Abstract: A propeller for aircraft has a tip-to-tip flex-beam spar and torsionally stiff hollow blades bonded to the spar throughout an outer portion of the blades. The spar has two end caps which are separated from each other at the hub and converge in the outer portion. The blades have an inner region which is not bonded to the spar, allowing an inner portion of the spar to twist during pitch changes. A counterweight is mounted to an arm extending from an inner end cuff of each blade. The counterweight is located out of the plane of rotation. The counterweight is also located on a side of a line opposite from the trailing edge, the line passing through the pivot axis perpendicular to the plane of rotation.

Abstract: A windmill having a plurality of radially extending blades, each being an aerodynamic-shaped airfoil having a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge into the wind, and a trailing edge which has a flange doubled back toward the leading edge and an end cap. The blade is of substantial uniform thickness. An air compressor and generator are driven by the windmill. The compressor is connected to a storage tank which is connected to the intake of a second compressor.

Abstract: An assembly for a rotating composite inlet nose cone is reinforced or is repaired after having undergone delamination. The assembly strengthens the inlet nose cone and thus blacks delaminations of the inlet nose cone. In one particular embodiment, the assembly includes an outer ring that blacks delaminations in an undamaged rotating inlet nose cone. The outer ring has a higher stiffness to mass ratio than the adjacent portion of the inlet nose cone assembly. In one detailed embodiment, an inner ring is disposed inwardly of the adjacent portion of the inlet nose cone assembly. The inner ring in one detailed embodiment has a lower stiffness to mass ratio than the outer ring.

Abstract: Apparatus is provided for creating heat by electromagnetic induction between relatively rotating components. In RAT applications, part of the nose cone (34) is formed from electrically conductive material (106) which is in thermally conductive relation to the nose cone exterior. A magnetic field is created by components (60) that are spaced apart from the electrically conductive material and relatively rotatable with respect to that material. The electrically conductive material intersects the magnetic field, at least in part, such that eddy currents are created in the electrically conductive material by relative rotation with respect to the magnetic field. These eddy currents create heat which is conducted to the exterior surface of the RAT nose cone. Preferably, the magnetic field is created by a pair of spaced-apart permanent magnets (60) mounted on a support plate (62) inside the RAT hub (28) and immediately behind the nose cone.

Abstract: The present invention provides an apparatus for minimizing the blade opening between the blade shank of propeller and spinner in order to improve the overall efficiency of an aircraft and propeller system. The present invention consists of a two piece blade opening filler; the bulkhead insert which attaches to the bulkhead, and the spinner insert which maybe attached to bulkhead insert after installation of the propeller blade. The blade opening filler fills the blade opening between the spinner and blade shank while facilitating maintenance of the system.

Abstract: A nose cone on the fan of a gas turbine engine contains access holes that provide access to cap screws that hold the nose cone on the fan hub. The cap screws extend through an internal flange on the nose cone. A spring clip extends from the flange in a configuration that covers the access hole and holds the cap screw in the flange as the nose cone is installed.

Abstract: A centrifugal pump assembly including a housing containing a pump impeller having an axis of rotation with an inlet opening for fluids generally aligned with the axis of rotation of the impeller and a discharge opening aligned with the periphery of the impeller. The impeller is attached to a drive shaft for rotation by means of a central hub which has at least one circumferentially extending surface having an edge projecting toward the inlet at a circumference radially spaced from the axis of rotation. The surface, which is progressively recessed away from the inlet toward the rotational axis, modifies fluid flow through the pump to reduce whirling motion in the inlet, thereby significantly improving efficiency of the pump.

Abstract: A tail rotor for a rotary wing aircraft is located in a laterally directed duct located at the end of a tail cone extending rearward from the aircraft cabin and at the base of an empennage extending upward from the duct. The rotor includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, a rotating control shaft, a stationary control shaft, and an actuator connected to the stationary control shaft for moving the rotating control shaft axially. The rotor hub includes rotor arms each supporting a pitch shaft-blade spar assembly for pivotable movement about a pitch axis. A pitch beam supports flexures, each connected to a pitch arm offset laterally from the associated pitch axis. The flexures driveably connect the pitch arms to the pitch beam and transmit pitch control motion to the blades as the pitch beam moves along the rotor axis. Pitch bearings, on which the pitch shafts turn about the pitch axes, are supported on a rotor hub shell fixed to the rotor hub.

