Abstract: The mixing apparatus has a plurality of pump impellers having one common axis and extending parallel to each other. Immediately adjacent pump impellers have opposite directions of rotation. The blading of the pump impellers is such that the currents of the mediums exiting the pump impellers have an as large as possible peripheral component. The medium currents exiting the adjacent pump impellers and having opposite senses of rotation are guided together and generate at the mutual point of contact an extremely high turbulence because the peripheral components of the exiting rotating currents of the mediums are directed oppositely to each other and eliminate each other practically immediately.

Abstract: A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.

Abstract: The water pump impeller comprises a boss with a disk part shaped thereon and a circular or paraboloid transition region is provided between the boss and the disk part. A metal reinforcing disk is embedded round on either side by injection moulding in the disk part, including the transition region. The reinforcing disk has as a component of the boss, a boss part with which it can be mounted on a drive shaft.

Abstract: A fan blade in which a leading edge piece made of a hard sintered product is attached to the leading edge of a fan blade main body over along substantially 3/4 to 1/4 from the tip thereof so that a useful life of the fan blade is prolonged.

Abstract: An elastomeric-covered shrouded impeller having a pair of disk-like shrouds enclosing vanes and vane passages which has an improved throat opening having sweeping internal sidewalls is disclosed. A three-piece mold core is utilized to form the vane passage and the sweeping curved throat inlet of the impeller.

Abstract: An improved propeller blade for use in an environment subjecting the blade to particulate impacts tending to erode the dynamic profile of the blade, and which is carried by a rotatable hub and extends radially therefrom, whereby the blade bends in cantilever fashion and twists axially of its length during operation. The blade may be either of the aluminum alloy type or of a resinous molded matrix type with reinforcing inclusions, and is cut away along its leading edge to accommodate therein a plurality of serially aligned but separate erosion resistant implants. The implants are formed of a silicon based ceramic material and are externally shaped to complement in profile continuity the prescribed efficient dynamic profile of the blade, and there is employed a novel system for restraining the implants against dislodgements during operation of the propeller.

Abstract: There are disclosed a blade for use as part of an axial flow fan and a method of forming such a blade wherein a large concentration of silica particles are molded into the leading edge of a hollow, one-piece molded body which includes a core of reinforced, thermosetting resin having relatively low abrasion resistance.

Abstract: A fairing formed from a dihedron of which the faces, disposed in the extension of the intrados and extrados surfaces follow the aerodynamic profile of the blade. Such rejoin the blade at a small radius portion constituting a leading edge. The fairing imparts a characteristic enabling the optimum efficiency of the fan to be approached. The useful height of the dihedron is at least 5% of the height of the blade.

Abstract: The invention relates to the smooth coating with a lyophilic (non-welling) material the passive surfaces of elements moving through or having contact with a fluid medium, such as, water, oil or the like. In one embodiment the under surfaces of the pistons, outer surfaces of the connecting rods and the crank shaft of an internal combustion engine are coated with polytetrafluoroethylene or the like which is lyophilic to the lubricating oil to which it comes in contact. Other embodiments employ lyophilic smooth coatings for ship rudders and outboard lower end units.

Abstract: A high strength, lightweight, heat resistant control surface for a high speed aircraft such as a missile or the like, comprises a heat resistant lightweight composite such as a graphite reinforced polyimide having a leading edge portion comprising a heat resistant metal such as Inconel. The leading edge portion includes a web fixing the leading edge portion to the composite by bonded attachment thereto at a location remote from the leading edge and adjacent surfaces thereby providing delayed exposure of the bond to leading edge heat buildup during flight.

