Abstract: A hollow propfan aerofoil blade is provided with grooves which extend between its root and tip portions. The grooves contain filaments which are enclosed within a resin matrix material and are anchored to the root and tip portions. The filaments are arranged to be of sufficient strength to contain any of aerofoil portion of the blade in the event of any structural failure thereof.

Abstract: An airfoil particularly suited for use in rotor blades of large wind-driven ower plants is formed in three modular sections including a nose or leading section, a spar section and a trailing section, each separately formed and subsequently assembled. In the method of the invention the spar section is formed in two separate mold units which are configured to form part of the upper and lower aerodynamic profile of the airfoil and the two spar section units are trimmed along a junction plane and then joined together at the junction plane to form the spar section of the airfoil.

Abstract: A single-piece plastic fan wheel for a radial fan comprises a hub, a blade ring having fan blades and an intermediate piece interconnecting the hub and the blade ring. The hub comprises an inner hub ring attachable to the drive shaft of a motor and an outer hub ring connected to the inner hub ring by a plurality of axially and radially extending resilient strips which serve to damp tangential vibrations emanating from the motor owing to pulsations in the torque output thereof.

Abstract: A fan apparatus including a fan spider having a hub portion and a plurality of outwardly extending arms, a plurality of fan blade assemblies, each fan blade assembly having a molded plastic blade with an attachment insert partially embedded within, the exposed portion of each attachment insert being rigidly attached to a corresponding one of the arms of the spider.

Abstract: A propeller blade made of an advanced composite of uniaxial fibers laminated in crossplies to take advantage of their high axial strength. The thinness and strength of the plies are exploited in assembling the plies at various orientations to produce propeller blades which respond to changing aerodynamic loads in the complex ways necessary to maintain an optimum shape.

Abstract: A propeller includes a rotatable hub with a plurality of sockets, blades with roots that fit in the sockets and a plurality of pitch blocks which fit between the blade root and the socket walls. Hubs with two, three, and four sockets are shown. The blades have no twist and are formed of molded, glass reinforced nylon. The pitch blocks are also nylon and different pairs of pitch blocks may be used to hold the blades at different angles. All nylon components are designed to minimize stress concentrations. The hubs although also of nylon have steel reinforcing plates within them which take the centripetal forces. These forces are transmitted through bolts to passage walls in the pitch blocks, and from the pitch blocks through interengaging teeth to the blade roots. A snap on, snap off aerodynamic spinner is also provided.

Abstract: A stirring device attached to the vertical shaft of a sand mill having an annular metal collar received on the shaft and a flat, plastic, circular disc extending radially beyond the collar for a stirrer member concentrically affixed to the radial surface of the collar. The stirrer member has an outer ring and a central hub which are joined by circumferentially spaced spokes.

Abstract: An adjustable pitch aircraft propeller has peripherally spaced composite blades each including an elongated core of expanded rigid foam material extending from a metal base member having a reduced neck portion and an outwardly projecting flange portion. A casing or skin of plastic resin impregnated fabric material surrounds the core of each blade and extends inwardly along the neck portion and also has a flange portion overlying the flange portion of the base member. The skin material overlying the neck portion of the base member is retained by a filament winding impregnated with plastic resin, and the blade is coupled to the propeller hub by an annular lip portion which projects inwardly and overlies the flange portion of the skin material. The foam core of each propeller blade has longitudinally extending slots, and strips of resin impregnated fabric material extend through the slots to form corresponding webs which connect the skin material forming oposite side of the propeller blade.

Abstract: The invention relates to an axial fan with blades that automatically adjust to the direction of rotation. The fan blades are mounted with freedom to swivel on the fan wheel and are limited in their swiveling motion by stops which are provided on the fan wheel. In order to reduce the manufacturing cost of such an axial fan, spokes, to which the fan blades are fastened by means of film hinges are mounted on the fan wheel. The fan wheel is made from a single piece of plastic.

Abstract: A pump inpeller and a method for its manufacture wherein the impeller is made of two different synthetic plastics using a co-injection molding process. One plastic, used to fabricate a core section of the impeller, is a rigid thermoplastic material. The other plastic, used to fabricate the vanes section, is a thermoplastic elastomer. The latter is injected after the rigid thermoplastic material.

