Abstract: A method for adjusting a barometric cell may include coupling the barometric cell to a control device via an actuating rod. The actuating rod may be movably mounted on a charging device in any desired position. The method may include applying a freely selectable pressure to the barometric cell so as to bring the actuating rod into contact with a stop, adjusting the barometric cell until a sensor registers a predefined value, and fixing the barometric cell on the charging device.

Abstract: A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

Abstract: A pump housing support for use in a pump assembly, the pump assembly including a plurality of component parts which include a seal housing, a drive shaft having a rotation axis, an impeller and a pump housing, the pump housing which includes a main liner, the pump housing support including a base and a mounting member which includes a body portion to which a part of the pump housing can be mounted and a locating flange extending therefrom, the locating flange having first and second locating surfaces on opposing sides thereof and where the main liner is located on the first locating surface and the seal housing is located on the second locating surface.

Abstract: A rotor hub assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectable to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.

Abstract: A multilayer acoustic treatment panel including a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; and a second cellular-structure core sandwiched between the intermediate skin and a continuous skin. The perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with the two ends of a soundwave flow channel arranged in the second cellular-structure core.

Abstract: A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine.

Abstract: A fan assembly for creating an air current includes an air outlet mounted on a stand. The stand includes a base and a body tiltable relative to the base. Each of the base and the body has an outer surface shaped so that adjoining portions of the outer surfaces are substantially flush when the body is in the untilted position.

Abstract: The present invention provides a rotary blood pump with both an attractive magnetic axial bearing and a hydrodynamic bearing. In one embodiment according to the present invention, a rotary pump includes an impeller assembly supported within a pump housing assembly by a magnetic axial bearing and a hydrodynamic bearing. The magnetic axial bearing includes at least two magnets oriented to attract each other. One magnet is positioned in the spindle of the pump housing while the other is disposed within the rotor assembly, proximate to the spindle. In this respect, the two magnets create an attractive axial force that at least partially maintains the relative axial position of the rotor assembly. The hydrodynamic bearing is formed between sloping surfaces that form tight clearances below the rotor assembly.

Abstract: A composite spar for a helicopter blade includes two or more layers of unidirectional laminate material. One or more upper plies of bi-directional laminate extend from an upper airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional laminate material. One or more lower plies of bi-directional laminate material extend from a lower airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional material. The upper plies and the lower plies overlap defining a crackstopper layer configured to prevent propagation of defects in the spar.

Abstract: In one aspect, the invention is a novel and non-obvious design for wind fan or wind turbine that 1) can adjust to changes in wind direction and 2) is collapsible or retractable when desired. Further, the invention relates to a novel and non-obvious design for a fan blade assembly that allows for the ability of the wind turbine to adjust to changes in wind direction and allows for the wind turbine to collapse or retract into a housing when not in use.

Abstract: Disclosed are a rotor for wind power generation which converts wind power into electric energy, and a wind power generation apparatus having the same. The rotor for wind power generation includes a vertically or horizontally oriented rotating shaft, a plurality of main blades conically installed to the rotating shaft so as to be equidistantly spaced apart from one another, and an auxiliary blade coupled to each of the main blades, the auxiliary blade being configured to be bent according to the direction of wind. Through this configuration, it is possible to reduce an initial starting wind velocity and achieve increased lift and drag force, resulting in an enhancement in power generation efficiency.

Abstract: A sealing element is provided for sealing a leak path between a radial outer platform of a turbine nozzle and a carrier ring for carrying said radial outer platform. The carrier ring has an axially facing carrier ring surface and the radial outer platform has an axially facing platform surface. The carrier ring surface forms a first sealing surface and the platform surface forming a second sealing surface. The first and second sealing surfaces is aligned in a plane with a radial gap between them. The sealing element includes a leaf seal adapted to cover the gap between the first and second sealing surfaces, and an impingement plate for allowing impingement cooling of a radial outer surface of the radial outer platform. The impingement plate is adapted to be fixed to the turbine nozzle. The sealing element may be part of a nozzle arrangement of a gas turbine.

Abstract: A method of locking a rotor of a wind turbine, the method including positioning of the rotor in a locking position; applying a rotor lock; forcing the rotor to turn in a first direction; and, applying a rotor brake.

Abstract: A bucket assembly and a method for treating a bucket assembly are disclosed. The bucket assembly includes a platform, the platform defining a platform cooling circuit, and an airfoil extending generally radially outward from the platform, the airfoil defining an airfoil cooling circuit. The bucket assembly additionally includes a lower body portion extending generally radially inward from the platform, the lower body portion defining a root and a cooling passage extending from the root, the cooling passage in fluid communication with the airfoil cooling circuit. The bucket assembly further includes a transfer passage defined between and in fluid communication with the airfoil cooling circuit and the platform cooling circuit such that a cooling medium may flow from the airfoil cooling circuit through the transfer passage to the platform cooling circuit.

Abstract: A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described.

Abstract: The present application provides a turbine blade cooling system. The turbine blade cooling system may include a first turbine blade with a first turbine blade platform having a cooling cavity in communication with a pressure side passage and a second turbine blade with a second turbine blade platform having a platform cooling cavity with a suction side passage. The pressure side passage of the first turbine blade platform is in communication with the suction side passage of the second turbine blade platform.

Abstract: A nose cone assembly is provided comprising a nose cone 104, a support ring 106 on which the nose cone 104 is mounted, and an insulating layer 110 disposed between the nose cone 104 and the support ring 106, the insulating layer 110 at least partially comprising glass fibers. A composite nose cone is also provided comprising an attachment region A, in which composite fibers are oriented substantially perpendicular to an axis of rotation of the nose cone 104, and an impact region I, in which composite fibers are oriented substantially parallel to the axis of rotation of the nose cone 104. Also provided is a support ring 106 for a nose cone assembly, the support ring 106 comprising an annular main body 140 and an annular projecting attachment flange 142, the attachment flange 142 terminating in a plurality of circumferentially spaced attachment tabs 144, wherein the attachment flange 142 forms with the main body 140 a cross section having at least two C curves 160, 162.

Abstract: A blade for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles (7, 9, 10) arranged one behind the other in the flow direction are provided, of which each has substantially the shape of a blade profile, where a passage (8) is provided between each two partial profiles and is passed through by fluid from the blade pressure side to the blade suction side.

Abstract: A turbine blade cooled by an automatically variable internal flow of cooling fluid. The blade includes orifices situated under the blade root via which the cooling fluid penetrates, and an adjustment plate including holes situated in register with the orifices, the adjustment plate having a coefficient of expansion that is different from the coefficient of expansion of the blade root.

Abstract: An airfoil includes an airfoil wall having an exterior airfoil surface and an interior surface. The interior surface provides an airfoil cavity. A baffle is arranged in the airfoil cavity and provides a baffle wall having first and second portions spaced from one another on first and second sides. A tube interconnects the first and second portions and is configured to convey fluid through the tube between the first and second sides. The airfoil is cooled by supplying cooling fluid to a baffle arranged within an airfoil. The cooling fluid is passed through baffle cooling holes to a gap between the baffle and airfoil to cool an interior surface of the airfoil. A portion of cooling fluid is conveyed from one gap location to another gap through a tube in the baffle. Another portion of the cooling fluid is passed through film cooling holes in the airfoil.