Abstract: A ceramic coated abrasion resistant member and method of making are described in which a plurality of thin plates of polycrystalline ceramic material of small size, for example, a square plate measuring 1.0 inch by 1.0 inch having a thickness less than 0.200 inch are bonded to a thicker substrate base member with a uniform layer of organic adhesive bonding material. The bonding material includes a thermosetting organic plastic adhesive and a coupling agent which forms covalent chemical bonds with the ceramic plates, base member and plastic adhesive. An organosilane, such as .gamma.-aminopropyl trimethoxy silane, may be used as the coupling agent. The ceramic material may be selected from the group consisting of aluminum oxide, zirconium oxide, silicon carbide, silicon nitride, and spinel ceramic materials. The substrate member is preferably metal, such as steel and the plastic adhesive may be an epoxy resin.

Abstract: A replaceable tip for an aircraft leading edge and which has a metallic abrasion shield glove removably mounted to the leading edge of the aircraft, fasteners for securing the abrasion shield glove to the leading edge of the aircraft, and a non-metallic resilient cushion insert fixedly attached to the abrasion shield glove so that the resilient cushion insert forms a dampening arrangement which reduces the amount of damage to the aircraft leading edge when the replaceable leading edge tip is hit.

Abstract: A hollow prop-fan aerofoil blade is covered by a woven containment sheath which is bonded to the aerofoil surface of the blade and operationally anchored to the blade root. The sheath is arranged to be of sufficient strength to contain any of the aerofoil cross-section portion of the blade in the event of any structural failure thereof.

Abstract: An improved blade tip with an abrasive coating is disclosed. The blade tip is included in a rotor blade which is rotatable with respect to a stationary surface. The tip has a contour which is effective for producing a normal loading component on the coating if the tip contacts the surface while rotating. In a specific form of the present invention, the tip comprises an end wall extending radially outwardly from the perimeter of the outer end of the rotor blade and a concave surface bounded by the end walls and extending radially inwardly therefrom.

Abstract: The present invention is a flexible fairing for covering rotor connections on a rotor wing aircraft. Such a fairing would comprise a flexible polyurethane foam material which could maintain its aerodynamic shape while in flight yet be compliant enough to allow for changes in blade pitch without adding significant torsional stiffness to the connector. In addition, a flexible urethane rubber coating may be used to protect the foam fairing for abrasion or moisture absorption.

Abstract: An armoring system for use with an airfoil centrifugal fan for preventing erosion of the airfoil blades of the fan. The armoring system comprises an armor shield adapted to be releasably secured to at least a portion of the upper surface of the fan blades to prevent erosion thereof. The armoring system further includes mounting means cooperating with the armor shield for releasably securing the armor shield to the blades. The mounting means are positionable within the hollow space formed by the upper and lower surfaces of the blades to structurally reinforce the blades without altering their aerodynamic shape.

Abstract: The inlet and/or outlet edge of a blank which is to be converted into the vane of an impeller for use in a centrifugal pump is reinforced by providing an exposed surface of the blank with a pair of contiguous recesses which extend along the edge and the deeper of which is immediately adjacent to the edge. The recesses are then filled with metallic armoring material by cladding so that some of the surplus extends beyond the recesses and/or beyond the edge. In the next step, the surplus of armoring material is removed by one or more material removing tools, together with a portion of the blank in the region of the edge so that the exposed surface is provided with a fresh edge which is defined by the armoring material.

Abstract: A reactor for gasifying solid fuels, particularly coal, comprises with the fixed bed of fuel at least one stirring arm, which is rotatable about a vertical axis and is approximately triangular in cross-section. The forward knife edge and the rear crushing edge of the stirring arm are provided with replaceable armoring. The armoring at the knife edge consists of a plurality of armoring elements (7), which are approximately V-shaped in cross-section and are arranged one beside the other so as to define an expansion joint. The armoring at the crushing edge consists also of a plurality of elements (10), which are mounted on the stirring arm so as to be movable at ambient temperature.

Abstract: In a centrifugal fan having radially directed fan blades, each having, in combination, a serrated surface forming in longitudinal cross-section a sawtooth configuration in the radial direction of the rotating blade with a wear resistant coating over a substantial area of the serrated surface.