Abstract: A stirring device attached to the vertical shaft of a sand mill having an annular metal collar received on the shaft and a flat, plastic, circular disc extending radially beyond the collar for a stirrer member concentrically affixed to the radial surface of the collar. The stirrer member has an outer ring and a central hub which are joined by circumferentially spaced spokes.

Abstract: A method of manufacturing boat parts submerged when in use comprises producing a metallic skeleton structure shaped for easiest production by conventional metal-forming methods, and covering this structure in a mold with an adhering layer or coating of a thermoplastic resin or a rubber-based vulcanizable substance. The inner walls of the mold have high finish and the desired streamlined outer shape of the finished product, such as a lower unit of a propulsion system, or a propeller and the like. The coating functionally neutralizes the technologically conditioned and generally not streamlined shapes of the skeleton structure and provides a protection of the skeleton structure against electroerosive corrosion.

Abstract: An inexpensive injection molded propeller for mounting on a drive shaft. The drive shaft is attached to the hub of the propeller by a chemical and thermal shrink fit and by deformation due to the rotational forces of the propeller thereby producing a positive locking hub on the drive shaft. The propeller may be used, not only for remote piloted missiles and aircraft, but can also be used with different types of boat inboard and outboard drives, vehicles and equipment requiring a propeller having a positive locking system for securing the propeller or the like to the drive shaft.

Abstract: The disclosure relates to a composite turbine wheel comprising a hub having a plurality of radially extending blades thereon. The hub and blades comprise a plurality of discrete axially spaced layers of radially extending carbon fibers and circumferentially extending carbon fibers. Hoop strength is given to the hub of the turbine wheel by the circumferentially oriented fibers and radial strength is given to the blades by the radially oriented fibers. Transmission of shear loads between the radial and circumferential fibers is minimized.

Abstract: A composite, single material, one-piece turbomachinery rotor constructed of fibers bonded in a matrix is disclosed together with a method of manufacture thereof.

Abstract: A method for making a helicopter rotor blade having a longitudinal axis and a monolithic spar comprising a longitudinally-extending counterweight, a root member attached to the counterweight, and a retention means retained by and projecting laterally from the root member. A plurality of longitudinally-extending fibers is assembled into a group and is wrapped around the retention member and brought back at least partially upon itself, and then the foregoing elements are bonded together to form a solid spar member. A longitudinally-extending spacer member and the spar member are placed between a top skin section and a bottom skin section, each of which skin sections extends laterally and has a leading edge and a trailing edge. The leading edges abut each other and the trailing edges are bonded to each other. Preferably the trailing portion of this blade is hollow and unsupported internally.

Abstract: The top portion of a composite (boron filament/aluminum matrix) blade which is useable in a fluid flow machine is made more resistant to impact energy by forming a cavity in the boron filament layer of the tip portion of each laminate (or ply) of the blade, then filling each cavity with a resin, and then bonding together the laminates with the resin-filled cavities therein.

Abstract: The neck portion of a rotor blade includes an annular, axially projecting segment integral with the neck and having side edges abutting corresponding segments of adjacent blades to form a segmented annular ring which cooperates with static structure to define an interstage annular seal. Each blade also includes an air dam extending laterally from each side of the root neck and extending radially between the blade platform and the annular seal segment. The air dams of adjacent blades also abut each other to define an annular seal which prevents the axial flow of air across the rotor stage under the blade platforms between the blade root necks. In a preferred embodiment thin strips of silicone rubber are used to seal any gaps between the abutting edges of adjacent blades.

Abstract: A method of making an inexpensive injection molded propeller for mounting on a drive shaft. The drive shaft is attached to the hub of the propeller by a chemical and thermal shrink fit and by deformation due to the rotational forces of the propeller thereby producing a positive locking hub on the drive shaft. The propeller may be used, not only for remote piloted missiles and aircraft, but can also be used with different types of boat inboard and outboard drives, vehicles and equipment requiring a propeller having a positive locking system for securing the propeller or the like to the drive shaft.

