US3792937A - Bladed rotors - Google Patents

Bladed rotors Download PDF

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Publication number
US3792937A
US3792937A US00187981A US3792937DA US3792937A US 3792937 A US3792937 A US 3792937A US 00187981 A US00187981 A US 00187981A US 3792937D A US3792937D A US 3792937DA US 3792937 A US3792937 A US 3792937A
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Prior art keywords
piston
blades
parts
portions
rotor
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Expired - Lifetime
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US00187981A
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English (en)
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J Chilman
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Dowty Rotol Ltd
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Dowty Rotol Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical

Definitions

  • a bladed rotor includes a hub defined by two casing parts having portions which, when the parts are held together by securing means, form sockets in which the blades of the rotor are mounted.
  • a guide is provided in one of said parts and another guide is provided in the other of said parts.
  • the guides are separated by space defining means and support a control member movable with respect thereto. Means provided in said space connect said control member to the blades and movement of that member adjusts the blades.
  • FIG. 1 is a cross-section of a propeller hub and of a part of a blade mounted in the hub,
  • FIG. 2 is a cross-section taken along line ll-ll
  • HO. 3 is a sectional view taken long the line Ill-Ill a hub defined by two casing parts having portions 5 on FIG. 1, and,
  • the securing means mayinclude bolts provided in the vicinity of the sockets.
  • Each blade may be mounted in an anti-friction bearing provided in its socket, each said bearing being split in a diametral plane thereof.
  • the bladed rotor may be a propeller suitable for an aerial vehicle, and the blades thereof may be of variable-pitch. Alternatively the blades may be of variabletwist or variable camber.
  • the guides may comprise bores and said control member comprise a piston which together form a pitchchange motor.
  • the pitch-change motor may be of single-acting hydraulic type.
  • the motor may be operable under the control of a speed-sensitive centrifugal governor and/or under the control of a manually-operable hydraulic valve having a follow-up mechanism associated therewith.
  • Movement of said piston under hydraulic pressure may be in a direction appropriate to pitch-fining of the blades, such movement being against the effort of first spring means.
  • the range of movement of the piston may be sufficient to afford movement of the blades beyond fine pitch, through zero pitch into the reverse pitch range for effecting braking of the associated vehicle.
  • the first said spring means may be a mechanical coil spring and said further spring means may comprise a Belleville washer stack, both said coil spring and said stack being arranged with their axes coincident with the rotational axis of the rotor.
  • Blades of the rotor may carry fly-weights so disposed with respect to each blade longitudinal axis as to assist said first spring means in biassing the blades in the pitch-coarsening direction.
  • the piston may have surfaces spaced apart from the adjacent end faces of the roots of at least certain of the blades with portions upstanding from those surfaces which have such sliding relationship with said faces and which are so disposed in relation to the respective blade longitudinal axis, as substantially to prevent angular displacement of said piston about the rotational axis of the rotor with respect to said hub, the area of the face associated with each upstanding portion which is in engagement with the respective blade root end face being small in relation to the area of that root end face.
  • FIG. 4 is a partial view in the direction of the arrow IV on FIG. 1.
  • a bladed rotor in the form of an aircraft propeller 1 1 includes a hub 12 comprising two aluminum alloy casing parts 13 and 14 held together by securing means which take the form of four bolts 15 and four nuts 16, the bolts passing through holes 17 and 18 provided in the parts 13 and 14.
  • the engaging faces 19 and 20 of the parts 13 and 14 lie in a plane 21.
  • the parts 13 and 14 together define four sockets 22, 23, 24 and 25 which receive the root portions 26, 27, 28 and 29 of aluminium alloy propeller blades 30, 31, 32 and 33 which are each mounted in respective roller bearings 34, 35, 36 and 37 for pitch variation about the respective longitudinal pitch-change axis 38.
  • each of these bearings are split in a diametral plane thereof.
  • Each inner race 39 is held in a suitablyshaped seating 42 in its respective blade root portion by a wire ring 43, while each outer race 41 is located in a suitably-shaped recess 44 formed in the respective hub socket.
  • Each blade has nylon bearing inserts 45 and 46 and a sealing ring 47 in the position shown. These components are also split in a diametral plane.
  • Each blade also carries a fly-weight assembly 48 so positioned thereon as in operation to produce moments about the blade longitudinal axis which oppose the inherent centrifugal twisting moments in the blades, and which bias the blades in the pitch-coarsening direction.
  • Each fly-weight assembly is held fast to its blade by a U-bolt 49, the U-bolt and part of the fly-weight assembly engaging a peripheral recess 50 in the blade.
  • the part 13 is formed with a guide in the form of a bore 51 whose axis is coincident with the rotational axis'52 of the rotor.
  • the bore 51 is closed at its forward end portion by a hard rubber plug 53 which engages an aperture 54 formed in the end wall 55.
