Abstract: In a fan including a hub mounted for rotation and a plurality of fan blades, an attachment assembly for detachably engaging at least one of the plurality of fan blades with the hub, the attachment assembly comprising a stop carried adjacent an end of a selected one of the plurality of fan blades, a socket carried by the hub for receiving the end of the selected one of the plurality of fan blades, and an abutment mounted for movement between a first position to permit the end of the selected one of the plurality of fan blades to admit into the socket, and a normal second position against the stop.

Abstract: The invention is a penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16). The casing includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional, but highly recommended collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36).

Abstract: A turbine blade includes an airfoil and integral dovetail. The airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending from a root to a tip plate. Twin ribs extend outwardly from the tip plate between the leading and trailing edges, and are spaced laterally apart to define an open-top tip channel therebetween. Each of the tip ribs has an airfoil profile for extracting energy from combustion gases flowable around the turbine blade.

Abstract: Brush seal for sealing two spaces of differing pressure (P1, P2) between a stator (20) and a rotor (10) of a turbomachine. The bristles (30) of the brush seal comprise angled bristle sections (31), of which the ends run against the seal surface of the rotor (10). In this manner, a low bristle stiffness and a low required radial structural space can simultaneously be achieved.

Abstract: A cooling steam circulation passage for a gas turbine rotor (30) having turbine discs (41.about.47) are composed of center line bores (73.about.77) open at an axial end of the rotor and extending through a central portion of the rotor; a steam inlet-outlet pipe (79) coaxially disposed therein so as to define an annular passage (81) for cooling steam at an outer side; steam cavities (89a, 89b) defined between and by facing side surfaces of said turbine discs; steam cavities (91a, 91b) each defined at non-facing side surface portions of said turbine discs (41, 43); axial steam holes (61, 63) formed to extend through the turbine discs and including a partition tube (99); and radial steam holes (97, 103a, 103b, 105, 107) extending from each of the steam cavities (91a, 101, 89a) to mounting portions for the rotor blades.

Abstract: A propulsion engine fan incorporates two sets of blades with recessed portions formed along the surface of each blade. One set of blades has a higher resonant frequency than the other set of blades. In an illustrative embodiment of the invention, first and second blade groups each comprise an airfoil portion forming a surface for directing the flow of a working fluid through the engine. Each of the first group of blades has first and second recessed regions formed from the blade surface and has a first resonant frequency. Each of the second group of blades has third and fourth recessed regions formed from the blade surface and has a second resonant frequency less than the first resonant frequency. The first and second group blades are arranged in an alternating pattern along the rotor portion of the fan.

Abstract: A protective air passing shield has a top shield resiliently releasably connected by a plurality of mounts to an end portion of a side shield. The protective air passing shield is disposed about a fan and connected to a shroud of a cooling system and blocks large particles from the cooling system.

Abstract: In a turbine construction which includes a rotor having at least one radial step formed therein, and at least one packing ring assembly mounted in a stationary turbine component and axially spanning the radial step, a thrust balancing arrangement for the rotor which includes an axial passage in the stationary component extending from a high pressure side of the stationary component and in fluid communication with an area adjacent the radial step on the rotor. A removable restrictor in the passage permits adjustment of the step thrust.

Abstract: The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the moving blade root section of the moving blade, a steam inlet is located in one cavity, and a steam outlet is installed in the other cavity. Steam is charged from the steam inlet and passes through a serpentine cooling passage consisting of a plurality of steam passages, and discharged to the steam outlet and collected. Bypasses are located near the base of the moving blade in the middle of each steam passage, so that cold steam on the leading edge side can be led into the bypass, mixed with the hot steam which comes from the tip section side and goes into the next downstream section of the steam passage, and flows to an upstream portion of the steam passage, thereby equalizing the steam temperature and cooling the steam over the entire range from the upstream to downstream of the steam flow.

Abstract: A drive system for a variable diameter rotor system that includes a plurality of rotor blade assemblies with inner and outer blade segments. The outer blade segment being telescopically mounted to the inner blade segment. The drive system engaging a jackscrew for telescoping the outer blade segment with respect to the inner blade segment. The drive system includes a rotor hub that is pivotally mounted to the upper end of a main rotor shaft about a pivot point. A gimbaled bearing is disposed between and attached to the main rotor shaft and the rotor hub. The gimbaled bearing permits the rotor hub to pivot about the pivot point. A blade actuation shaft is concentrically disposed within the main rotor shaft. The blade actuation shaft has a constant velocity joint pivotally attached to its upper end about the pivot point. A planetary gearset engages the blade actuation shaft with the jackscrew.

