Abstract: The need for a separate seal spring and sealing boot in an automotive water pump seal is eliminated by molding a flexible seal face mount integrally with the impeller.

Abstract: Apparatus and method for extending the thermal fatigue life and/or improving the performance of radial-flow turbine wheels in gas turbine engines by providing a thickened reinforcing pad on the wheel backface and cooling air passages in the surrounding case structure to direct high velocity cooling air onto the pad.

Abstract: A submersible pump having a plastic housing and adapted to accommodate multiple pump stages. The housing includes a pair of housing halves which enclose the impeller cartridges of the pump and an adjustment cone to retain the impeller cartridges for proper operation. Different length housings to accommodate a varying number of impeller stages are manufactured from the same mold utilizing removable inserts to vary the length of the mold. Accordingly, substantially integral housing halves can be formed at a substantial reduction in cost.

Abstract: A fast axial flow gas laser apparatus comprising an at least essentially closed loop defining a flow path for a laser gas, an arrangement for exciting gas flowing in the loop of the apparatus to cause the gas to lase, and a regenerative compressor for flowing gas through the closed loop along the flow path. The compressor is capable of operating with a pressure ratio sufficient to flow the gas along at least a portion of the loop at a speed at least half the speed of sound in the gas with inlet pressures of only a small fraction of an atmosphere. The uniform discharge pressure of the compressor results in a uniform laser discharge or output. A positive pressure fluid pressure seal prevents lubricant at a bearing support for the impeller shaft of the compressor from moving to the impeller and possibly contaminating the laser gas being compressed thereby and also prevents surrounding air from contaminating the laser gas.

Abstract: A propeller blade assembly which enables the mounting of a propeller blade in a hub assembly includes a bearing arrangement that circumferentially surrounds and engages with a section of the propeller blade. The bearing arrangement comprises an inner race assembly of angular contact bearings, and an outer race assembly of roller bearings. The roller bearings being arranged so that the axis of rotation thereof is substantially parallel to the longitudinal axis of the propeller blade.

Abstract: A single crystal turbine blade has a portion of its attachment section layered with a fine grained, poly-crystalline alloy. The blade is prepared by casting a single crystal body with an undersized attachment section, and then layering the attachment section with the poly-crystalline superalloy to form a composite structure. Layering is preferably accomplished by plasma spraying the body with the superalloy, and hot isostatically compacting the sprayed superalloy to minimize porosity. The composite structure is then heat treated to develop an optimized microstructure in the dual alloy attachment section. The polycrystalline material in the attachment section may be machined to a firtree shape for mounting in a turbine wheel. The resulting turbine blade has improved life resulting from reduced low cycle, low temperature fatigue susceptibility of, and crack growth in, the composite attachment section.

Abstract: An aerofoil balde rotor assembly in which a plurality of aerofoil blades having circumferentially extending platforms are located on the periphery of a rotatable disc. Each of the platforms is provided with tracks on its radially inner surface. The tracks of adjacent platforms define a convergent seating for a ceramic spherical damping member. Each spherical damping member frictionally engages the tracks of adjacent platforms simultaneously upon rotation of the assembly so as to provide aerofoil damping.

Abstract: An engine fan mount is provided which isolates the fan from vibrations causing pitch and yaw of the fan drive shaft. Each fan bolt is provided with a spacer extending through the fan, which metal washers at each end of the spacer on either side of the fan. Elastomeric washer are positioned about the spacer on either side of the fan between the fan and the metal washers. A slight clearance, e.g., 1 mm, is provided between the fan through bore and the spacer. When the bolt is tightened, the elastomeric washers are only slightly compressed, with the metal washers and spacers preventing further compression. The fan is free to float axially along the spacers, and to vary in angle (within the limits of the clearance) relative to the bolts and drive shaft.

Abstract: A runner type wind turbine designed to utilize maximum of the available energy carried by low speed stream. This turbine has a turbine disc which deflects and discharges a wind stream in radial and parallel direction relative to the disc; a rotor construction permits the disc and its power shaft to be arranged and assembled in a vertical or a horizontal position. The turbine includes a disc, mounted on a shaft located in central guides affixed to an outer stationary turbine stand. The disc mounts a plurality air blade shaped in such a way that the incoming air impinges on the blades radially, circumferentially and outwardly relative to the turbine disc.

Abstract: A blade attachment between a propfan blade and a propfan hub in a propfan propulsion system for a tube-launched expendable aircraft, the attachment including a hinger on a rotatable propfan hub on the aircraft, a stem of the propfan blade rotatably supported on the hinge, a pitch control arm rigidly attached to the propfan blade, and a pitch control link universally articulated at opposite ends to the pitch control arm and to the propfan hub. When the hinge is extended, the pitch control arm and pitch control link locate the propfan blade in a folded position generally flat against the fuselage of the aircraft for storage in and launch from a tube. After launch, the hinge rotates to a retracted position and the pitch control arm and pitch control link concurrently rotate the propfan blade to an unfolded position for propelling the aircraft forward when the propfan hub rotates.