  • the part 14 is provided with a guide in the form of a bore 56, of the same diameter as the bore 51, which is axially-spaced from the bore 51 and whose axis is also coincident with the axis 52.
  • the rearward end portion of the bore 56 is closed by a wall 57 which has an aperture 58 through which an oil supply tube 59 passes coaxially with the axis 52.
  • the forward end portion of the tube 59 is screw-threadedly connected at 60 to a flanged member 61 which in turn is held fast with respect to a pitch-change motor piston 62, which is of aluminium alloy, by means of set screws as at 63.
  • the piston 62 is hollow and is supported for axial sliding movement in the axially-spaced bores 51 and 56, thus toform a control member for the blades.
  • the piston 62 is provided with a central portion of generally square cross-sectional shape as at 64 which includes four upstanding portions 65 each of which is associated with a'respective crank pin 66 projecting from each blade root portion 26, 27, 28 and 29.
  • Each crank pin 66 projects into a bore provided in a respective slide block 67 which is itself slidingly mounted in a channel of the respective upstanding portion 65, a washer 68 being provided between the end face of the respective blade root portion and the portion 64.
  • two slide buttons 69 forming further upstanding portions are located in short bores 70 provided in the central portion 64, being positioned between the end faces of the two blade root portions 26 and 28 and the central portion 64 to prevent tilting of the piston about its longitudinal axis during its axial movement.
  • First spring means in the form of a mechanical coil spring 71 is provided between the right-hand portion in FIG. 1 of the piston 62 and a Belleville washer stack 72 which forms an abutment for the coil spring.
  • the Belleville washer stack 72 is housed at the forward end portion of the bore 51 and seats upon a tubular insert 73.
  • the coil spring 71 is also located on the insert 73 so that both the coil spring and the Belleville washer stack are co-axially arranged with respect to the rotational axis 52.
  • the propeller is intended for fitment upon an engine output shaft shown in dotted lines at 74 with a mounting flange 75 and spigot portion 76.
  • the rearward portion of the part 14 is so shaped as to fit upon the spigot 76, and eight set bolts, one of which is shown at 77, which pass through the flange 75 retain the propeller upon the shaft 74, two locating dowels, one of which is shown at 78, also being provided.
  • FIG. 1 of the drawings the piston 62 is shown in its extreme rearward position corresponding to maximum coarse pitch of the blades 30, 31, 32 and 33.
  • the chamber 79 to the rear of the piston 62 is chargeable with liquid under pressure supplied through the tube 59 and passing into the chamber through ports 80 in the tube.
  • the central portion 64 of the piston 62 is provided with a stop face 81 at the position shown in FIG. 1 which comes into engagement with the face 82 of the casing part 13 at the maximum reverse pitch condition, while the face 83 at the rearward end portion of the piston comes into engagement with the wall '57 at the fully-feathered condition.
  • the construction of the hub hereinbefore described is of relatively simple and inexpensive construction because the pitch-change motor simply comprises the portions of the casing parts 13 and 14 having the two bores 51 and 56 and the piston 62 supported by these bores.
  • the axial spacing between the bores gives a relatively large access opening for connection of the piston to the roots of the propeller blades for pitch-change.
  • the casing part 14 is positioned with its face horizontal and the appropriate outer half-races 41 of the split roller bearing 34, 35, 36 and 37 are fitted into their recesses 44 complete with the half-sets of rollers in their half-cages 40.
  • the appropriate halves of the inserts 45 and 46 and of the sealing rings 47 are also fitted.
  • a special tool (not shown) is applied to the part 13 for compression of the coil spring 71 and the Belleville washer stack 72. This tool is applied with the plug member 53 removed.
  • the part 13 complete with the tool in its operative position is fitted to the assembly of components and secured by the bolts 15 and the nuts 16.
  • the tool is then adjusted to allow the coil spring 71 and Belleville washer stack 72 to expand to their full free length, whereupon the tool is released and removed from the assembly and the plug member 53 is fitted to the aperture 54.
  • the fly-weight assemblies 48 are then fitted to the blades.
  • Suitable balance weights (not shown) are bolted in convenient manner to the hub as necessary for balance of the structure.
  • the tube 59 is fitted to the flanged member 61 just prior to mounting the propeller on the engine shaft 74.
  • liquid under pressure admitted under the control of a control valve assembly (not shown, but carried by the engine structure) into the chamber 79 causes compression of the coil spring 71 and movement of the piston 62 and thus of the blades 30, 31, 32 and 33 in the pitch-fining direction, to the left in FIG. 1, the blocks 67 which are of nylon, sliding in their respective upstanding portions 65, and the washers 68, which are basically of polytetrafluoroethylene material, and the buttons 69, which are also basically of polytetrafluoroethylene material, affording low friction between the linearly moving piston 62 and flat end faces of the blade root portions 26, 27, 28 and 29 as the blades rotate about their pitch-change axes 38.
  • the tube 59 applies a follow up signal to the control valve assembly to arrest the supply of pressure liquid through the tube and to hold the piston 62 hydraulically against the effort of the spring 71 so that the blades are held in the selected position.
