Abstract: The connection between the actuating link of each variably settable vane of a compressor flow straightener in a turbine plant and the control ring for the vanes comprises a cylindrical roller rotatably mounted in a bore in the ring parallel to the axis of the compressor, the roller having a radial bore registering with a radial opening in the ring and housing the shaft of the link as a rotary and sliding fit. This arrangement prevents any torsional strain on the link during operation, and is found to be substantially simpler and more reliable than the known arrangements.

Abstract: A pulp feeder feeds the pulp from the pulp feeder housing to the pump impeller. The impeller is provided with vanes specially constructed to provide channels of sufficient dimension to permit the flow of the pulp through the channels. The impeller also has helical flights for feeding the pulp to the channels. The end of the pulp feeder is spaced close enough to the impeller to feed the pulp to the impeller flights but far enough away from the impeller to not interfere with the removal of air. An air removal pipe may also be included in the pulp feeder housing.

Abstract: A flywheel rotary engine power plant comprises a flywheel having internal passages through which power fluid is conducted to impart rotation to the flywheel about an axis. The flywheel is mounted on a journaled shaft and the pressure fluid is conducted through the shaft and introduced into a central region of the flywheel. The passages extend generally radially outwardly from the center of the flywheel. Each passage comprises a straight entrance section which merges into a single turn helix section of approximately 315.degree. extent and the helix section in turn merges into a straight exit section which extends to the passage outlet at the perimeter of the flywheel. The exiting fluid is directed against a vaned casing surrounding the perimeter of the flywheel to add a jet-propulsion effect. The propulsive force is developed by the action of the fluid on the single turn helix chambers and the jet-propulsion effect.

Abstract: A pump for pumping fragile articles including fish and glasses without damage includes a rotary pump having a plain disc impeller disposed in a substantially cylindrical chamber of a housing with an inlet into, or coaxial of, the impeller into the housing and an outlet from the periphery of the chamber, with the rotor arranged to provide a substantially unobstructed passage between the inlet past the rotor to the outlet of the pump. The method includes pumping fragile articles in a fluid medium by means of a disc impeller pump having an unobstructed passageway between the inlet and outlet of the pump.

Abstract: A ceramic stator vane assembly for a gas turbine engine comprises a plurality of ceramic stator vane segments arranged in an annular array with each vane segment having integral concentric tip and root platform members. The tip and root platform members define continuous inner and outer surfaces for receiving inner and outer ceramic rings. Radial and axial housing members are provided for mounting the stator vane assembly within the engine, and thermal insulation means are provided between the ceramic vane assembly and the housing members.

Abstract: A molded fiber-filled polymer impeller having a polygon molded hole with machined grooves at the apexes of the polygon and a process for forming such grooves.

Abstract: Pump system includes a centrifugal pump having an inlet reservoir connected to the upstream end thereof for initially receiving the vapor/liquid mixture entering the system to allow air or vapor to separate from the liquid. Below the liquid level in the reservoir is a mixing tube which provides the only liquid flow path to the centrifugal pump. Also within the reservoir below the liquid level is a main ejector pump which injects liquid into the mixing tube. The injected liquid induces liquid flow from the reservoir into the mixing tube for flow to the centrifugal pump. Also, one or more vapor scavenge ejectors may be provided within the reservoir to induce air or vapor from selected collection areas within the reservoir and propel the air or vapor into the mixing tube intermediate its length where the air or vapor is thoroughly mixed with the liquid contained therein at an intermediate pressure higher than the reservoir pressure before entering the centrifugal pump.

Abstract: Judiciously dimensioned slots in feather seals between adjacent edges of platforms of segmented stator vane for a gas turbine power plant serves to allow the flow of cooling air through the slots notwithstanding the feather seal shifting.

Abstract: A method of selecting particular blades to be placed in particular slots involving an initial selection based on length and a final dedication based on weight.

Abstract: A frame-supported fan in which the mounting portions between the motor and the frame are formed in the shape of an arrowhead and/or are provided with sculptured edges extending to the frame or are provided with interfering bodies mounted to the outer ends of the edges of the frame, so as to reduce unwanted noise by producing non-uniform flow separation in the air stream through the fan.

