Abstract: An impeller for a fan comprising a hub for rotation by a drive rotor and a plurality of fan blades for rotation with the hub, the impeller further comprising a support or guide member supporting or connecting fan blades of said plurality, and wherein one or more pockets are provided in said support or guide member and open axially of the fan for receiving balance weights.

Abstract: In the device, the turbine blades are anchored with blade feet, which are profiled like teeth, to correspondingly shaped axial grooves of a wheel disk. An axial gap is left between each blade foot end and the base of an axial groove, in which gap a securing element is disposed. The securing element can be bent on both ends, which protrude out from the gap, directed opposite each other against faces of the wheel disk and a blade foot, and is clamped in a wedged manner in the relevant axial gap between the groove base and the blade foot. The securing element bridges over a recess, which is formed in the blade foot to receive a balancing mass.

Abstract: A windmill blade with booster members comprised of a circular mounting portion having a receiving aperture formed through a central portion thereof. The circular mounting portion is adapted for coupling with a free standing leg member. A plurality of elongated blade members are coupled with the circular mounting portion. A plurality of weighted spherical members are secured to distal ends of their respective elongated member.

Abstract: A rotor disk arrangement for a turbojet engine includes a balancing and damping system which has a ring having a circumferential surface recessed with housings and balance masses respectively positioned in the housings. A disk having a circumferential surface is provided which engages the circumferential surface of the ring. The circumferential surfaces are provided with a plurality of bayonet couplings, the couplings including a tenon and a groove engaged with the tenon. The groove includes a straight entrance portion which is substantially parallel to the axis of the engine and a crooked hind part which is substantially circumferentially positioned in the engine. In addition, a plurality of tongues are provided which are respectively inserted into the entrance portions of the grooves and fastened to the ring.

Abstract: A pump rotor for displacing fluids includes a cover and a bottom part having blades. Both the bottom part and the cover are formed by injection molding of thermoplastic materials, preferably reinforced by fillers. The bottom part and the cover are joined together by welding. The walls of the bottom part and cover are sufficiently thin to replace similar metal parts and to provide maximum benefit of the skin effect resulting from the specific surface qualities of the molded material forming the bottom part and the cover. A mold for molding the bottom part and the cover is equipped with a cap which is angularly and vertically adjustable making it possible for a balancing weight to be fitted on the molded parts. The balancing weight is also angularly adjustable and has an adjustable mass.

Abstract: The attachment of the blade to the disk of a gas turbine engine includes a sloped deep slot formed in the rim of the disk for accepting the dovetail of the root of he fan or compressor blade allowing the removal of a single blade from the disk and includes a segmented retainer plate disposed at the aft end of the bearing against the blade root to react out the slope induced axial blade loads providing a low hub-tip ratio configuration. A blade support disposed between the live rim of the disk and the bottom of the blade serves to support the blades radially during non-operating conditions and includes pockets for retaining weights for dynamic balance of the rotor. A forward mounted snap ring prevents forward movement of the blade during non-operating conditions.

Abstract: A rotor blade for a turbine engine rotor assembly is provided comprising a root, an airfoil, a platform, and apparatus for damping vibrations in the airfoil. The airfoil includes a pocket formed in a chordwise surface. The apparatus for damping vibrations in the blade includes a damper and a pocket lid. The damper is received within the pocket between an inner surface of the pocket and the pocket lid. The pocket lid is attached to the airfoil by conventional attachment apparatus and contoured to match the curvature of the airfoil.

Abstract: A propeller for a boat having a plurality of recesses and a plurality of land portions arranged circumferentially alternately around an outer periphery of a propeller boss which is fitted over and connected to a propeller shaft. A boss of each of propeller blades and each of blade shafts disposed parallel to an axis of the propeller boss to rotatably support such propeller blade are accommodated in each of the recesses, and each of the land portions is provided with an exhaust passage extending axially through the land portion to permit an exhaust outlet in a body of a propelling device to be opened at a rear end face of the propeller boss. Thus, it is possible to discharge an exhaust gas from an engine through the inside of the propeller boss into water.