  • the blades are positioned at approximately 0 for engine starting, at approximately l8 for take-off of the aircraft, at approximately 35 for flight cruise, and at approximately 15 for approach idling.
  • FIG. 4 indicates the range of pitch-change movement, showing the extreme crank-pin positions at 66 and 66.
  • the Belleville washer stack 72 is of higher rate than the coil spring 71 and serves to overcome the aerodynamic twisting moments, (otherwise effective upon the blades to move them in the pitch-fining direction), thus to move the blades back into the positive pitch range when the hydraulic pressure in the chamber 79 is sufficiently relieved by appropriate selection of the control valve assembly.
  • the coil spring 71 is of sufficient rate as to ensure completion of the feathering movement.
  • tilting of the piston 62 about the rotational axis 52 is substantially prevented in one direction (the clockwise direction when viewed in FIG. 2) by each of the two buttons 69 which are in sliding engagement with the respective blade root end face and is substantially prevented in the other direction (the anti-clockwise direction when viewed in FIG. 2) by the upstanding portions 65 and the associated washers 68, the latter also engaging the respective blade root end face.
  • each button 69 and of the face of each washer 68 in engagement with the respective blade root end face is small in relation to the area of the root end face, since the material of each button and each washer is basically polytetrafluoroethylene, and since the slide blocks 67 are of nylon, low friction is afforded between the linearly moving piston 62 and the flat root end faces of the blades as the blades are driven about their longitudinal axes for pitch-change.
  • the arrangement provides a low-friction pitch-change connection between the pitch-change motor and the blades.
  • the piston is thus constructed in a manner which avoids the use of splines or rods in its mounting in the hub and in its connection to the blades.
  • the forgings from which the hub parts 13 and 14 are produced can be of the same basic shape, the differences between the forward portion of the hub structure and the rearward portion of the hub structure being obtained by machining.
  • the forgings from which the hub parts 13 and 14 are produced can be of the same basic shape, the differences between the forward portion of the hub structure and the rearward portion of the hub structure being obtained by machining.
  • only one basic forging shape is required contributes to the inexpensiveness of this propeller construction.
  • the invention is not limited to the provision of four blades on the hub as any other desired number of blades, with a piston of suitable cross-sectional shape in the zone of the blade root end portions, may be provided.
  • the invention is not limited to aircraft propellers as with advantage it may well be applied to any other bladed rotor, for example propellers for aircushion vehicles, for boats, ships and the like, or alternatively, fans for vehicles or fixed installations, or the bladed rotors of ram-air turbines.
  • the blades each have fly-weights attached thereto, in other embodiments no such flyweights may be provided, or alternatively in yet other embodiments further fly-weights may be provided. Again, on a four-bladed propeller, only two fly-weights may be provided on opposite blades.
  • blades of a bladed rotor are variable in pitch, in other embodiments they may instead be variable in twist, or variable in camber. Also, the rotor may instead be of non-reversible pitch type.
  • piston moves rearwardly of the propeller for pitch-coarsening
  • piston instead moves forwardly of the propeller for pitch-coarsening
  • pitch-change motor of the bladed rotor may be controlled by a speed-sensitive centrifugal governor, or by a manually-operable control valve assembly and a speed-sensitive cntrifugal governor.
  • the invention is not limited to the type of pitchchange motor described with reference to the drawings, as in other embodiments it may be of doubleactinghydraulic type, or again in other embodiments the motor may not be of hydraulic type but instead may be of pneumatic type.
  • control member may be a device other than a piston mounted in guides other than bores and displaceable with respect to the guides by mechanical, electrical or other suitable means.
  • a bladed rotor including a hub casing defined by two casing parts, each having a first portion including radiallyoutwardly-directed projections, the two portions being of substantially identical form so that when said parts are held together in assembled relation by securing means said projections form radially-outwardlydirected sockets of circular cross-section in which the blades of the rotor are mounted with freedom for pitchchange adjustment about their longitudinal axes, the plane in which the said two parts are in engagement being disposed diametrically of all the sockets, each of said casing parts also having a single cylindrical portion projectingfrom its said first portion, the two cylindrical portions being of substantially identical form and extending from the first portions away from each other with their axes coincident with the axis of rotation of the rotor, space-defining means which separate the two cylindrical portions, the one axially from the other, one end closure wall provided at the end of one of said cylindrical portions remote from said plane, another end closure wall positioned at that end of the other of said cylindrical portions remote from said plane, a piston
