Abstract: A gas-turbine moving blade made of a Ni-base superalloy containing less grain boundary strengthening elements, in which a blade portion is formed of a single crystal and the rest is formed of columnar crystals, and a gas turbine including the moving blade. A thermal efficiency of the gas turbine can be improved to 35% or more, and a thermal efficiency of complex power generation with a steam turbine can be improved to 45% or more.

Abstract: A hybrid vacuum pump comprising a turbomolecular stage positioned at the inlet end of the pump and comprising a stator formed from an array of stationary blades and a rotor formed from a further array of blades arranged for rotation at high speed between the stator blades. A molecular drag stage is positioned at the outlet (high pressure) end of the pump and comprises at least two discs arranged for rotation within a stator with a minimal clearance between the circumferential edge of the discs and the stator. A flow passageway linking the turbomolecular stage with annular channels is defined between the stator and opposing faces of the discs and projections extending from the stator are provided for deflecting gas being pumped from the annular channels during rotation of the discs.

Abstract: A plastic fan includes two injection molded parts, each of which includes its own hub and a set blades extending outwardly from the hub to a band. The two parts are co-operatively sized and shaped to be assembled into a single operable fan having: 1) a hub comprising the hubs of each of the component parts; 2) the blades of the component parts; and 3) a circumferential band comprising the bands of the component parts. The fan blade separation on each of the fan parts is relatively large, permitting separate injection molding of each part. The resulting fan may be designed to have far greater blade number and blade solidity that would be possible for a fan that is injection molded by standard techniques. The fan may be packaged in an airhandler assembly that includes a flexible cylindrical retraining member generally coaxial with, and external to, a rigid cylindrical member, the fan band and the stator assembly, so as to support the stator assembly and to maintain the parts in place.

Abstract: An aircraft gas turbine has a barrier air flow produced by the fan or a low-pressure compressor which passes continuously through the compressor bearing chamber, while the turbine bearing chamber is supplied with barrier air by the high-pressure compressor. The barrier air flow drawn from the turbine bearing chamber passes into an ejector which is also connected to the compressor bearing chamber so that, when the pressure is insufficient, the barrier air flow is drawn-off by the ejector.

Abstract: A fluid forcing device comprising many rotatable slender elements that converts mechanical energy into fluid energy by mechanically arranging and maintaining, at all times, the rotatable slender elements in a pre-determined wave form and by mechanically moving the wave form in a direction normal to the rotation of the elements.

Abstract: A transverse fan in which a plurality of blades are disposed between disk- or ring-shaped end plates in a circumferential arrangement at fixed mounting pitches in a ring-shaped configuration. Partitions plates are disposed at intermediate portions in the longitudinal direction of the blades such that each of the blades is inclined at fixed angles with respect to a fan axis and mounted at unequal pitches. The transverse fan includes a plurality of multi-bladed impeller units disposed between the disk-shaped end plates. Each of the multi-bladed impeller units has one disk-shaped partition plate having one surface on which a plurality of blades are integrally disposed along a circumferential direction thereof at unequal pitches and inclined at predetermined angles so as to extend along the axial direction of the transverse fan. A plurality of the multi-bladed impeller units are integrally stacked coaxially with each other to form the transverse-fan.

Abstract: A rotor blade for a rotary-wing aircraft, of an airfoil section has a basic blade thickness at 12% chord length, a portion of an increased blade thickness between the leading edge and a point corresponding to about 90% chord length, a maximum blade thickness at a position shifted backward, a curvature distribution concentrated on the middle portion thereof, and a portion contiguous with the trailing edge and cambered. The drag coefficient of the airfoil section is small when the Mach number is about 0.6 and the lift coefficient is about 0.6, and the airfoil section has a large maximum lift coefficient and a large zero-lift drag divergence Mach number, and generates a small pitching moment.

Abstract: A cast and hot isostatically pressed gamma titanium aluminide turbine blade has an aerofoil portion including a concave pressure surface and a convex suction surface. The concave pressure surface has surface irregularities, produced by the action of the hot isostatic pressing process on voids located within the cast turbine blade, located in that region of the concave pressure surface where in operation aerodynamic separation occurs to minimise the aerodynamic effects of the surface irregularities upon the operation of the turbine blade. The remaining portion of the concave pressure surface and the whole of the convex suction surface are substantially free of surface irregularities.

Abstract: An actuator for actuating a valve from a first position to a second position includes a housing and a rotatable stem mounted within the housing and restricted from moving axially. The actuator also includes a non-rotatable plunger engaging the stem such that the plunger moves axially in response to rotation of the stem, whereby the valve is actuated from the first position to the second position. The actuator is also provided with a non-rotatable indicator member, which is mounted within the housing and through which the stem extends. The indicator member engages the stem such that the indicator member moves axially in response to rotation of the stem. A viewing window is formed in a wall of the housing such that the indicator member can be seen through the window for indicating the first position and the second position of the valve.

Abstract: A method and apparatus are disclosed for controlling the rotational speed of gas and steam turbines, and hot gas expanders, with each of these drivers driving a rotational load by way of a shaft. To accomplish this control technique, it is necessary to easily and accurately calculate the amount of power which must be shed by the driver(s) to maintain a constant speed, i.e., neither accelerating nor decelerating. Action must be taken to reduce the power applied to the shaft by this amount. The method incorporates an open-loop approach and uses a time derivative to moderate the open-loop action accordingly.