Abstract: A tail rotor for a rotary wing aircraft is located in a laterally directed duct located at the end of a tail cone extending rearward from the aircraft cabin and at the base of an empennage extending upward from the duct. The rotor includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, a rotating control shaft, a stationary control shaft, and an actuator connected to the stationary control shaft for moving the rotating control shaft axially. The rotor hub includes rotor arms each supporting a pitch shaft for pivotable movement about a pitch axis. Each pitch shaft is adapted to support a rotor blade so that its angle of attack changes with movement of the pitch shafts. A pitch beam, located adjacent the rotor hub, supports flexure members, each connected to a pitch shaft eccentric of its pitch axis.

Abstract: A fan for a ducted fan gas turbine engine comprises a hub carrying an array of generally radially extending fan blades. The hub is hollow and tapered in an axial direction. The radially outer hub surface is provided with a plurality of generally axially extending slots. The slots receive corresponding stepped teeth provided on the radially inner ends of the fan blades. A nose cone engages the upstream end of the roots of the fan blades to ensure that the teeth are retained in the slots.

Abstract: An apparatus and method for the disassembly of an ultra high bypass turbine engine having an outer engine portion and an inner engine portion. A plurality of fan blades and acoustic panels are removed from the inner portion of the engine. The outer portion of the engine which includes a plurality of fan outlet guide vanes and fan casing are disconnected from the engine and axially removed. Certain outer portions of the engine including a hinged thrust reverser and hinged fan cowling may be coupled to an aircraft pylon and used interchangeably with replacement engines.

Abstract: A hybrid metal/composite spinner cone used in aircraft applications and a method of manufacturing the same. The spinner cone has a metal outer shell which is bonded during the molding process to an inner structural member of thermoplastic composite. The metal shell imparts several desirable characteristics to the spinner cone such as impact resistance, erosion resistance, appearance, and supplying a lightning strike material to protect the composite structure. The thermoplastic composite has significant property advantages over metal or thermoset systems. The hybrid metal/composite spinner cone is manufactured using a ceramic mold which is less expensive and more readily available than a steel mold. The metal shell provides a barrier between the thermoplastic composite and the ceramic mold and allows the finished spinner cone to be easily released from the mold.

Abstract: To control unsteady motion phenomena in turbomachines, it has been proposed to employ an active control system to modify the flow conditions. In the present invention, the modification is effected by devices mounted in a bullet or nose bullet at the entry to a rotor of the turbomachine.

Abstract: A ducted fan gas turbine engine spinner is so configured so as to be generally outwardly flared at its downstream end. The flared portion provides a decrease in the local axial velocity of the air flow over the spinner. This in turn leads to the reduction or elimination of choking in the radially inner region of the fan of the engine.

Abstract: A fan wheel has a cup shaped hub having an outer cup wall with a plurality of vanes and a cup bottom connectable with a shaft of a drive and provided at its inner side with a plurality of ribs defining a plurality of fields therebetween. The cup bottom in the region of the fields has a plurality of depressions extending from its inner side and having a width approximately 70% of a thickness of the cup bottom.

Abstract: A gas turbine engine has a forward rotor, a row of fan blades radially extending from the rotor, and a core turbine engine located rearwardly of the fan blades and rotor and coupled to the rotor for rotatably driving the rotor. An outer annular nacelle surrounds the rotor, fan blades and core engine. An inner annular splitter fairing is disposed rearwardly of the fan blades, surrounds the core engine, and is spaced radially inwardly from the nacelle so as to define therebetween a bypass air flow duct located outwardly from the core engine and rearwardly of the fan blades for producing thrust upon rotation of the rotor and fan blades. A hybrid shape spinner nose is attached about the rotor and projects forwardly therefrom within the nacelle and forwardly of the fan blades.