Abstract: An axial flow ring fan has improved efficiency and reduced noise by making the leading edge of each blade a generally sinusoidal shape and projecting this geometry throughout the blade by imparting fall off to each blade.

Abstract: A rotary turbine fluid pump employs unique configurations of turbine vane receptacle opening and turbine vanes. The turbine vane receptacle is connected to a circumferentially extending fluid path, in which free ends of turbine vanes are inserted for pressurization of the fluid therein. The turbine vane receptacle operation has pair of surfaces opposing and spaced apart to each other. Each surface is radially tapered toward the center at a first inclination rate. Each turbine vane is provided edges opposing the surfaces of the turbine vane receptacle operation. The edges are correspondingly tapered at a second rate which is determined so that the spacing between the surface and the edge is gradually increased toward the rotation center of the turbine. This construction minimizes friction increasing when the pressure balance in floating seal formed between the surface and the edge is destroyed.

Abstract: The invention relates to a rotor head having interblade ties with resilient return in lag and with built-in damping, wherein each tie is connected, to each of the two rotor blades joined by it, by articulation means comprising a main ball retained on a member connecting a blade to the hub and centered on or in immediate proximity to the pitch change axis of the corresponding blade.A single main ball may be connected to the adjacent ends of two neighboring ties by a connection member having the shape of a V open towards the hub, or else each tie is connected to a connection member by a respective one of two main balls offset transversely in relation to the pitch change axis of the blade and/or radially along said axis.Application to the main and/or auxiliary rotors of helicopters.

Abstract: A runner is provided which consists of a radial turbine ceramic rotor with an integrated ceramic shaft and a non-ceramic compressor impeller which are connected by a releasable, thermally and mechanically loadable mechanical coupling in such a way that the releasable mechanical coupling is located with the compressor impeller. This coupling consists of a cylindrical slotted sleeve which, on the one hand, is fitted into a cylindrical fitting bore in the compressor impeller and, on the other hand, accepts the end of the ceramic shaft in a fitting bore. In addition, the coupling has a tie rod with a screw thread and a pair of conical clamping elements between the cylindrical sleeve and the compressor impeller.

Abstract: An apparatus and method is provided for locking side entry blades, in a rotor, such as used in compressors, turbines and fans. The apparatus utilizes arcuate locking devices retained in a circumferential groove in the periphery of the rotor. Each locking device features a key which engages a keyway in the side of the blade root shank. Use of the locking devices does not require that the blades having abutting platforms.

Abstract: An apparatus for converting air flow into mechanical motion using a single variable direction airfoil movable within a vertical track. Change in vertical direction of the airfoil and associated angle of attack is self-determined within a pre-set range dependent on work requirement.

Abstract: A centrifugal fan, comprising a housing with axially directed inlet and radially directed outlet as well as a driven impeller with rearwardly curved fan blades, the impeller being pivoted in the housing, includes a housing with an octogonal outer and inner cross section and further includes a sheet-metal deflector in the neighbourhood of the radial outlet, the deflector extending from one front wall to the other one and leading from the back edge of the outlet with respect to the rotational direction of the impeller radially inwards to the neighbourhood of the circumference of the impeller and from there outwards to the housing wall in a spiral-like curve. In a particular embodiment the impeller is displaced by a certain amount with respect to the center of the housing.

Abstract: A pitch feathering system for a gas turbine driven aircraft propeller having multiple variable pitch blades utilizes a counter-weight linked to the blades. The weight is constrained to move, when effecting a pitch change, only in a radial plane and about an axis which rotates about the propeller axis. The system includes a linkage allowing the weight to move through a larger angle than the associated pitch change of the blade.

Abstract: This invention relates to a section for shrouded propeller blade, of which the relative thickness is included between 9% and 15%, wherein, the curvature of said section having a maximum value at the leading edge thereof, the upper surface line comprises three successive portions, such thatin the first portion, the curvature decreases rapidly from said maximum value at the leading edge to a value close to 20 at a first point of which the reduced abscissa is close to 1%;in the second portion, the curvature decreases more slowly from said value close to 20 at said first point up to a value close to 1 at a second point, of which the reduced abscissa is close to 25%; andin the third portion, the curvature is less than 1 between said second point and said trailing edge.

Abstract: A collapsible fan is disclosed which can be easily stored, include logos and messages, and unfolds into a fan that is about six times its folded size. The fan includes a spring-type frame foldable into itself and unfoldable to its original shape, and a membrane connected across the spring frame. A carrying case has an opening in one portion for receiving the collapsed spring frame and membrane.