Abstract: The present invention is directed to an assembled steam turbine with at least one balancing ring. The assembled steam turbine includes a shaft rotatable about an axis and a housing, defining a machine interior. The housing has first and second axially-spaced end walls, with the shaft extending through the first end wall. A first bearing and a second bearing rotatably support the shaft. The first and second bearings are axially spaced along the shaft and at least the first bearing is positioned outside the machine interior, proximate the first end wall of the housing. At least one balancing ring which has a plurality of radial holes is coaxially-mounted on the shaft outside the machine interior between the first end wall of the housing and the first bearing. A method for balancing the assembled steam turbine disclosed above includes several steps.

Abstract: A blower blade assembly has a plurality of blades, at least one of which is provided with a counterbalancer. The counterbalancer is of one-piece construction and includes a first arm having two contact areas spaced apart from each other and adapted to contact the first surface of the fan blade when the counterbalancer is mounted on the fan blade, a second arm having one contact area adapted to contact the second surface of the fan blade when the counterbalancer is mounted on the fan blade, and an elastic connecting bridge connecting the first and second arms together.

Abstract: Leading edge weights for helicopter rotor blades are required to provide blade chordwise balance and maintain rotor inertia. Provision for retention of the leading edge weights in a high centrifugal force field, after failure of the primary adhesive bond, is necessary. The invention discloses wrapping a prepreg strap around the conical or cylindrical outboard end of each weight segment. The weight segment is then placed in the rotor blade spar and goes through the spar cure cycle with it. Primary retention is provided by adhesive bonding between the weight and the spar. Secondary retention is by hoop tension in the strap, acting through interlaminar shears at the co-cured interface with the spar.

Abstract: A device for axially securing a moving blade and for eliminating rotor unbalances is provided. The moving blade has a blade base. A wheel disk has circumferentially distributed axial grooves. The blade base is anchored in one of the axial grooves wherein the axial groove encloses an indentation formed between a bottom of the axial groove and an end of the blade base. A filler piece operatively arranged on the bottom of the axial groove, and a securing plate having two ends, are insertable into the indentation. The securing plate is arranged to bridge a gap formed between the end of the blade base and the filler piece along an axial length of the indentation with the two ends projecting beyond the indentation. The securing plate is bent at each of its two ends in a mutually opposite manner with respect to end faces of the filler piece, wheel disk and blade base. One rotor unbalance of the blade is compensated by at least one filler piece.

Abstract: The invention is directed to an axial fan having a hub and including an annular flange and a plurality of fan blade units distributed in spaced relationship about the periphery of the annular flange. Each of the fan blade units includes a base portion defining a hub component and a fan blade extending outwardly from the base portion. The hub components are disposed in spaced relationship one next to the other around the periphery of the annular flange to define the hub of the axial fan and so as to cause each two mutually adjacent ones of the hub components to be separated from each other and to define a gap therebetween. Each of the fan blade units is a single piece injection molded onto the annular flange.

Abstract: A ceiling fan mounts an elongate continuous tube member containing a viscous fluid permitting displacement of the fluid to counter-balance imbalance in a fan assembly, with the tube arranged for mounting to the individual fan blades of the fan assembly.

Abstract: The invention is directed to a damper ring for damping the natural vibration of the rotor blades of an integrally bladed rocket turbine rotor. The invention consists of an integral damper ring which is fixed to the underside of the rotor blade platform of a turbine rotor. The damper ring includes integral supports which extend radially outwardly therefrom. The supports are located adjacent the base portion and directly under each blade of the rotor. Vibration damping is accomplished by action of tuned mass damper beams attached at each end to the supports. These beams vibrate at a predetermined frequency during operation. The vibration of the beams enforce a local node of zero vibratory amplitude at the interface between the supports and the beam. The vibration of the beams create forces upon the supports which forces are transmitted through the rotor blade mounting platform to the base of each rotor blade.

Abstract: A blade of a built-up marine propeller is balanced by forming an open cavity of a predetermined size at a predetermined location proximate to the blade tip, conducting a spin-balancing test in which the blade being balanced and a calibration blade are assembled diametrically opposite each other on a dummy hub to form a simulated two-blade propeller, determining from the test the weight that must be added to the blade to balance the simulated propeller, and affixing a balance member of a predetermined weight in the blade cavity. A cover plate is secured in the cavity opening of the blade in sealed relation, and the external surface of the cover plate is ground to make it fair to the profile of the portion of the blade face adjacent the cavity opening.