Abstract: A turbine rotor including a turbine vane wheel made of ceramics, a ceramic shaft formed integrally with the turbine wheel, and a metallic shaft bonded to the ceramic shaft. The hardness of a part of or the whole part of a compressor wheel-fitting shaft portion of the metallic shaft is made smaller than that of a portion of metallic shaft apart from the compressor wheel-fitting shaft, said portion being located on the turbine vane wheel side. Thereby, slackening between the compressor wheel and the fitting shaft is avoided. Methods of producing the turbine rotor are also disclosed.

Abstract: The pump includes a stator and a rotor which describe an upper annular chamber having a filling mouth and a delivery mouth and a lower annular chamber in which is housed an annular cam to drive the pump blades housed in a vertically sliding manner in respective radial passages of the rotor. Into the lower chamber essentially in a position diametrically opposed to the filling mouth there opens an exhaust mouth which communicates with the upper chamber through an ample passage and with the zone of the lower chamber underlying the filling mouth through a narrow passage.

Abstract: A rotor stage disposed within an annular fluid flowpath in a turbomachine is disclosed. The rotor stage includes outer and inner rings and a plurality of first and second airfoils. The outer and inner rings define flowpath surfaces for said flowpath. The first and second airfoils extend between the rings for transferring energy between the fluid and the rotor stage. At least one of the first airfoils surrounds means for transmitting energy across the flowpath.

Abstract: A linkage (36) is provided for manipulating an internal component (32) of a turbofan gas turbine engine (10) in response to an externally mounted actuator (50). The linkage includes a radial torque shaft (38) supported between two spherical bearings (40, 42). The shaft (38) is slidable within the radially outer bearing (42) for accommodating relative radial movement in addition to relative axial and circumferential movement between the inner compressor case (26) and the outer fan duct (28).

Abstract: An impeller is provided that is adapted to be rotationally driven, and which is constructed of a resiliently stretchable elastomeric material, such that, with increased centrifugal force that is applied to the impeller vanes with increased rotation of the impeller, the impeller increases in diameter and provides increased output performance beyond the output performance of a non-stretchable impeller of the same general size as the impeller at rest.

Abstract: An air seal assembly 10 for a gas turbine engine comprising a full ring cover plate 20 and seal segment 14 attached to impingement boxes 18. The impingement boxes have counter mounted hooks 24, 26 that interlock with a turbine flange 22 and cover plate 20 to secure the seal assembly 10. Holes 36 in the impingement boxes 18 direct cooling air to the entire backside 38 of seal 14. Seals 14 are mounted to the impingement boxes 18 by pedestals 40 that are positioned to enhance seal flexibility since axial edges are unrestrained.

Abstract: A support system useful to interconnect interstage components in a centrifugal compressor. The system allows controlled balancing of pressure induced forces while accommodating thermal expansion and contraction. In one preferred form a support ring is mounted about a scroll volute but supported through tie rods from a conduit concentrically aligned with the volute. A second support ring is mounted about the conduit, facing but spaced from the first ring, and supported from the volute. The support rings are respectively sealed to the volute and conduit through O-rings which allow sliding axial motion. A grooved peripheral pipe coupling seals the space between the support rings. The surface area of the support rings can be selectively chosen to direct and control pressure forces within the compressor system.

Abstract: An improved vane platform feather seal is disclosed for use in turbine engines. This feather seal contains a flat, thin feather seal, which is attached by adhesive to ease assembly to an L-shaped retainer plate to result in a combined thickness of 0.032 inches. This new seal may be used to replace the inner vane platform seals which are currently used in F-100 turbine engines, which have a history of not bending easily to conform to seal slots. The new seal provides improved platform sealing without loss of platform retention in the event of vane burn through.

Abstract: A rotor-shaft assembly includes a ceramic solid hubbed turbine rotor having an integral stub shaft interference fit within one end of a generally cylindrically shaped sleeve member. The sleeve member defines a hub portion adapted to mate with a piston ring seal and a coaxial bore therethrough. The interference fit, which is defined by the change in the diameter of the bore, schedules the compressive forces acting on the stub shaft. A metal shaft is brazed within the other end of the sleeve member in a torque transmitting relationship.

Abstract: In a double flow section of a steam turbine, the inner web of the diaphragm surrounding the rotor shaft in the region of divergence of the steam flow paths, is fabricated in the form of two cylindrical shells which are held together either in a fixed position or in a relatively fixed position which permits some slight axial motion between the shells. This form of diaphragm eliminates a number of machining and fabrication alignment problems and additionally permits differential axial expansion of the two pieces occurring as a result of internal thermal steam conditions.