Abstract: A dual inlet flow wind power generating system is disclosed having two inflow chambers directing air flow into a common turbine. In one embodiment, a second phase of air flow directly impinges on the air blades of the turbine to provide multi-phased air flow with enhanced power generation. Two inflow chambers may be configured on either side of the common impingement chamber and the system may be configured around a vertical axis. Additionally, air deflectors in one or more chambers may direct flow into a flow tube and may be configured as a positive flow vortex inducer. A negative flow vortex inducer is also described, whereby air is directed by air deflectors to reduce the pressure at the outlet end of a flow tube. In another embodiment, a dual outlet flow system is described having a single inflow chamber and two impingement chambers for second phase air flow.

Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: Provided here is a counter-rotating axial flow fan with improved air flow-static pressure characteristics and reduced power consumption and noise compared to the related art. A plurality of struts are disposed to be stationary between a front impeller and a rear impeller in an air channel. A plurality of front blades are each formed of a swept-back blade, and a plurality of rear blades are each formed of a forward-swept blade.

Abstract: The present application thus provides a stator vane assembly for a turbine engine. The stator vane assembly may include a casing slot and a number of ring segments positioned within the casing slot. Each of the ring segments may include a first end and a second end. The first end and the second end may have a stepped configuration.

Abstract: A structure for a gas turbine casing, capable of preventing gas from leaking when the structure is subjected to pressure. A structure for a gas turbine casing, divided by a horizontal plane at flange sections into two halves comprising an upper-half casing (10) and a lower-half casing (11). The structure is provided with bolts (12) which are disposed in the inner surfaces of the upper-half casing (10) and the lower-half casing (11) so as to bridge therebetween, upper nuts (13) which are disposed in the inner surface of the upper-half casing (10) and attached to the bolts (12), and lower nuts (14) which are disposed in the inner surface of the lower-half casing (11) and attached to the bolts (12).

Abstract: A system for forming a barrier between a lubrication oil region and an air region of a gas turbine engine comprising a lubrication oil return path, a centrifugal oil slinger on a rotating member fixed to a spool of the gas turbine engine, a spiral groove configured to direct lubrication oil toward an oil return path, a labyrinth seal, and a cavity configured to form a non-contacting seal with the spiral groove and the labyrinth seal.

Abstract: A number of variations may include a method of balancing a rotor assembly and a balanced rotor assembly which may involve additive material applied to the rotor assembly. One or more of the following options may be employed: adding a mass to an impeller hub between two adjacent vanes; adding a mass to an impeller back wall; adding a mass to back wall scallops, and adding a mass to an impeller nose. Material removal may be used in combination with material addition.

Abstract: A yaw or pitch bearing for a wind turbine includes a slewing ring bearing assembly having an outer race and an inner race, both having an inner surface and an outer surface. The inner surface of the outer race and the outer surface of the inner race have a plurality of threads that engage and define a threaded bearing surface.

Abstract: A wind turbine with a rotor mounted on a hub section, wherein the rotor comprises a plurality of blades, at least one of which comprises a main blade section, which is optionally pitchable, and an auxiliary blade section mounted to the hub section. The auxiliary blade section is arranged in the area of a leading edge or of a trailing edge of the main blade, so that each blade is thereby provided with a leading edge slat or a trailing edge flap formed by the auxiliary blade section to increase the planform area of the blade and increase aerodynamic lift. A control method for a wind turbine controls a main blade section and an auxiliary blade section to provide different angles of attack to reduce undesired loads at sudden extreme changes of wind speed, e.g. during idling of the wind turbine. In a separate aspect, the invention provides a wind turbine having a blade with a non-pitchable leading edge slat, which extends at most 40% of the radius of the rotor in a longitudinal direction of the blade.

Abstract: A turbine blade includes a blade portion, the blade portion comprising a tip outer wall and a trailing edge, an internal cooling circuit, the internal cooling circuit being configured for directing cooling air within the blade portion, and a tip trailing edge slot positioned adjacent to the tip outer wall and the trailing edge, the tip trailing edge slot being fluidly connected to the internal cooling circuit. The tip outer wall is recessed at the tip trailing edge slot such that the tip outer wall is not provided over the trailing edge slot, thereby allowing cooling air to flow from the cooling circuit, into the trailing edge slot, and radially over the tip outer wall.

Abstract: Retention systems are disclosed. In some embodiments, a retainer apparatus is configured to retain a battery of the type used to power a pitch-control drivetrain for adjusting a pitch angle of a wind-turbine rotor. In a working embodiment, the retainer apparatus has a separable housing member and sleeve member configured to matingly engage each other in an interlocking relationship and to define a retention chamber having an open interior region sized to receive the battery. Adjustable pitch rotors having one or more innovative retainer apparatus are also disclosed. Innovative principles disclosed herein can be adapted to retainers for a wide variety of retainable elements, other than batteries.

Abstract: Systems and devices configured to shield portions of turbine conduits from contact with a working fluid flow and reduce the associated thermal gradients therein are disclosed. In one embodiment, a sleeve includes: a base portion defining a shield aperture, the base portion including an external surface configured to contact an internal surface of a turbine conduit; and a neck portion connected to the base portion and defining a neck aperture proximate a terminus of the turbine conduit, the neck aperture fluidly connected to the shield aperture.

Abstract: A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end and a rear end and mounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial or spanwise axis of the rotor blade. The flap has a basic position in which it lies flat against the upper surface of the main body. Further, the flap is passively swiveled by aerodynamic forces and inertial forces about its swivel axis to raise above the upper surface of the main body, and a reset force acts upon the flap to reset it into its basic position on the surface of the main body.

Abstract: A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.

Abstract: A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: A guide vane of a turbo-compressor has variable turbine geometry, in particular for a motor vehicle. The guide vane has a profile with a lower side, an upper side and a front edge. The guide vane is characterized by a nose which extends along the front edge of the vane, from the front edge of the vane to the upper side of the vane and forms a low pressure on the upper side of the vane when waste gas impacts the guide vane. A guide vane configuration, a turbo-compressor, a motor vehicle and a method for operating this type of turbo-compressor are further disclosed.

Abstract: A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with a pressurized fluid source for moving the seal member between the stowed position and the deployed position.

Abstract: An integrally bladed rotor for a gas turbine engine includes at least one discontinuity formed in an outer face of an outer rim. The discontinuity reduces hoop stress in the outer rim.