Abstract: A hybrid metal/composite spinner cone used in aircraft applications. The spinner cone has a metal outer shell which is bonded during the molding process to an inner structural member of thermoplastic composite. The metal shell imparts several desirable characteristics to the spinner cone such as impact resistance, erosion resistance, appearance, and supplying a lightning strike material to protect the composite structure. The thermoplastic composite has significant property advantages over metal or thermoset systems. The hybrid metal/composite spinner cone is manufactured using a ceramic mold which is less expensive and more readily available than a steel mold. The metal shell provides a barrier between the thermoplastic composite and the ceramic mold and allows the finished spinner cone to be easily released from the mold.

Abstract: A polyester composite propeller spinner (1) has a conical wall (2), radial internal support gussets (3), and means for attaching to a propeller hub. Improved impact strength is achieved by combining a vinyl terminated liquid reactive compound with a polyester resin and adding a plurality of fiberglass fibers. The fiberglass fibers are in at least two fiber lengths, having a 2:1 ratio of long to short fibers. A propeller spinner formed from such a composition has an impact strength of greater than 4.84 Kg-m (35 ft-lbs) .

Abstract: A nose cowl or spinner is provided for a fixed, non-rotatable central hub of a turbojet engine having assembly means that facilitate the attachment and detachment of the nose cowl to the central hub, and provides a readily visible indication of whether or not the nose cowl has been properly assembled to the hub. The nose cowl has a smooth outer surface to provide undisturbed air flow into the turbojet engine compressor and defines means to circulate heated air to prevent icing of the external surface. An inner cowl member is attached to a bearing cover of the central hub in a non-rotatable manner, an outer cowl member is axially locked to the central hub so as to be concentrally arranged about the inner cowl member, and a locking device is used to lock the inner and outer cowl members together to prevent inadvertent rotation of the outer cowl member.

Abstract: The invention provides improvements to aerial propellers, particularly for aircraft propulsive units, wherein the cowling of the propeller is defined by a meridian line having: at its origin (B) a maximum curvature greater than 15; then a curvature decreasing rapidly from the maximum value to a value of 7; then a curvature decreasing linearly from the value 7 to a value of 0; than a curvature decreasing more slowly from the value 0 to a minimum value between -3 and -5; then a curvature increasing rapidly from the minimum value to a value of 0.

Abstract: A propeller hub supports a plurality of adjustable pitch propeller blades which are rotated on corresponding radial axes by a hydraulic actuating system supported by the hub. The hub and pitch changing system are enclosed by a spinner assembly including a substantially flat circular bulkhead member having a core molded between skins of resin impregnated high modulus fiber material. The bulkhead member supports a spinner dome of molded resin impregnated high modulus fiber material, and concentric slip rings are supported by a member connected to the rearward face of the bulkhead member. Terminal posts extend from the slip rings through the bulkhead member to receive conductor wires for supplying electrical current to de-icing heating elements mounted on the blades. A fairing is bonded to the spinner dome for each blade to provide for optimum aerodynamic flow around the base portion of each blade, and each fairing is formed by a molded resin skin material covering a rigid foam core.

Abstract: A variable pitch propeller is provided with a blade cuff, with a radially inner portion of the cuff formed in closely surrounding relation to the cylindrical shank of the blade, and with a nose portion of the cuff extending radially outwardly and smoothly flaring to the full cordwise dimension of the cuff, through the conventional blade opening in a spinner. The arrangement eliminates regions for ice entrapment or build-up, and permits a heater boot to be applied to the leading edge down to or even into the blade opening.

Abstract: A fan blade structure of a fan such as, for example, a mixed-flow cooling fan for an automotive internal combustion engine, comprising a blade member having an annular boss portion having a cylindrical outer peripheral surface and a plurality of blade portions integral with and radially projecting outwardly from the boss portion, and a collar member secured to the blade member and having a frusto-conical outer wall portion surrounding the boss portion of the blade member and tapering toward the front end of the boss portion and an inner flange portion circumferentially extending along the boss portion of the blade member and attached to the rear end face of the boss portion, the outer wall portion of the collar member being formed with slots angled and configured conformingly to radially inner end portions of the blade portions, respectively, of the blade member and open at the radially reduced axial end of the collar member.

