Abstract: A composite blading member includes an airfoil and a base of composite material layers and a platform of composite material layers interfused with the airfoil and base. The platform comprises a platform shelf and a plurality of spaced-apart platform supports integral with the platform shelf and interfused with surfaces of the base. Such blading member was made by providing a partially cured airfoil-base preform and a platform preform, including an airfoil shaped opening therethrough and preforms of the platform supports. The airfoil-base preform was inserted through the airfoil shaped opening whereby cooperating surfaces of the platform preform and airfoil-base preform were in juxtaposition. The preforms were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms under conditions to substantially fully cure the structures.

Abstract: A yawing system for a wind turbine, the wind turbine comprising a tower fixed to the ground and a frame (1) housing an electric power generator, the tower and the frame (1) being joined by the yawing system which allows the orientation of the frame (1) with respect to the tower according to the direction of the wind. The yawing system comprises: a gear ring (2) fixed to the tower, the gear ring having a sliding track (3) on which the frame (1) rests and slides in its yawing movement, at least one geared motor fixed to the frame (1), meshed with the gear ring (2) through a gear wheel, at least one active braking module (5), and at least one passive braking module (6). The invention further comprises a sliding track (3) and a friction track on the gear ring, this friction track (10) being different from the sliding track (3), and the active braking modules (5) and passive braking modules (6) comprising a friction plate (11) acting on the friction track (10) of the ring.

Abstract: A blade for a wind turbine includes a device for causing air at an increased velocity and/or pressure to escape from exit openings in the blade, thereby to apply a force. Pressure and diameter adjustable valves may be provided at each exit opening or orifice to allow the air to exit from the blade only when the air pressure within the blade exceeds a preset level. Also disclosed is the provision of valves at the exit openings or orifices on an opposite edge of the blade that allows air to escape from the blade to slow down but not stop rotation of the blade when a dangerous wind condition is detected.

Abstract: A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.

Abstract: A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.

Abstract: A retaining key for a turbine nozzle includes a key body having top and bottom surfaces, a pair of sides and a pair of ends including a forward end having a pair of horizontal shoulders on opposite sides of a center rib, the shoulders located substantially midway between the top and bottom surfaces such that the forward end has a substantially inverted T-shaped profile, and a rearward end having a first surface portion extending from and substantially perpendicular to the top surface and a second surface portion extending at an acute angle downwardly and toward the forward end and intersecting the bottom surface.

Abstract: A system for mounting a fan shroud to a radiator assembly comprises a fan shroud having a general profile defining at least one fan shroud slot aligned along a first axis. A fan shroud mount is carried by the radiator assembly. The fan shroud mount has a general profile defining at least one fan shroud mount slot aligned along a second axis which is perpendicular to the first axis of the fan shroud slot. A cage nut is utilized for mounting the fan shroud with the fan shroud mount. The fan shroud slot and the fan shroud mount slot are designed for overlapping orientation. This overlapping orientation enables the fan shroud fastener to be simultaneously received within the fan shroud slot and the fan shroud mount slot. In operation, the fan shroud fastener may move along either the first axis or the second axis for positioning the fan shroud at a desired horizontal and vertical location with respect to the radiator assembly.