Abstract: A pump drive apparatus comprises a housing (1) that accommodates a shaft (2) and a pump impeller (3). Both rotate around the same axis (4). The impeller rotates against the housing on at least one bearing (5). There is an eccentric journal (6) on the end of the shaft inside the impeller. The journal rotates in an orbital journal bearing (7). The orbital journal bearing moves in a circle within an eccentric bearing 14 on the impeller, driving the impeller. The orbital bearing tightly encloses the journal. A flexible component (9) prevents the orbital bearing from rotating in, and seals it off from, the housing.

Abstract: A three way switching controller (1) for handling high purity gas, and the like, used for a semiconductor manufacturing plant, and the like, prevents lines on switching sides thereof from communicating with each other at time of switching. The three way switching controller includes a body (2), first and second valves (3 and 4), a cylinder (5), and a linking mechanism (6), with the linking mechanism including a disengagement device (7). The cylinder, operating through the linking mechanism, alternately opens and closes normally-closed valves. The disengagement device prevents a driving force of the cylinder from being applied at once to the valves upon initiation of operation of the cylinder, thereby allowing both of the valves to be in a free state (closed state).

Abstract: A drainage pump 1 comprises a pump housing 40 defining a suction inlet 42, a pumping chamber 44 and a delivery outlet 46, and a cover 32. An impeller 50 accommodated in the pump housing is driven by a motor 10. The impeller 50 comprises a shaft 52 coupled to an output shaft of the motor 10, large-radius vanes 60 in form of flat plates radially extending from the shaft 52, and small-radius vanes 54 continuous from the large-radius vanes 60. Outer circumferential edges of the large-radius vanes 60 are connected by a cylindrical wall member 64, and outer circumferential parts of lower edges of the large-radius vanes 60 are connected by an annular member 62. The cylindrical wall member 64 has a rounded portion 70 at its upper end, and the small-radius vanes 54 also have rounded portions 57 at their lower ends.

Abstract: A centrifugal pump of the type adapted to pump high consistency fiber suspensions includes impeller vanes having portions which are immediately adjacent the fiber suspension in the interior of a vessel from which the suspension is to be pumped. The pump additionally includes a sideplate which is mounted directly to the vessel containing the fiber suspension so as to permit the impeller of the pump-to be brought in close proximity to the fiber suspension in the vessel. The sideplate additionally includes elongated portions that extend along the outer contour of the vanes of the impeller to determine the directions from which fiber suspension enters the impeller of the pump.

Abstract: A diffuser apparatus for use in connection with gas turbines which will markedly increase the fuel efficiency of the turbine. The apparatus is specially designed for use with a gas turbine having both inner and outer walls on which a boundary layer develops and can become detached. The apparatus includes a strategically located capture scoop for capturing a portion of the high velocity gas stream of the gas turbine in the area of maximum velocity and redirecting it through a plurality of spaced-apart injector slots provided in both the inner and outer walls of a shroud which is positioned relative to the turbine in a manner to capture the high velocity gas stream generated by the blades of the turbine.

Abstract: A tank venting system includes first and second tank valves and a valve for controlling venting from valves to vapor recovery canister. The valve includes a housing containing a first valve assembly for controlling venting of the first tank valve and a second valve assembly for controlling venting of the second tank valve. A vent conduit defines a bleed passageway for dissipating pressurized fuel vapor in a housing flow tube to a filler neck through a signal port and a passageway. A tube includes a vacuum-relief passageway and a valve for regulating flow of ambient air from the signal passageway into the housing when a cap is off the filler neck.

Abstract: Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas turbine engine. For example, a flow of cooling air is directed to a plurality of airfoils having a leading edge and includes a cooling path therein each of the plurality of blades in which is positioned a device which causes the cooling air to swirl and more effectively absorb heat and cool the leading edge of the airfoil.

Abstract: A valve plate in the form of a sheet metal preform is disclosed for a thermostatic valve. The preform includes an edge with a surrounding ring groove accommodating a rectangular cross section sealing ring. An exterior wall defining the ring groove is bent inward penetrating into the sealing ring to securely hold it in place.

Abstract: An axisymmetric elastomeric bearing assembly (30) for an articulated rotor hub assembly (10), which axisymmetric elastomeric bearing assembly (30) is disposed in combination with a rotor assembly yoke (24) and hub retention member (12) of the rotor hub assembly (10) and is operative for accommodating the multi-directional displacement of a rotor blade assembly (14) thereof. The axisymmetric elastomeric bearing assembly (30) includes a central bearing element (32) having a spherical bearing surface (32s) defining a bearing focal point (30f) and spherical elastomeric elements (34) bonded to the spherical bearing surface (32s) on opposing sides of the bearing focal point (30f). Each of the spherical elastomeric elements (34) have a plurality of alternating layers of elastomer and nonresilient shims (36, 38) which have a center of curvature which is coincident with the bearing focal point (30f) and disposed at increasing radii therefrom.

Abstract: A flap-type pressure relief valve includes a frame defining a flow opening therethrough with a flexible flap valve element positioned adjacent the frame to overlie the opening and allow fluid flow in a first direction through the opening while preventing flow in the opposite direction. A retainer assembly for joining a peripheral edge portion of the flap valve element to the frame comprises an elongated retainer bar integrally joined to the frame at one edge and connected to the frame at the other edge along a side of the flow opening in overlying relationship to a peripheral edge of the flap valve element. The retainer bar has a retainer surface spaced from the frame a distance slightly greater than the thickness of the flap valve element. Retainer pins extend from the frame through openings in the flap valve element. The assembly thus supports the flap valve element in a freely floating manner without forming air leakage openings.