Abstract: The present rotor blade is constructed as a so-called monocoque or shell type blade for use in large fans and windmill rotors. For this purpose the blade is made of fiber reinforced synthetic material with a differnt orientation of the fibers in different sections of the blade. The transition between the blade proper and the connecting end of the blade is formed by a blade root section which has a connecting end of circular or elliptical cross-section and a wing facing end corresponding in cross-section to the blade cross-section. The blade root section has three zones. In the main leading edge zone including the leading edge and adjacent sides of the blade root section the reinforcing fibers extend in parallel to one another. The fibers also extend unidirectionally in a rear zone forming the trailing edge of the blade root section and in this trailing edge zone the fibers also extend in parallel to one another but at an angle relative to the fibers in the leading edge zone.

Abstract: An adjustable pitch aircraft propeller has peripherally spaced composite blades each including an elongated core of expanded rigid foam material extending from a metal base member having a reduced neck portion and an outwardly projecting flange portion. A casing or skin of plastic resin impregnated fabric material surrounds the core of each blade and extends inwardly along the neck portion and also has a flange portion overlying the flange portion of the base member. The skin material overlying the neck portion of the base member is retained by a filament winding impregnated with plastic resin, and the blade is coupled to the propeller hub by an annular lip portion which projects inwardly and overlies the flange portion of the skin material. The foam core of each propeller blade has longitudinally extending slots, and strips of resin impregnated fabric material extend through the slots to form corresponding webs which connect the skin material forming opposite side of the propeller blade.

Abstract: An engine cooling fan driven by an engine and located in a shroud extending from a radiator to the engine including a hub having a cylindrical rear end portion for mounting the fan on the engine, a plurality of blades provided on the hub and a ring fixedly provided on tip portions of the blades and extending in an axial direction so as to fully encircle the tips of the blades and forming a radial clearance between the shroud and the ring, the ring including a rear end portion positioned axially rearwardly of the cylindrical rear end of the shroud and extending radially outwardly of the shroud thereby restricting air flow from the rear side of the fan into the radial clearance formed between the shroud and the ring.

Abstract: A bendable and twistable element having a high level of tensile strength, while remaining flexible and bendable in respect of twisting is produced by individually forming in a mould unitary layers of resin impregnated cut lengths of a continuous member, with their ends located between resin impregnated layers of fabric, polymerizing the resin, locating a plurality of the unitary layers in a further mould with the interposition, between the superposed pairs of layers of fabric, of layers of glue, setting the glue by heating and compression to form rigid end members, injecting a viscous elastomer into the middle portion of the bundle of cut lengths of the several unitary layers and curing the elastomer. The elements have particular use for connecting helicopter rotor blades to a hub member.

Abstract: An integral composite airfoil and disc assembly for use in a turbomachine is provided wherein the assembly includes an airfoil portion having a plurality of axially adjacent first filaments extending in a first direction. The assembly further includes a hub portion having at least one second filament extending in a second direction and a matrix material dispersed between filaments of the first plurality and the second filament. The first and second filaments are disposed so as to extend in the direction of principal stress in the airfoil and disc portions respectively.

Abstract: A cooling fan assembly for a powered vehicle, preferably adapted for automotive use, and having a hub and a plurality of radial fan blades made integral therewith and of synthetic and resilient resin material, the assembly being characterized by the provision of externally knurled bushings and a spacer member, the bushings being coinserted in holes in the hub and the spacer member, the spacer member being fixed to the bushings at one end of the bushings and pressed to one side face of the hub.

Abstract: A molding process, resinous formulations for use in the process, and the resulting products are disclosed characterized in that the product comprises mainly a bulk or fill resinous body having a film or skin of a cross-linked polyester resin formed about the body. Even though the body has intricate curving surface contours, the film is smooth and free of surface tears and blemishes. The product is molded by first spraying formulated, dry particles of a partially cured polyester resin against a hot mold to cause the particles to fuse and flow and form a substantially continuous skin or film on the mold. Thereafter, the bulk resin is added and the mold is heated to cure the polyester resin as well as the bulk resin and to interreact the bulk and polyester resins together to mold the bulk resin with a film of the polyester resin.