Abstract: Blade pitch is changed by an actuator that is responsive to the relative rotation of two input members. Blade pitch is not changed when the members are rotated at the same speed. However, blade pitch is changed in one direction when a braking torque is applied to one member, and blade pitch is changed in an opposite direction when a braking torque is applied to the other member.

Abstract: A rotor blade balance weight assembly comprises a weight retention housing (10) having a hollow core (22) and being closed on one end (12). The housing is disposed in an aperture which extends from the upper (52) to the lower (53) airfoil surfaces of the rotor blade (50). The closure end of the housing is contoured to match the airfoil upper surface contour. A stud (70) extends along the central axis of the housing, and washer-like balance weights (72) are received over the stud and secured by a locking nut (75). The open end of the housing is closed by a cover plate (25) that is contoured to match the airfoil lower surface contour, the cover plate being secured to the housing by a nut (78) in locking engagement with the stud. A pair of clips (37) are received within the housing, each clip having a tab surface (40) which extends through slots (42) in the housing, the clips being secured by the locking nut and stud.

Abstract: An axial blower has a blower motor and a blower wheel. The blower motor includes a motor shaft; a motor housing; a front and a rear bearing cover attached to the motor housing; ventilating openings provided in the front bearing cover; and air outlet openings provided in the rear bearing cover. The blower wheel includes a hollow hub surrounding the rear side of the motor housing; a plurality of impellers affixed to the exterior of the hub and projecting therefrom; a plurality of vane-like ribs carried by the hub at the interior thereof for generating a cooling air stream flowing between the hub and the motor housing; a bell-shaped part forming an axial continuation of the hub and surrounding the front side of the motor housing, a bottom portion, a central opening in the bottom portion and a plurality of ventilating openings provided in the bottom portion. The ventilating openings are arranged in a circular array concentrically with the central opening.

Abstract: A method for balancing the rotor of a wind turbine and a balancing weight. The weight is formed of a piece of steel or other material of sufficient weight bent in an L shape with holes that allow it to be bolted onto a flange at the root of the wind turbine's blades. The width, thickness, or length of the weight can be varied to produce balancing weights of unique weight and radius from the rotor's axis of rotation. A trial weight is disclosed for use with the so-called four run method of determining the rotor's unbalance. The trial weight can be quickly and easily attached and removed.

Abstract: A slowly turning rotating mass, such as a wind turbine rotor, is balanced in situ by measuring the magnitude of a phenomenon, such as acceleration, created by rotor unbalance at a location on a mass support shaft which is close to the mass. The measurement of the phenomenon is made along a line selected to be insensitive to the bias of gravity on the mass. The measurement is made while the mass turns at its usual operating rate. The structure which supports the shaft is fixed as rigidly as possible in space while measurements of the phenomenon are made.

Abstract: A radial compressor rotor, especially for static imbalance of a dual flow radial compressor impeller, having back-to-back blades in a gas turbine engine, is provided with at least one axial through hole in the rotor hub. The axial hole is filled in by an imbalance compensating insert which covers the ends of the hole between neighboring radial blade contour surfaces in an aerodynamically flush manner. The density and density distribution of the material of the insert is selected relative to the density and mass concentration of the material of the compressor impeller to achieve the desired imbalance compensating effect.

Abstract: A balance weight for the rotor of a gas turbine engine is adapted to mount within the cavity formed between the innermost surface of the dovetail slots formed in the circumference of the rotor disk and the bottom of the dovetail root of the rotor blades inserted within the dovetail slots. The balance weight has a head portion formed with a bottom surface which mates with the innermost surface of the dovetail slots, and a lip connected to the head portion which engages the aft surface of the rotor disk. The balance weight is supported in an aft direction within the dovetail slots by an aft blade retainer having a shoulder or projection which contacts the balance weight.

Abstract: A method and apparatus for balancing the rotor in the low pressure stage of the turbine in a jet engine comprises attaching at least one balance clip to the shroud of the rotor. The balance clip comprises a clip body formed with a forward hook portion adapted to extend over the forward rail of the shroud and an aft tab which is crimped over the aft rail of the shroud onto its outer surface so that the clip body is retained against the interior face or diameter of the shroud. The balance clip is formed of sheet material such as AMS 5596E/5597B whose weight can be varied by altering the thickness or width of the clip body, or by drilling holes in the clip body to remove material therefrom.