Abstract: A fan wheel or pre-guide wheel for axial or semi-axial air flow, especially for use with the cooling systems of motor vehicles. In order to provide for advantageous stream line flow, the leading surfaces of the fan wheel hub or an upstream pre-guide wheel hub are suitably rounded providing for a generally increasing hub diameter in the direction of the air flow. In order to simplify the casting or extrusion of the fan wheel so configured, the invention provides for a substantially cylindrical or conically decreasing hub diameter in the region of the fan hub lying generally behind each fan blade. For fan hubs of relatively low axial depth, for example with riveted fan blades, the gaps may remain uncovered without detrimental effects on the air stream.

Abstract: Propeller apparatus including a propeller spinner with a plurality of spaced protruding surfaces extending radially outward from the exterior surface of the spinner and a plurality of variable pitch propeller blades extending radially outward from the spinner through the protruding surfaces of the spinner. Each propeller blade has an inner or root end portion located adjacent to the protruding surface of the spinner and the root end portion has a propeller cuff attached to it or alternatively the root end portion can have an airfoil section.

Abstract: A fluid propeller fan useful as but not limited to an air-circulating cooling fan for an automotive engine, wherein each of the vanes of the fan has a pitch angle which is gradually reduced from the tip or an intermediate portion toward the radially innermost end of the vane so as to provide an increased draught volume and improved draught flow characteristics.

Abstract: Device for the locking of blade roots and the fastening of the forward cowl consisting of a fastening piece comprising a parallelepipedic part (16) engaging radial slots (5) of the teeth (4) of the rim, a prismatic part (17), the convergent faces of which are resting against the sides of the groove and a cylindrical part (22) for the fastening of the cowl (24). The parallelepipedic (16) and prismatic (17) parts are parallel to each other and perpendicular to the cylindrical part (22). The cowl (24) has perforated counterbores (25) through which the cylindrical parts (22) are passing, with the ends of the cylindrical parts receiving a screw (27) to fasten the cowl.

Abstract: A gas turbine propulsion engine for aircraft of the type in which thrust is provided only from flow of exhaust gases or a combination of flow of exhaust gases and by-pass air, the engine having a cone-shaped spinner with a solid pointed tip portion and a main body portion. The tip portion has at least a surface made of a different material from the substantially rigid material of the main body portion, the at least surface of the tip portion being flexible relative to the body portion at operational rotations of the spinner whereby ice is automatically shed from the spinner due to cracks being developed at the bond between the tip portion and the main body portion. The cracks in the ice developed at the bond are propagated by the surface deflection of the remainder of the tip portion causing any accretion of ice thereon to shed from the remainder of the spinner.

Abstract: A spinner is disclosed for use with a model airplane, or the like, which has a propeller on a propeller shaft, the propeller being disposed between a thrust plate fixed to the propeller shaft and retaining means such as a propeller nut threaded onto the propeller shaft. A base plate has an axial passage for receiving the propeller shaft and the propeller nut holds the base plate between the thrust plate and the propeller for conjoint rotation therewith. An air piercing nose cone is releasably mounted to the base plate and has radial openings for receiving the shanks of the propeller blades. A locking ring is rotatably mounted on the base plate for rotation relative thereto about the axis of the propeller shaft between a locking position and a release position. The nose cone has at least one interior stud having a radial notch for engagement by a locking edge of the locking ring when in said locking position to releasably hold the nose cone on the base plate for conjoint rotation therewith.

Abstract: There is disclosed an axial flow fan having blades which are made up of metallic inner portions attached to the hub of the fan, and outer plastic portions whose inner ends are secured to the outer ends of the metallic portion. The plastic portions are hollow and have an exterior surface of air foil cross section, and seal discs on one side of the hub extend outwardly therefrom to approximately the intersection of the metallic and plastic portions.

