface and defining at least one annular groove and a plurality of slots spaced circumferentially about the outer radial surface. Each slot may have an end terminating in the at least one annular groove. The annular seal may also include a first axial sidewall forming a sidewall sealing surface and a recessed portion and a second axial sidewall opposing the first axial sidewall. At least one annular groove and the plurality of slots may be configured to maintain a low pressure environment across at least a portion of the outer radial surface. The second axial sidewall, the recessed portion, and the inner radial surface may be configured to maintain a high pressure environment there across during operation of the turbomachine.

Abstract: A bearing cup structure and a thermal module thereof. The bearing cup structure includes a cup body and a retainer ring. The cup body has a fixing section, a receiving space and a shoulder section. The fixing section is formed at one end of the cup body. The shoulder section is formed in the receiving space. The retainer ring is formed with a hole in communication with the receiving space. With the bearing cup structure, the heat dissipation efficiency of the thermal module is increased and the assembling time is shortened to lower the manufacturing cost.

Abstract: The use of a shroud surrounding turbine blades to enhance the energy output creates a distribution of wind speeds in the plane of the blades. A unique class of such shrouds previously patented by the author creates zones of higher velocity near the tips. In order to take advantage of this new distribution of velocity, new principles of propeller design are required. One of the designs involves increasing the P/D ratio and the PHI in the outer portion of the blades. This solution works for liquids and gases.

Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Abstract: A centrifugal fan includes a main plate that is driven to rotate around a rotational axis, a shroud that is disposed so as to be opposed to the main plate, including an intake port for taking in air, and plural blades that are disposed upright between the main plate and the shroud. An adjacent distance between trailing edges of two adjacent blades is gradually decreased in the direction from the shroud to the main plate, at least from a certain point in the direction from the shroud to the main plate, and further, in each blade, an inclination of a negative pressure surface of the blade that extends from the main plate toward the shroud is smaller at least in the vicinity of the trailing edge than an inclination of a pressure surface of the blade that extends from the main plate toward the shroud.

Abstract: A centrifugal pump with a cutter mechanism has a toothed cutter auger affixed to an impeller, and a toothed cutter stator affixed to the volute casing. The auger is a rotor cutter preferably profiled radially to match the inlet geometry of the impeller vanes while extending along its central axis towards the pump suction. The auger is preferably radially concentric to the impeller and includes vanes numbered preferably to match the number of vanes on the impeller. The auger is affixed to the impeller, preferably with a lockscrew threaded into a common pump shaft. The radial profile of the auger essentially makes a continuous vane with the impeller, and prevents solids from hanging on the inlet vane tip or center void while providing a smooth flow transition into the impeller.

Abstract: A rotary blood pump includes a casing defining a pumping chamber. The pumping chamber has a blood inlet and a tangential blood outlet. One or more motor stators are provided outside of the pumping chamber. A rotatable impeller is within the pumping chamber and is adapted to cause blood entering the pumping chamber to move to the blood outlet. The impeller has one or more magnetic regions. The impeller is radially constrained in rotation by magnetic coupling to one or more motor stators and is axially constrained in rotation by one or more hydrodynamic thrust bearing surfaces on the impeller.

Abstract: An integrated wind turbine. Each turbine blade has a flexible skin. Openings in the leading edge lead to one or more inflation chambers for ram air inflation during operation. A pivotal connection with the support post allows the plurality of turbine blades to yaw such that the rotor plane remains substantially perpendicular to the wind direction. The wind turbine may also include self-deploying drag vanes that extend away from the flexible skin when the wind speed is greater than the speed of the airfoil.

Abstract: A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.

Abstract: Combined bleed air and hot section component cooling air systems for gas turbine engines and methods of operating combined bleed air and hot section component cooling air systems are disclosed. An example system may include a high-pressure bleed air line receiving high-pressure bleed air; a precooler receiving at least some of the high-pressure bleed air and discharging cooled high-pressure bleed air; a pressure regulator receiving at least some of the cooled high-pressure bleed air and discharging pressure-regulated cooled bleed air to a pneumatic systems supply line; and/or a hot section component cooling air line connected upstream of the first pressure regulator and configured to convey at least some of the cooled high-pressure bleed air to a hot section component for use as hot section component cooling air.

Abstract: A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.

Abstract: The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, and a locking blade positioned about the rotor. The locking blade may include a multi-piece configuration.

Abstract: A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion.

Abstract: An assembly including a part for mounting at least one shaft bearing of a turbine engine and a support part that forms an abutment for the mounting part. The mounting part includes at least one channel through which engine gases pass, and connection parts that are capable of connecting the channel to an outer structure of the engine and to a housing holding the bearing. At least one of the connection parts is flexible so as to enable radial movement of the channel, an amplitude of the radial movement being limited by at least one of the elements of the mounting part coming onto an abutment supported by the support part. The support part extends longitudinally with regard to the direction of the rotational axis of the turbine engine so as to generate a turbine shroud that is configured to be positioned in alignment with a turbine wheel of the turbine engine.

Abstract: A fan assembly comprising, a shroud having a through opening, around which the shroud defines an air conveying ring, a motor-fan assembly which includes an axial fan rotatable with respect to the support about an axis of rotation, and a noise-reducing annular structure, having a plurality of projections which are arranged in succession in a circumferential direction and extend radially towards the axis of rotation of the fan, each projection having a face which is directed towards the axis of rotation and is substantially parallel thereto, and a plurality of portions radially recessed towards the air conveying ring. Each of the recessed portions has a face which is directed towards the axis of rotation of the fan and the profile of which in the axial direction is generally curvilinear and not parallel to the axis of rotation.