Abstract: An aircraft propeller blade is constructed by forming two shells of composite material laminates and bonding the two shells to a metallic spar with foam filler pieces interposed between the shells at desired locations. The blade is then balanced radially and chordwise.

Abstract: A V-twin, two stage compressor has valve plates disposed between the head and cylinder of each stage and mounting free-floating flexible reed intake and exhaust valves therein. The flexible reeds are movably captured between the floors of respective reed recesses, and separate, non-fixed keeper bars are disposed over, but slightly spaced from, the reeds. Keeper bars over the exhaust reed extend above the valve plate for engagement by the head. A restrictor plate lies within a valve plate recess on keeper bars over the intake valve. A cored crankshaft providing motor drive shaft lubrication, and a removable counter-weight providing crankshaft use with one-piece connecting rods is disclosed. A cooling fan is driven by the removable counterweight and V-shaped fan shroud projections direct cooling air over the cylinders and heads while another cooling air port directs air over an intercooler.

Abstract: A gas turbine rotor includes a disk (50) with axial dovetail slots (64) and air cooled blades (52) having mating, but shortened dovetails (66). The axial flow path (68) so formed is blocked at the far end and is in fluid communication with the blade cooling passages. Balance weights (70) fit within the openings in a manner which does not interfere with the cooling airflow.

Abstract: A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the asssembly balance of the rotor. A snap ring (42) retains the weights within the openings.

Abstract: A balanced turbine rotor has a cylindrical member with a pair of opposed end shafts and an enlarged central portion, the enlarged central portion having first and second faces, with a circular groove formed in at least one of the faces and expandable weight assemblies engageable in the groove. The weight assemblies have an arcuate body member and an expander screw, the arcuate body member formed into upper and lower deformable secetions by a bore therethrough and slots from side walls thereof to the bore, such that the expander screw forces the deformable sections apart to secure the weights at any desired location about the groove in the face of the enlarged central portion of the rotor.

Abstract: In a low capacity compressor, the shaft (20) of the drive motor carries a fan wheel (42) including a crank pin (46) formed integral therewith. The lower end of a connecting rod (62) is journalled on the crank pin (46). The portion of the fan wheel (42) opposing the crank pin (46) is formed with an arc shaped balancing rib (82) having an angular extension of 180.degree.. Precise balancing of the piston/fan wheel unit is obtained by cutting material from the initially oversized balancing rib (82) and/or cutting from the portion of the fan wheel (42) being opposed to the balancing rib (82) so that a balancing groove (102) is obtained.

Abstract: A snap ring substantially uniform corss section is placed within a groove in a rotor disk of a bladed rotor. Unbalance of the bladed rotor with the ring installed is determined. The snap ring is removed for grinding to correct the unbalance and reinstalled at the same location grinding on or near the rotor is thereby avoided.

Abstract: A composite material blade is provided having a twin longeron and twin box structure with laminated honeycomb sandwich coverings, including a front leading edge longeron of a C shaped section, a central longeron with two sole pieces at the ends of a transverse web with honeycomb filling sandwiched between lateral sheets, and laminated coverings made from honeycomb panels sandwiched between external and internal sheets formed by stacking layers of fiber fabric, so as to define two boxes filled with very light foam cores, the sole pieces being integrated in the coverings which are joined at the level of the trailing edge by a rider in the form of a foam wedge.

Abstract: A balance system for a high speed bladed rotor includes a collar (28) with an inwardly facing groove (30). Balance weights (36) are located in the groove with a cover plate (44) retaining the weights and covering the weights, groove and slots (32) in the collar. A compact arrangement is achieved with the weight close to the disk and windage losses are reduced.

Abstract: A controllable lifting rotary wing for an aircraft wherein each rotor blade is mounted in such a manner that it has freedom to oscillate in pitch about its feathering axis. The aerodynamic center on each rotor blade is displaced forward of this feathering axis over at least a portion of the span. Cyclic aerodynamic forces on this spanwise portion cause the blade to change pitch sinusoidally once-per-revolution of the rotor whenever the rotary wing aircraft experiences a change in flight attitude or velocity. The result is that the rotor blades automatically and continuously change pitch to cancel out cyclic lateral flapping moments which are normally produced on a helicopter rotor blade by such a flight disturbance. This rotary wing has greatly improved stability by virtue of this self-feathering action. Cyclic pitch control moments are applied to the rotor blades by indirect means which do not interfere with automatic blade feathering. Means for control of collective pitch of the blades are also provided.