Abstract: An improved helicopter designed to create minimum drag and turbulence in which the main rotor pylon has a top surface having a forward portion defining the rotor head well aperture so as to have a selectively curved lip on the rearward side thereof to eliminate flow separation therefrom of the air being discharged rearwardly from the rotor head well, further having a central portion curving slightly away from the direction of helicopter flight and including a laterally extending boundary layer slot a selected distance downstream of the curved lip through which fluid is expelled substantially parallel to the direction of helicopter flight to energize the surface flow along the pylon top surface, further having a rear portion at a lower elevation extending approximately in the direction of helicopter flight, and having engine and other exhaust ports positioned a selected distance downstream of the boundary layer control slot through which the exhaust fluids are directed over the rear portion in a direction subs

Abstract: A helicopter main rotor has an improved fairing enclosing the rotor hub and blade root area for drag and vibration reduction purposes. The fairing has peripheral cutouts through which the blades project provided with rounded lips on the rim of the cutouts to streamline air flowing in and out of the fairing through the cutouts. Internal partitions divide the fairing into chambers, each of which subtends one cutout, thus preventing flow of air through the fairing and attendant drag caused thereby. The rotor pylon is provided with a well through which the rotor drive shaft projects having a rounded lip adjacent the fairing to produce streamline airflow out of the well.

Abstract: Autogyro rotor comprises blades radiating outwardly from central disc structure. Disc structure extends over substantial part of the area of the rotor to increase lifting forces provided by rotor and may be shaped to produce aerodynamic lift on forward movement of rotor. Specifically, disc structure may include annular section of aerofoil cross-section surrounded by smaller annular section to produce similar effect to conventional aircraft wing flaps and slots. Blades are carried on shafts journalled in tubes extending out through disc structure and there is also disclosed a pitch control mechanism for rotating the shafts in the tubes to vary pitch of the blades.

Abstract: A small diameter, highly loaded multiple bladed variable pitch propulsor having swept blades with thin advanced airfoil sections, integrated with a nacelle contoured to retard the airflow through the blades thereby reducing compressibility losses and designed to operate with a turbine engine and using a single stage reduction gear resulting in a high performance, lightweight propulsion system providing a substantial improvement in efficiency over the high bypass ratio turbofan engine.

Abstract: The disclosure of this invention pertains to a gas turbine engine with anti-icing facility. The engine has an axial flow compressor having a rotor hub provided at its upstream end with a nose for dividing the air stream into the compressor. The nose has a pointed conical upstream part of limited angle of divergence where ice formation is minimal. The conical part is followed by a toroidally surfaced concave intermediate part defining a transition from the downstream end of the conical part toward the relatively longer diameter of the hub. The increasing angle of divergence of the intermediate part is progressively more prone to ice formation but is also progressively, more able to throw off the ice by centrifugal force. A convex toroidal part forms a surface blending the intermediate part to the hub.

Abstract: A rotating mechanism such as a model aircraft propeller shaft is balanced by a dynamic balancing apparatus comprising a disc rotating with the shaft and a stainless steel O-ring partly filled with mercury lodged in an undercut groove in the face of the disc. The method of manufacture involves placing the ring in the groove and compressing the ring to expand it radially into the undercut area.

Abstract: In a fan with a fluid friction clutch wherein the housing of the clutch is connected with the fan or has fan blades attached thereto and wherein the surface of the clutch housing facing the air intake opening of the fan is provided with cooling ribs to carry off slippage heat, the improvement comprises flow direction means for reducing the effects of the secondary air flow around the clutch housing. The flow directing means comprise either the cooling ribs on the surface of the clutch housing facing the air intake opening of the fan which ribs are curved at the outer edges thereof in a direction reverse to that of the rotation of the fan; cooling ribs of construction angled in reverse direction to that of the direction of rotation of the fan; annular cooling ribs; or cooling ribs of conventional radial arrangement covered by a flow directing intake housing.

Abstract: The spinner for a fan jet engine is constructed from a metallic material having sufficient strength so that it serves as a structural support affording stiffness to the rim of the fan disc.