Abstract: A turbine having a cam follower operable to control turbine blade pitch in association with a position thereof is provided and includes an axially movable plate, a rotational and axially movable flyweight and a system operably coupled to the plate and the flyweight whereby, at low RPMs, the system prevents flyweight rotation such that the plate and the flyweight position the cam follower at a first position, at medium RPMs, the system permits flyweight rotation such that the plate and the flyweight position the cam follower at a second position, and, at high RPMs, the system prevents further flyweight rotation and permits initial axial movement of the plate and the flyweight such that the plate and the flyweight position the cam follower at a third position.

Abstract: Provided is a small-sized propeller windmill which can efficiently generate power even when a wing speed is low, has no possibility that the windmill is broken even when a strong wind blows, can stably ensure a weathercock direction of a base blade, and can suppress an environmental burden, in such a propeller windmill, the blade having a corrugated wing shape is supported in a cantilever manner by way of an elastic body, and the blade and the elastic body are made of paper or plastic. Further, to stably ensure the weathercock. direction of the base blade, a weathercock stabilizing mechanism is arranged behind the base blade.

Abstract: A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates.

Abstract: A fan holder for holding a fan is disclosed. The fan holder includes a frame for containing the fan, at least one hook for hooking the fan when the fan is contained inside the frame, at least one resilient arm connected to the frame for resiliently contacting the fan base when the frame is installed inside a fan base, and at least one resilient clip connected to at least one lateral side of the frame for wedging inside a slot formed between the fan base and a casing when the frame is installed inside the fan base.

Abstract: Embodiments of the invention provide a hydraulic isolator to split a volute of a pump into two compartments. The hydraulic isolator is positioned within the volute and includes an inlet positioned around a volute inlet channel of the pump, and an outlet positioned adjacent to an outlet channel of the pump. The hydraulic isolator also includes a toroidal portion to at least partially surround an impeller of the pump.

Abstract: A method is provided for repairing a metallic turbine component which includes at least two airfoils interconnected by a mid-span shroud. The method includes: (a) applying a reinforcement plate to the mid-span shroud; (b) applying braze material to at least a portion of a perimeter of the reinforcement plate; (c) heating the component to melt and flow the braze material between the reinforcement plate and the mid-span shroud; and (d) allowing the braze material to cool and solidify so as to bond the reinforcement plate to the mid-span shroud.

Abstract: The invention relates to a fluid pump, in particular liquid pump, with a rotor, with a rotor shaft (11) and with at least one rotor blade for delivering the fluid, wherein the rotor with regard to its diameter may be changed between a first, compressed condition, and a second expanded condition, wherein the at least one rotor blade comprises at least two erection elements (12, 13, 14) which are distanced to one another along the longitudinal axis (18) of the rotor shaft (11) and which project away from the shaft in the expanded condition of the rotor, as well as at least two limp rib elements (25, 26, 27, 28, 29, 30) which run at a distance to one another from one erection element (12, 13, 14) at least up to a further erection element, wherein a limp membrane (10) is held between the rib elements, which is tautened in the expanded condition of the rotor.

Abstract: A clip to connect a blade to a rotor disk, the blade with a root and a tip in a spanwise direction, and a leading edge and a trailing edge in a chordwise direction, the root with a bottom surface, includes a locking mechanism shaped to engage a complementary slot extending into the bottom surface of the blade root in the spanwise direction; a support connected to the locking mechanism extending the length of the bottom surface of the root in the chordwise direction; and first and second arms extending radially inward converging in an axial direction so that the arms are closer at their distal ends to engage the rotor disk.

Abstract: A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.

Abstract: In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.

Abstract: According to the inventive concept, there is provided a wind turbine with at least one blade. The wind turbine comprises a first accelerometer mounted at a first radial position of the blade and being adapted to determine a first acceleration value, and a second accelerometer mounted at a second radial position of the blade different from the first radial position, and the accelerometer being adapted to determine a second acceleration value. The wind turbine further comprises a controller adapted to generate a signal based on said first and second acceleration values. There is also provided a method for monitoring a blade of a wind turbine.

Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, and third sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13 and PA-1 to PA-9, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

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: A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).

Abstract: A Ram Air Turbine (RAT) is provided and includes a turbine hub having an end plate and a nose cone attached thereto at trailing and leading ends, respectively, a governor shaft, to which turbine blades are connected, which is coupled to the end plate and supported within the nose cone to be rotatable with the turbine blades about a central axis thereof and axially movable from a first position relative to the turbine hub to a second position relative to the turbine hub and a hub assembly operably coupled to the turbine hub, the governor shaft and the turbine blades whereby the hub assembly biases the governor shaft toward the first position at low rotational speeds such that the turbine blades assume a partial coarse pitch angle, and the second position at high rotational speeds such that the turbine blades assume a fine pitch angle.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.

Abstract: A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.

Abstract: Process for producing a ceramic composite structure includes impregnating a reinforcing material with a suitable precursor slurry composition including thermosetting resin, a suitable curing agent, a ceramic component, a carbonaceous solids component, and optionally, a suitable solvent. Exemplary thermosetting resins include polyesters, vinyl esters, epoxy resins, bismaleimide resins, and polyimide resins. The carbonaceous solids component provides a suitable amount of carbon char upon pyrolization. The preform may be dried prior to curing to remove solvents and thereby provide a working material comprising up to 70 volume % solids. The preform is cured, pyrolized, and infiltrated with molten silicon to form a composite article. The thermosetting resin is selected for processibility, green strength, and relatively fast cure cycle.

Abstract: A fan rotor for an airplane turbojet including locking blade roots in the respective grooves of an airplane turbojet fan rotor. Each blade root is housed in a groove that is closed by a main latch and by an additional latch that is distinct from the main latch and that is spaced apart therefrom by a predetermined distance.

Abstract: A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.