A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.

An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions.

A method for manufacturing a stator operatively associated with an inner and outer circumferential jigs including sequentially ordered steps of inserting segment coils, each constituting of a pair of straight portions connected with a connecting portion in a U-like shape, in slots of a stator core, rotating a twisting ring while distal end parts of the pairs of straight portions protruding on an opposite side to the connecting portions are engaged with ring grooves of the twisting ring to twist and shape in one direction the distal end parts located in odd-numbered positions from an outer circumferential side or an inner circumferential side in a radial direction and twist and shape the distal end parts located in even-numbered positions in an opposite direction to the one direction, and welding the distal end parts twisted in the one direction and the distal end parts twisted in the opposite direction.

A fan includes a hub, several fan blades, and a motor that is operable to drive the hub. A motor controller is in communication with the motor, and is configured to select the rate of rotation at which the motor drives the hub. The fan is installed in a place having a floor and a ceiling. An upper temperature sensor is positioned near the ceiling. A lower temperature sensor is positioned near the floor. The temperature sensors communicate with the motor controller, which includes a processor configured to compare substantially contemporaneous temperature readings from the upper and lower temperature sensors. The motor controller is thus configured to automatically control the fan motor to minimize the differences between substantially contemporaneous temperature readings from the upper and lower temperature sensors. The fan system may thus substantially destratify air in an environment, to provide a substantially uniform temperature distribution within the environment.

A blade attaching method is provided for a power generating apparatus which may include a blade, a hub having a blade attaching part, a bearing, a generator, and a pitch drive mechanism. The method may include, but is not limited to: a step of attaching a suspension device to the blade; a step of lifting the blade; a step of holding the blade so that the blade attaching part of the hub faces the blade root part of the; a step of rotating the blade attaching part by the pitch drive mechanism to a set angular position while holding the hub; and a step of fixing the blade to the hub after rotating the blade attaching part to the set angular position.

A method of working a gas turbine engine component, for example, a turbine airfoil platform having a heat crack, is disclosed. The presented method may allow turbine airfoils to be repaired, modified, manufactured or otherwise worked and subsequently assembled into a turbine section of a gas turbine engine. This method may help to reduce the costs of operating a gas turbine engine by allowing damaged turbine airfoils to be repaired rather than discarded.

An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.

A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.

An object is to provide a manufacturing method of a compressor impeller which produces a small post-cutting residual strain. A compressor impeller is formed by cutting a workpiece. The manufacturing method of a compressor impeller includes: a workpiece-fixing step of fixing a workpiece W on the supporting pedestal 3; and a cutting step of cutting inter-vane regions R and forming a plurality of vane sections B1, B2 and so on with intervals between one another in the circumferential direction of the workpiece W while pressing the workpiece. The cutting step includes selecting one of following steps. In the first cutting step, when successively cutting the plurality of inter-vane regions R1, R2 and so on disposed continuously in the circumferential direction of the workpiece, adjacent one of the inter-vane regions is avoided as often as possible. In the second cutting step, when simultaneously cutting a part of the plurality of inter-vane regions R1, R2 and so on which includes more than one of the inter-vane regions disposed continuously in the circumferential direction of the workpiece, at least one of the part of the plurality of inter-vane regions being cut simultaneously is positioned away from other inter-vane regions being cut simultaneously by a distance of one or more inter-vane regions as often as possible.