Abstract: A centrifugal pump impeller, particularly for use in pumps for effecting forced circulation of contaminated fluids in the primary circuits of nuclear reactor plants, has an impeller body which is surrounded by a cylindrical wear ring. The wear ring has an exposed end face and a second end face which is adjacent to a circumferential shoulder of the impeller body. The second end face of the ring is formed with axially parallel bores or slots which extend toward but short of the first end face, and the shoulder has recesses which are aligned with the open ends of the adjacent bores or slots. The first end face of the ring is formed with markers in the form of notches which register with the corresponding bores or slots and allow for accurate positioning of a boring tool which is used to bore out the ring after a certain period of wear to facilitate its separation from the impeller body and replacement with a fresh wear ring.

Abstract: A highly wear-resistant impeller for centrifugal pumps of composite construction comprising a base and a cover plate formed of material which can be worked with relative ease and an insert sandwiched between said base and cover plate formed of high temperature and wear-resistant material.

Abstract: A replaceable tip cap for attachment to the end of a rotor blade. The tip cap includes a plurality of walls defining a compartment which, if desired, can be divided into a plurality of subcompartments. The tip cap can include inlet and outlet holes in walls thereof to permit fluid communication of a cooling fluid therethrough. Abrasive material can be attached with the radially outer wall of the tip cap.

Abstract: A tip cap for a rotor blade which includes at least one radially extending rib having an abrasive coating thereon for providing a close clearance seal between the rotor blade and the surrounding shroud and also for cleaning the shroud of deposits of material thereon. The tip cap can include a cooling arrangement therein comprising a plurality of cooling passages and a thermal barrier. A method is provided for replacing one tip cap with another and includes the steps of removing a tip cap, machining the end of the rotor blade flat, aligning the replacement tip cap and securing it with the rotor blade.

Abstract: A moving blade for use in a steam turbine has a turbine rotor carrying a multiplicity of radially outwardly extending moving blades, each moving blade being provided at its leading edge of the radially outer end thereof with an anti-erosion plate attached by welding. The turbine blade has thicknesswise protrusions formed on both surfaces thereof at a portion near the base of the anti-erosion plate where it is attached to the moving blade. Thanks to these thicknesswise protrusions, the moving blade has such a radial distribution of cross-sectional area that the cross-sectional area is greater at the portion where the thicknesswise protrusions are formed than at other portions which are adjacent to the above-mentioned portion of the moving blade in the radial direction. As a result, the stresses at the portion of the moving blade near the base of the anti-erosion plate are reduced.

Abstract: A centrifuge conveyor is provided with improved hard surfacing wherein unitary subassemblies of backing tiles and wear-resistant members are welded by the backing tile to the conveyor. A subassembly is made unitary by the interengagement of the wear-resistant member to an undercut groove in the backing tile and by bonding with a heat reactive adhesive or grout applied to the interengaging parts. Each fragile wear-resistant member is braced against deflection at its outer portion through its backing tile to the conveyor. The preferred embodiment employs a plurality of wear-resistant members per backing tile, each such member being accurately pressed to its intricate, interlocking shape from sintered tungsten carbide.

Abstract: A surface aerating rotor has an intake zone for circulating and aerating a liquid, and includes a supporting assembly, a driving shaft connected to the supporting assembly, fixed flow guidance devices disposed in the intake zone of the rotor, and a plurality of fluid throughput units. Each fluid throughput unit has a discharge opening, and includes a vane which has an adjustable discharge angle with respect to the radial direction, and at least one flow guide wall. At least some of the fluid throughput units include an extension member downstream of the discharge opening, a flow guide profile on the extension member, and a baffle downstream of the flow guide profile. Connecting pins join the fluid throughput units to the supporting assembly, for adjustment of the vane discharge angle within a predetermined range.

Abstract: A considerable increase of the life time of metallic members, particularly the blades of fans or turbines, which are exposed to air-borne abrasive particles is obtained by providing such members with a wear-resisting attachment comprising at least two wear-resisting layers consisting of materials having complementary relationships of the erosion caused by said abrasive particles to the impact angle of the particles, said attachment being applied to surface portions of the members to be protected.