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 selection of the mass of a mechanical damper 20 for a blade 12 in a turbine wheel 10, 12 independent of the size of a damper receiving opening 22 is achieved by making the damper 20, 40, 50, 60, partially hollow (FIG. 4) or completely hollow (FIGS. 5-7, inclusive).

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 nodalized rotor system is provided for a multi-bladed helicopter. Equally spaced radial arms each have an inboard flapping section to accommodate beam-wise blade flapping and an outboard flex section to accommodate pitch changes. A blade is coupled to the end of each arm with a cuff and pitch horn rigidly connected to the blade and pivotally connected to its arm in the region of the flapping section. The blade has a concentration of weight over the section of blade extending from about 32% to 42% of the hub-blade radius of running weight four times the running weight at 50% of the hub-blade radius. Said blade has a reduced mass at outboard 30% of the hub-blade radius, at a level of 80% of the running weight at 50% of the hub-blade radius.

Abstract: The invention is related to an impeller for a single vane type of centrifugal pump. In order to diminish the risk of clogging of the pump when pumping a fluid having a large impurity content, a vane having varying thickness is provided. In this manner, the speed reduced in the channel is limited resulting in a favorable flow pattern. Additionally, the vane may be made hollow in order to reduce unbalance problems.

Abstract: A pump impeller to be used when pumping liquid containing solid bodies. The impeller is provided with one single vane designed with a hollow for balancing the impeller. The hollow is connected to the surroundings via a slot at a point where the vane has its maximum diameter. The impeller is then perfectly balanced when rotating in liquid as well as in air.

Abstract: Dovetail spacers containing slots enable final balancing of a turbine or compressor rotor or wheel without employing grooves or drilling holes in the wheel itself. The spacers are installed in the normal fashion and, when final balancing is performed, appropriate weights are inserted into the slots in selected ones of the spacers. Fine tuning can be performed by drilling or grinding the weights. In one embodiment, the spacer is provided with a radial hole which joins an axial hole. After the turbine or compressor rotor is assembled, additional counterweight material can be added through the radial hole and then be held in place by suitable means such as a setscrew. In this embodiment, weights of suitable material can also be removed as necessary.

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: 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: A nondestructive method of applying and removing instrumentation on airfoils.

Abstract: A propeller fan construction is provided in which the impeller thereof includes a spider member having a plurality of symmetrically arranged planar marginal portions, and a plurality of blades projecting outwardly from the spider member. Each blade has an inner end provided with a planar segment which is fixedly mounted on a planar marginal portion of the spider member. The spider member and each of the blades are formed of sheet material. Each blade is provided with an elongated embossment extending from one elongated edge of the blade in an angular direction relative to the longitudinal axis of the blade. The embossment is position between the outer end of the blade and the planar segment of the inner end.

Abstract: Disclosed is a technique and apparatus for dynamically balancing rotating members without the necessity of dismantling the same. A horizontally mounted fan is disclosed having passageways in the shaft thereof leading to receptacles within the fan blades themselves wherein weights may be deposited by means of the centrifugal force of the rotating fan. Further means are presented wherein access may be made to weight receptacles of a sealed fan system by means of a weight depositing probe which is operative to make engagement with the various weight receptacles. Yet another embodiment utilizes tubular passageways mounted externally to the rotational shaft of a horizontal system to make engagement with weight receptacles positioned about the rotating system. Also disclosed is a unique slide rule particularly adapted to appropriately divide a requisite balancing weight into components for the various weight receiving receptacles available.

Abstract: A helicopter rotor blade having at least one ramp tab of selected span and chord dimensions, weight and shaped to define an outer surface of selected angularity with respect to the blade chord and being selectively positioned along the blade trailing edge and bonded to its upper or lower surface so as to be totally within the blade chord profile and be effective to eliminate or reduce to within acceptable limits blade pitching moment dynamic unbalance.

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.