Abstract: A turbofan engine fan blade made of composite material, and a method of making the fan, are taught. The fan blade essentially comprises an airfoil section having a root end and made of a plurality of bonded plies of composite material which are splayed and which are in a staggered condition at the root end; a two-piece platform section made of titanium or of aluminum, with one piece of the platform on each side of the airfoil section; and a steel outsert section which holds and secures the platform section to the airfoil section, with the outsert section having a triangular shaped cavity located at the root end of the airfoil section, between the splayed and staggered plies of the airfoil section. Among other advantages, the cavity eliminates the "insert plies" (or wedge) used in the prior art and the inherent disadvantages associated with such use.

Abstract: A fan assembly including a hub portion from which blades and a stem are extended respectively radially outwardly and radially inwardly, the hub portion, the blades and the stem being formed of molded plastics and made integral with each other. The stem is connected to an output shaft of fluid coupling by means of bolts each of which passes through a bushing. The bushing having knurling portion at outer surface thereof is inserted in the hole of the stem and the periphery of the hole is melted by heating upon insertion of the bushing therein so as to ensure the connection of the fan assembly to the output member. In case that a spacer is interposed between the stem and a flange of the bush, the spacer is fixedly connected to the bushing.

Abstract: In a rotor for a rotary wing aircraft, an integral central headpiece supps the rotor blades. The headpiece consists of two plates interconnected by a centrally arranged distance member. Each plate has a similar star-shape with at least four angularly spaced point-like arms. Each plate is formed of a number of superposed layers with each layer containing continuous loops extending in the direction of the point-like arms. At least one loop extends from one point-like arm into another diametrically opposite point-like arm. Others of the loops, located in the other point-like arms, extend radially outwardly from the loop extending through the two point-like arms. The headpiece consisting of the plates and distance member, is a unitary or integral structure.

Abstract: A helicopter rotor blade having a longitudinal axis and a monolithic spar comprising a longitudinally-extending counterweight, a root member attached to the counterweight, and a retention means retained by and projecting laterally from the root member. A plurality of longitudinally-extending fibers is assembled into a group and is wrapped around the retention member and brought back at least partially upon itself, and then the foregoing elements are bonded together to form a solid spar member. A longitudinally-extending spacer member and the spar member are placed between a top skin section and a bottom skin section, each of which skin sections extends laterally and has a leading edge and a trailing edge. The leading edges abut each other and the trailing edges are bonded to each other. Preferably the trailing portion of this blade is hollow and unsupported internally. A method of making this blade and its component part is also disclosed.

Abstract: A blade for a wind motor comprises a load-bearing structure and an external covering of plastic material. The load-bearing structure is of flat tubular form and is composed of a pair of facing half shells constituted by sheet metal pressings of substantially channel section. Flat-bottomed impressions are provided along the edges of the shells. The shells are joined together by spot welds welding the bottoms of the impressions of one shell to the bottoms of corresponding impressions of the other shell.

Abstract: An adjustable pitch aircraft propeller has peripherally spaced composite blades each including an elongated core of expanded rigid foam material extending from a metal base member having a reduced neck portion and an outwardly projecting flange portion. A casing or skin of plastic resin impregnated fabric material surrounds the core of each blade and extends inwardly along the neck portion and also has a flange portion overlying the flange portion of the base member. The skin material overlying the neck portion of the base member is retained by a filament winding impregnated with plastic resin, and the blade is coupled to the propeller hub by an annular lip portion which projects inwardly and overlies the flange portion of the skin material. The foam core of each propeller blade has longitudinally extending slots, and strips of resin impregnated fabric material extend through the slots to form corresponding webs which connect the skin material forming opposite side of the propeller blade.

Abstract: To prevent the generation of noise from axial oscillations of the fan wheel on electric machinery, especially motors and generators in motor vehicles, the fan wheel is composed of a support assembly consisting of a plurality of adjacent metal discs or rings, surrounded by a preferably molded plastic fan circle in which the fan blades are embedded. The component discs of the support assembly may be of different thickness to provide different natural resonant frequencies, thereby further suppressing axial oscillations.

Abstract: A machined-to-size superalloy turbine rotor disc for a gas turbine engine has its fatigue life increased by coating its fatigue-prone machined surfaces with an air-impervious protective layer of material which retains its integrity and adherence to the machined surfaces for a large number of mechanical and heat stress cycles.

Abstract: A wind motor blade of composite construction has a blade shell of plastics material reinforced internally by transverse ribs and intersecting longitudinal struts in which metal fork arms are embedded, the fork arms being connected to a metal root attachment spigot through a metal cross-piece encapsulated in the plastics material.