Abstract: A slip-on shroud to protect the shank of a mixing paddle of an asphalt mixer. The shroud is disposed on the shank and is formed with a generally triangular cross-sectional area to protect the front of the shank while reducing the quantity of material used to form the shroud and is formed with a generally triangular opening to receive the shank. The shroud is also formed with flanges confronting the opening to retain the shroud on the shank while reducing the quantity of material required to hold the shroud on the shank.

Abstract: A fan impeller comprises a back plate, a front plate and a plurality of blades fixedly attached between the front plate and the back plate. Two bars are welded to the back of each blade and are bolted to the front and back plates. Each blade is a channel section member having a base and two sides, the base being normal to the planes of the front and back plates of the impeller, one side lying along the front plate and the other side lying along the back plate. The sides extend from the base in the direction of rotation of the impeller in use so that the inside of each channel section is presented to the airstream as the impeller rotates. The inside working surface of each blade may be hardened to a minimum hardness of Rockwell C55.

Abstract: An improved heat shield and thermal insulating arrangement for a hub 12 of a high temperature centrifugal fan includes a cover overlying thermal insulation 38, the cover including a circumferential portion comprising segments 42, 44, an end ring 52, and fasteners 54, 58 holding the cover to the hub and a locking collar 28, with the cover basically shielding the root portion 20 of the hub, and being remote from and unattached to the wheel plate 16.

Abstract: Damaged screw propellers are repaired by use of hollow, thin-walled envelopes, each envelope having surfaces corresponding in configuration to an outer portion of a screw propeller blade. Each envelope is located on a blade, and a workable material is interposed between the damaged blade portion and the hollow interior of the envelope. The workable material and the envelope become an integral part of the blade to substantially duplicate the original configuration of the blade.

Abstract: A refurbished turbine vane or blade. Used turbine vanes and blades are cleaned, annealed and in some cases slotted adjacent their ends, after which any cooling passages are welded closed and all cracks welded over, on both leading and trailing edges. The trailing edge, for a vane or blade having a short chord, is built up by welding along its full length with an alloy wire, after which any slots that were cut adjacent the ends are closed, also by welding. Then the worn surfaces of the vane or blade are built-up by a plasma spray process, using a metal powder with added silica, to a thickness as great as 30 to 40 thousandths of an inch. The built-up vane or blade is then sintered and thereafter surface finished to conform to the original contour of the component when new. Any cooling holes are finally recut, and the vane or blade polished as required and inspected.

Abstract: A method of fabricating a turbomachinery blade is provided whereby high stress levels associated with stripe mode resonance can be avoided. Once the nodal pattern for an objectionable stripe mode resonance condition of a metallic blade is determined by conventional means, a portion of the blade parent metal near the tip is replaced with a composite patch, the composite patch comprising elongated filaments embedded in a matrix material. The chordwise extent of the patch includes the nodal points at the objectionable stripe mode resonance condition and the filament orientation is chordwise to enhance chordwise stiffness.

Abstract: A fan blade having a breakaway leading edge positioned on the spar and shell that constitute the main structure of the blade, the leading edge being adapted to break away, in part at least, upon being struck by a large foreign object, with the shell providing an acceptable leading edge after the breakaway.

Abstract: A compressor rotor blade for a turbomachine is disclosed. Techniques for increasing the strength to weight ratio of the blade while maintaining adequate resistance to foreign object damage are developed. In one specific embodiment an all composite construction employs matrix materials of varied ductilities and yield strengths to improve the energy absorbing capabilities of the blade.

Abstract: A composite rotor blade for a turbomachine is disclosed. Concepts for maximizing the blade strength to weight ratio while maintaining adequate resistance to foreign object damage are developed. Techniques for maximizing the torsional rigidity of the structure are disclosed, and in one embodiment, a judicious yet effective placement of titanium sheet material on the pressure side of the blade is made.

