Abstract: A steam turbine and a rotor are disclosed having steam extending internally along at least part of the rotor. The rotor includes an interface and a steam passage system formed in the rotor, the passage system including a first inlet flow passage to the interface, the first inlet flow passage configured to receive steam from a first region of an outer surface of the rotor, a first outlet flow passage from the interface, the first outlet flow passage configured to pass steam to a second region of the rotor, a second inlet flow passage to the interface, the second inlet flow passage configured to receive steam from a third region of the outer surface of the rotor, a second outlet flow passage from the interface, the second outlet flow passage configured to pass steam to a fourth region of the rotor.

Abstract: A blade assembly for a rotary component comprises an aerofoil member and a displacement apparatus on the aerofoil member for displacing a detached first portion of the aerofoil member in a rearward direction relative to a second portion of the aerofoil member. On failure of the aerofoil member, the displacement apparatus displaces the first portion from the second portion in the rearward direction.

Abstract: A multiblade air blower has a multiblade impeller, an orifice, an axially overlaid portion, and an airflow collision prevention device. The multiblade impeller includes a main plate and a blade. The blade is provided at the main plate to form a blade inner periphery. The orifice has an open end and an orifice inner periphery. The open end is positioned toward the main plate from a blade end face. The orifice inner periphery has an inner diameter larger than that of the blade inner periphery, and guides air to the multiblade impeller. The axially overlaid portion is a part where the orifice and the blades are overlaid. The airflow collision prevention device is provided at the blade and at an inner side of the orifice inner periphery. The multiblade air blower suppresses loss of air distribution efficiency and increased noise.

Abstract: A multi-blade fan including a spirally-shaped casing having an inlet and an outlet; an electric motor disposed inside the casing; a main plate provided perpendicular to a rotation axis of the electric motor and having a ventilation hole; first blades disposed at a side of the inlet of the main plate; and second blades disposed at an opposite side of the inlet of the main plate. Herein, a diameter of the main plate is smaller than an outer diameter of the first and second blades and is larger than an inner diameter of them. Furthermore, an outlet angle of any one or both of the first blade and the second blade is sequentially changed in an axis direction.

Abstract: A rotor assembly for a miniature gas turbine propulsion system comprises a centrifugal compressor wheel, a turbine wheel, a shaft and a tie bolt. The centrifugal compressor wheel includes a first curved tooth coupling, and the turbine wheel includes a second curved tooth coupling interconnected with the first curved tooth coupling. The shaft extends from the centrifugal compressor wheel, and the tie bolt extends between the shaft and the turbine wheel to bring the first curved tooth coupling into compression with the second curved tooth coupling. As such, the compressor wheel and the turbine wheel are assembled and remain, over the operational envelope of the propulsion system, in a reliably robust aligned configuration.

Abstract: An aerodynamic profile includes a main profile body defining a profile depth direction and being shear-flexible in the profile depth direction, a tension-stiff and compression-stiff upper covering skin, a tension-stiff and compression-stiff lower covering skin, wherein the upper and lower covering skins envelope the main profile body, a bearingless and hingeless rear profile deformation region disposed at a rear edge region, and at least one actuator disposed in the main profile body. The at least one actuator is configured to initiate a flexural motion of the main profile body resulting in a curvature of the upper and lower covering skins and to deform the rear profile deformation region and so as to yield a flap deflection directed opposite to a direction of the flexural motion.

Abstract: A compressor rotor 6a and a turbine rotor 7a are respectively attached at either end of the main shaft 13 so that the compressor rotor 6a is driven by the power generated by the turbine rotor 7a. The main shaft 13 is supported by rolling contact bearings 15 and 16 relative to the radial direction. The thrust force applied to the main shaft 13 is supported by electromagnets 17. A sensor 18 is provided to detect the thrust force which affects the main shaft 13 through air within the compressor 6 and the expansion turbine 7. In the sensor 18, sensor elements having the properties changeable in accordance with a pressing force and capable to electrically detect the change in the properties are arranged in a circumferential direction of the main shaft. The sensor 18 detects the thrust force from the output of the sensor elements.

Abstract: An apparatus includes an optical portion disposed on a carrier portion. The optical portion includes an optical path of and a magneto-sensitive element within the optical path. A light source is disposed on the carrier portion in operative communication with a first end of the optical path, and a photo-detector is disposed on the carrier portion in operative communication with a second end of the optical path.

Abstract: A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage.

Abstract: A blade joint for joining a first blade segment and a second blade segment, each having an aerodynamic profile, in a rotor blade is disclosed. The blade joint includes a first joint segment and a second joint segment each having an outer surface, an inner surface, and a thickness therebetween. The outer surface of each joint segment has an aerodynamic profile. The first joint segment and the second joint segment each further have a joint interface end, a blade interface end, and a length therebetween. The joint interface end of the first joint segment and the joint interface end of the second joint segment are configured to couple the first joint segment and second joint segment together.

Abstract: This patent discloses a fan capable of 360 degree continuous rotation. The fan may include an impeller positioned within the impeller housing, an impeller motor fixed to the impeller housing, where a control knob may control the impeller motor. The fan further may include an impeller shaft connected between the impeller and the impeller motor to rotate the impeller and the impeller housing may reside on a base. A contact ring may be positioned within the base. The impeller motor and the impeller housing may rotate relative to the contact ring, which may provide power to the impeller motor through brushes. A housing motor may be positioned within the base and be connected to the impeller motor to rotate the impeller motor. A housing motor switch may control the housing motor.

Abstract: An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.

Abstract: A turbomachine fan including blades and inter-blade platforms having radial flanges fastened to flanges of a rotor disk by threaded rods inserted into bushes mounted in orifices in the flanges of the platforms is disclosed. Each bush includes at least one deformable part interposed transversely between the threaded rod and an edge of the orifice in which the bush is mounted. The deformable part is intended to allow the platform to pivot in the event of an impact of a blade against the platform and to absorb some of the energy of the impact.

Abstract: A device for controlling a pivot of a variable-pitch blade in a stator of a turbomachine compressor is disclosed. The device for controlling a pivot of a variable-pitch blade includes a control lever and a pivot with a bottom end and a top end. The top end is connected to the control lever. The device also includes a first swivel bearing placed at the bottom end of the pivot and a second swivel bearing placed at the top end of the pivot.

Abstract: A turbine rotor blade with a low cooling flow serpentine circuit to provides cooling for the airfoil. The circuit includes a three pass aft flowing serpentine circuit that begins at the airfoil mid-chord region and connects to a series of multiple impingement cooling holes formed within the trailing edge region. A double pass forward flowing serpentine circuit then connects with the triple pass aft flowing serpentine circuit to provide cooling for the airfoil mid-chord region and then discharges the cooling air into a blade tip cooling channel to provide cooling for the blade tip section. The three pass aft flowing serpentine circuit includes a tip turn that provides cooling for a forward section of the blade tip not covered by the tip cooling channel.

Abstract: An air turbine starter for starting an engine includes a housing, and a flow path communicating a flow of gas therethrough; a turbine member; a clutch; and a decoupler device at least partially housed within the output member of the clutch. The decoupler device includes a first shaft portion coupled to and rotating with the output member and a second shaft portion coupled to and rotating with the engine. The first and second shaft portions are axially aligned and configured to engage each another for rotation in a first direction and to separate from each other in a second direction to decouple the output member of the clutch from the engine. The starter further includes a bearing between the inner surface of the output member and the second shaft portion for reducing friction between the second shaft portion and the inner surface of the output member when the first and second shaft portions are decoupled.