Abstract: A reverse flow, gas cooled dynamoelectric machine includes a rotor mounted fan at each machine end for circulating gas coolant throughout the machine. Improved pressure and efficiency for the fan is achieved by positioning stationary guide vanes upstream from the fan for directing gas coolant into the fan blades at an optimum angle. The invention is directed toward an improved guide vane assembly construction and composition.

Abstract: A fan blade has a protective beading on at least some of the edges thereof, the protective beading protecting against injuries while the fan is operating.

Abstract: Fan blade assembly and shaft mounting in which there is minimized axial face run out or wobble of the rotating fan by virtue of the fan taking a perpendicularity signal from a shaft mounted hub plate which divorces the squareness of the fan shaft opening from influencing the hub plate perpendicularity signal. The fan is mounted on the motor shaft by a nut and Belleville spring assembly to provide end play takeup by the load deflection characteristic of the Belleville spring.

Abstract: A fan for use as a front fan or in the lift fan system with aircraft jet engines having blades supported by a segmented hub platform and a segmented tip platform which are supported by hub support hoops and tip support hoops. The blades are secured to the hub platform segments and tip platform segments by composite pre-preg pin stock which is inserted in holes in the tip platform, the hub platform and fan blades. The pins are placed under axial compression to expand the pin diameter to provide a precise fit. Channel members are provided between the tip hoops and the blades. Some of the channels have extensions which form seals.

Abstract: A rotor driven for an axial flow gas turbine engine compressor is formed as a composite structure of inner and outer skins with a core therebetween and a set of tensile reinforcing rings each located in a respective groove of a corrugated outer surface of the drum. In the completed drum the drum body is preferably under compressive prestress while the reinforcing rings are under tensile prestress.

Abstract: A fluid coupling device and fan mounting arrangement is disclosed. The fan is of the type having a hub portion and a plurality of fan blades integrally molded therewith from a plastic material and an annular spider having its outer periphery attached to the hub portion and a plurality of inwardly extending tabs bolted to bolt bosses projecting forwardly from the front surface of the output coupling member. The bolt bosses define a bolt circle having a radius R.sub.1 and the output coupling member includes a plurality of pilot portions defining a pilot diameter of radius R.sub.2, wherein R.sub.2 is greater than R.sub.1. The annular spider includes a plurality of inwardly extending pilot tabs, each of which engages the outer periphery of one of the pilot portions of the output member.

Abstract: Foil, wire and similar coherent bodies of catalytic metal are provided with catalytically active surfaces by diffusing a chemically removable metal such as aluminum or zinc into those surfaces and then selectively dissolving out at least about a third of the removable metal. Platinum wire screens activated in this way make effective exhaust catalysts for automotive engines.

Abstract: A fan and motor assembly for an electric appliance, wherein the fan is comprised of a plastic material and has a mounting hole of a diameter greater than the shaft diameter of the motor. Insulating washers closely fitted in annular recesses at the end of the mounting hole have inner diameters substantially the same as that of the shaft for centering the fan on the shaft.

Abstract: A system of spars, each having a rectangular cross-section, is provided by placing the spars in lateral juxtaposition to one another like a plank to form a rotor blade. A skin of plastic foam is provided on the blade. The cross-sections of the spars, and the corresponding cross-sections of the blade, are varied in accordance with aerodynamic requirements. The spars are kept in position by means of clamps and/or connections and/or rings, forming an integral unit similar to a plank; and the integrated spars are directly attached to a hub or an electric generator.

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: A rotor blade system which is adaptd for long term reliable operation in a gas turbine engine is disclosed. Techniques incorporating composite materials into the rotor system are developed. One rotor structure shown utilizes a paired blade assembly having a core of continuous fibers running from the tip of one blade to the tip of the adjacent blade. Each of said paired blade assemblies is mchanically detachable from the engine rotor.

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: Foil, wire and similar coherent bodies of catalytic metal are provided with catalytically active surfaces by diffusing a chemically removable metal such as aluminum or zinc into those surfaces and then selectively dissolving out at least about a third of the removable metal. Platinum wire screens activated in this way make effective exhaust catalysts for automotive engines.