Abstract: A ceiling sweep fan comprising a rotor supported for axial rotation about upper and lower housings, the rotor supporting a plurality of radially extending fan blades, the upper housing and rotor enclosing an electric motor that drives the rotor; wherein the fan includes stop means to cause the rotor to stop at a fixed position relative to the upper and lower housings.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment 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 and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction.

Abstract: A cooled component for a gas turbine engine, the component includes a segment region defining a segment of an annulus for passage of hot gases therethrough, the segment region having a pair of opposed side faces configured to lie substantially adjacent respective corresponding side faces of segments of similar operationally and circumferentially adjacent components, wherein: the segment region includes an elongate cooling slot in at least one of the side faces, the cooling slot being arranged in fluid communication with at least one flow passage within the segment region for a supply of cooling fluid to the slot, and the slot is substantially closed at an upstream end of the slot and open at a downstream end of the slot so as to define an outlet for the cooling fluid at an operationally downstream region of the at least one of the side faces.

Abstract: The intake cone for a gas-turbine engine is wound in one piece from fiber compound material with fiber layers crossing one another. It is provided with a fiber compound belt, wound in the circumferential direction of the intake cone, in the connecting area with a mounting flange, which is of segmented design and thus features reduced circumferential stiffness, of a metallic retaining ring attached to a fan rotor disk. The intake cone is easily manufacturable with almost constant wall thickness and in high quality, can reliably be subjected to non-destructive testing and, in combination with the mounting flange, which is flexible in the radial direction, ensures safe connection of the two components despite the different thermal and elastic behavior of the respective materials.

Abstract: A turbine bucket is provided and includes a shank defining a cavity therein, which is connectable with a rotor such that wheelspace air having an initial pressure is permitted to flow into the cavity and a platform coupled to the shank and defining a cooling hole therein, the shank and the platform each further defining the cavity and the cooling hole, respectively, as being fluidly communicative with one another, such that the wheelspace air permitted to flow into the cavity is deliverable from the cavity and through the cooling hole at a second pressure greater than the initial pressure.

Abstract: A compressor rotor for an air cycle machine (ACM) includes a plurality of blades that each includes a root, a tip, a first surface and second surfaces. The first and second surfaces are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor. The X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction.

Abstract: A turbine rotor for an Air Cycle Machine includes a hub with a multiple turbine blades which extend therefrom, each of the multiple of turbine blades defined by a set of coordinates.

Abstract: The present invention deals with a new system for transmitting energy through a cable and interconnected pulleys. The traditional power transmission through pulleys sizes the system of belts and friction surfaces depending on energy to be transmitted and is obtained through systems composed of a rotary element for every point of application and of a flexible element for the connection. In the proposed system, the flexible element is a high-resistance cable and friction on the rotary element is increased by using interconnected pulleys, which increase the cable friction surface allowing power transmissions without any sliding till the cable breaking point. The lightness of such system allows it to find optimum application in transmitting to ground all wind energy produced at an upper level. The system of interconnected pulleys is further applied to discontinuous tractions in the sailing field, replacing the traditionally used winches.

Abstract: A stator vane with an endwall having a mate face with a seal slot, where the seal slot includes a row of feed slots on an outer side and two rows of impingement slots on an inner side and along the sides of the seal pin. Each impingement slot is connected by an impingement hole to one of the feed slots. With the seal pin secured within mate face seal slots of adjacent endwalls, cooling air flows through the feed holes and through the impingement holes to provide convection and impingement cooling for the mate faces. The spent impingement cooling air then flows out the diffusion slots and into the gap to purge hot gas flow away from the gap.