Abstract: An impeller shell 40a of a torque converter includes a main portion 41, a connection portion 42 and a stepped portion 43. The main portion 41 has a curved inner peripheral surface 41a carrying impeller blades, and is opposed to a turbine 5. The connection portion 42 has a cylindrical form larger in diameter than an outer periphery of the inner peripheral surface 41a, and is fixed to a front cover 3. The stepped portion 43 couples an end of the main portion 41 near an engine to an end of the connection portion 42 near a transmission. A corner portion formed of the inner peripheral surface 41a and a surface 43a near the engine has a radius set to 4 mm or less by preliminary forming by a press and subsequent finish forming by a press.

Abstract: In a steam cooled type gas turbine, taking the effect of efficiency and power output into consideration, a rear stage is sufficiently cooled by air in place of cooling all of the stages by steam. In a rotor of the gas turbine having a steam cooled moving blade, a moving blade disposed in a front stage is cooled by steam, and a moving blade disposed at the rear stage is cooled by cooling air through a stationary blade disposed in front of the moving blade at the rear stage.

Abstract: A rotor blade actuation system is disclosed for controlling extension and retraction of an outboard blade section of a rotor blade by varying the speed and direction of rotation between a main rotor shaft and a blade actuation shaft. The rotor blade actuation system includes a drive gear on the main rotor shaft and a blade actuation drive gear on the blade actuation drive shaft. A primary drive unit is engaged with and transmits rotary motion from the main rotor shaft to the blade actuation shaft. The primary drive unit includes an input gear engaged with the drive gear. A primary drive is engaged with the drive gear through an input gear and a master clutch. An output drive is engaged with the blade actuation drive gear. A forward clutch controls engagement of a forward planetary gearset with the primary drive and the output drive. The engagement of the forward planetary gearset causes the blade actuation shaft to rotate in the same direction as the rotation of the main rotor shaft.

Abstract: A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade.

Abstract: A removable and replaceable cover for a ceiling fan blade is disclosed. The cover includes a first material which covers the bottom surface of the fan blade and wraps around the outer edges of the fan blade and a second elastic material which joins the ends of the first material and is positioned adjacent the top surface of the fan blade. One or more straps are attached to the open end of the cover and wrap around the arm which attaches the blade to the fan motor. A hook-and-loop fastener is provided on the end of the strap and a mating attachment is provided on the first material.

Abstract: In a pumping system, a PEEK composite material may be applied to wear areas on internal components. Typically, the internal component provides a metallic substrate which is prepared with a metallic bonding layer arc sprayed onto its surface, at least at the wear area. A powderized PEEK composite material is heated and propelled against the substrate and bonding layer by a high velocity oxy fuel technique. This uniformly coats the substrate providing a durable wear surface for prolonging component life.

Abstract: The insert part (12) is introduced into the tubular part (10) from one end and comes to butt, in the direction of the longitudinal axis (11) of the tubular part (10), against a stop (24). At its end into which the insert part (12) is pushed, the tubular part (10) exhibits a region (30) with increased outer cross section. An annular tool part (36) with an opening (38) is pushed over the tubular part (10), from its other end, the cross section of which opening is smaller than that of the region (30) of the tubular part (10) with increased outer cross section. The tool part (36) is drawn over the region (30) with increased outer cross section, with the result that said region (30) is forced radially inwards, plastic deformation taking place in the process, and comes to butt, against the insert part (12), in doing so fixing the latter in the direction of the longitudinal axis (11).

Abstract: A radially sealed centrifugal pump comprises a casing (2) to which a shaft (4) is rotatably connected, and an impeller (5), connected to said shaft (4), free to rotate within said casing (2), and said pump has, between said casing (2) and said impeller (5) which are in relative motion, opposed surfaces (21, 22) which are substantially perpendicular to the axis of said impeller (5) and which form the seal.

Abstract: A gas turbine moving blade having a cooling medium flow path constructed so that a concave spherical surface (C) is formed on a inside surface of an end portion of the cooling medium path (B) formed in a blade root portion. A hollow pipe (6) is provided in the cooling medium flow path between the blade root portion and a disc. The hollow pipe has a convex spherical surface (D) at one end thereof which engages the concave spherical surface (C) and the other end of the pipe has a convex spherical surface (F) which engages an inside surface of a cooling medium path (E) formed in the disc. The hollow pipe (6) provides communication between the cooling medium path (B) on the blade side and the cooling medium path (E) on the disc side. A supporting structure (7, 8, 9) is provided for holding the hollow pipe in the communicating position.

Abstract: A propeller pitch control apparatus for an aircraft in which the vector sum of the aircraft forward speed and the propeller rotational tip speed is a selected fraction of the speed of sound, the fraction based on percent power and altitude, to maximize efficiency and minimize noise.