Abstract: An elastomeric damping arrangement is constructed to provide a highly efficient damping of the vibrations of a vibration prone member, such as an airfoil, especially a helicopter rotor blade. The damping arrangement is applied directly on or to the vibration prone structural member in the region of dynamic deformation, as an integral component part of the structural member. At least one damping layer is covered by a protecting layer which merges smoothly into the surface of the vibration prone member. The damping layer is made of a viscoelastic material having a high internal damping action. The protecting or cover layer is made of high strength material having a high rigidity in the direction of the occurring damping force.

Abstract: A method of manufacturing a hydraulic torque converter impeller member and the product of such manufacture in which a hardened steel cylindrical bearing is assembled to a drawn hub portion of a generally annular sheet metal part to comprise a torque converter impeller comprising the steps of (1) semidrawing the part to include a partly drawn hub portion, (2) placing a hardened cylindrical bearing in a die mechanism, (3) assembling the generally annular part into the die mechanism with the hub portion engaged in the cylindrical bearing (4) drawing and extruding the hub by moving an object the size of the desired finished inside diameter of the hub through same whereby the hub is formed and forced against the bearing member with sufficient force to make a permanent connection between the hub and bearing, and (5) trimming the excess material from the outer end of the hub portion to conform same to the dimensions of the cylindrical bearing.

Abstract: An article such as a blade fabricated from a plurality of high-strength, reinforcing filaments embedded in a matrix material and characterized by a portion of the filaments oriented transverse to the blade longitudinal axis in a direction through the blade to enhance transverse shear strength. In one embodiment, a plurality of columnar filament cores are each wrapped with a filament sheet and bonded together laterally to form the blade primary structure. The orientation of the filaments within the sheet forms an angle with the core longitudinal axes such that at least a portion of the sheet filaments runs transverse to the blade from one aerodynamic surface to the other. In an alternative embodiment, a blade is formed of a plurality of bonded filament laminates accordian folded with the fold lines angled with respect to the longitudinal axes of the filaments, the distance between fold lines being equal to or greater than the blade thickness.

Abstract: A method for producing a generally bifurcated metal protective sheath for the edge of an aerodynamic blade comprising the steps of (1) providing a metal sheath mid-section element having a top and bottom surface, (2) covering the top and bottom surface with an aluminum bonding material, (3) laying up separate metal top and bottom sheath cover elements on each of the top and bottom surfaces of the mid-section element to cover and overhang the same, the aluminum bonding material having a solidus temperature lower than the solidus temperatures of the mid-section element and the top and bottom cover elements, and (4) subjecting the layup to heat and pressure in a die for a time sufficient to bring the temperature of the bonding material to a temperature which is below but within approximately 20.degree. F of its solidus temperature to solid state diffusion bond the mid-section and cover elements together without forming intermetallics.

Abstract: A laminated filament composite structure, such as an airfoil for use in an environment in which it is subjected to both foreign object impact and bending is provided with improved leading edge protection. At least one fine wire mesh layer is partially bonded within the composite structure along its neutral bending axis. A portion of the wire mesh layer extends beyond the neutral bending axis and partially around the leading edge where it is bonded to the outer periphery of the primary composite structure. The wire mesh is clad with a metal such as nickel to provide an improved leading edge protective device which is firmly anchored within the composite structure. The neutral bending axis anchoring tends to retain the leading edge protective device intact even after the delamination of the composite structure.

Abstract: A centrifugal separator having a rotating chamber with a material advancing structure within the chamber including a spirally shaped carrier vane arranged coaxially within the chamber and supported on a rotatable driving shaft driven in rotation at a speed different than the chamber with a spirally shaped wear plate supported on the vane having an outer edge radially outwardly of the vane with a mounting face extending radially alongside a radial face of the carrier vane and a mounting piece secured to the mounting face of the carrier vane with means securing the wear plate to the mounting piece such as bevelled radially facing circumferentially extending interlock surfaces between a channel of the wear plate and the mounting piece and a tangentially or circumferentially inserted locking element extending between the radial outer surface of the mounting piece or the carrier vane for carrying the wear plate so that it will not tilt on the carrier vane.