  • a bladed rotor including a hub casing defined by two casing parts, each having a first portion including radially-outwardly-directed projections, the two portions being of substantially identical form so that when said parts are held together in assembled relation by securing means said projections form radially-outwardlydirection sockets of circular cross-section in which the blades of the rotor are mounted with freedom for pitchchange adjustment about their longitudinal axes, the plane in which the said two parts are in engagement being disposed diametrically of all the sockets, each of said parts also having a single cylindrical portion projecting from its said first portion, the two cylindrical portions being of substantially identical form and extending from the first portions away from each other with their axes coincident with the axis of rotation of the rotor, space-defining means which separate the two cylindrical portions, the one axially from the other, one end closure wall provided at that end of one of said cylindrical portions remote from said plane, another end closure wall positioned at that end of the other of said cylindrical portions remote from said plane, a piston
  • a bladed rotor including a hub casing defined by two casing parts, each having a first portion including radially-outwardly-directed projections, the two portions being of substantially identical form so that when said parts are held together in assembled relation by securing means said projections form radially-outwardlydirected sockets of circular cross-section in which the blades of the rotor are mounted with freedom for pitchchange adjustment about their longitudinal axes, the plane in which the said two parts are in engagement being disposed diametrically of all the sockets, each of said casing parts also having a single cylindrical portion projecting from its said first portion, the two cylindrical portions being of substantially identical form and extending from the first portions away from each other with their axes coincident with the axis of rotation of the rotor, space-defining means which separate thetwo cylindrical portions, the one axially from the other, one end closure wall provided at that end of one of said cylindrical portions remote from said plane, another end closure wall positioned at that end of the other of said cylindrical portions remote from said plane, a
  • a bladed rotor including a hub defined by two casing parts having portions which, when the parts are held together in assembled relation by securing means, form radially-outwardly-directed sockets of circular cross-section which house anti-friction bearing means by way of which the blades of the rotor are mounted with freedome for pitch-change adjustment about their longitudinal axes, the plane in which said two parts are in engagement being disposed diametrically of all the sockets, and said two parts each having a respective bore portion provided with an end closure wall remote from said plane, the axis of one bore portion being coincident with that of the other bore portion, spacedefining means which separate'said bore portions axially one with respect to the other, a hollow piston wholly enclosed within said two assembled casing parts with one end portion thereof slidably supported in said one bore portion and the other end portion thereof slidably supported in said other bore portion, said piston closed at said other end portion and there forming with said other bore portion an expansible pitch-change motor chmber which is connectible with
  • a bladed rotor including a hub defined by two casing parts having portions which, when the parts are held together in assembled relation by securing means, form radially-outward]y-directed sockets of circular cross-section which house anti-friction bearing means by way of which the blades of the rotor are mounted with freedom for pitch-change adjustment about their longitudinal axes, the plane in which said two parts are in engagement being disposed diametrically of all the sockets, and said two parts each having a respective bore portion, the axis of one bore portion being coincident with that of the other 'bore portion, spacedefming means which separate said bore portions axially one with respect to the other, a hollow piston wholly enclosed within said two assembled casing parts with one end portion thereof slidably supported in said one bore portion and the other end portion thereof slidably supported in said other bore portion, said piston being closed at said other end portion and there forming with said other bore portion an expansible pitchchange motor chamber which is connectible withfluid under pressure, and the piston
  • each blade is mounted in an anti-friction bearing provided in its socket, each said bearing being split in a diametral plane thereof.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Hydraulic Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00187981A 1970-11-04 1971-10-12 Bladed rotors Expired - Lifetime US3792937A (en)

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Application Number Priority Date Filing Date Title
GB5255770A GB1363426A (en) 1970-11-04 1970-11-04 Bladed rotors

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US3792937A true US3792937A (en) 1974-02-19

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US00187981A Expired - Lifetime US3792937A (en) 1970-11-04 1971-10-12 Bladed rotors

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FR (1) FR2112447B1 (enrdf_load_stackoverflow)
GB (1) GB1363426A (enrdf_load_stackoverflow)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4037986A (en) * 1975-09-04 1977-07-26 Dowty Rotol Limited Bladed rotors having control means for effecting blade pitch adjustment
US4221541A (en) * 1977-02-28 1980-09-09 Axial International Aktiengesellschaft Fan comprising a blade pitch control mechanism
US4362467A (en) * 1979-02-08 1982-12-07 Elliott Morris C Variable pitch propeller device
US4365937A (en) * 1979-11-26 1982-12-28 Hiebert Harold L Adjustable pitch propeller drive
US4428716A (en) 1977-06-10 1984-01-31 Maloof Ralph P Variable pitch propeller hub with fluid motor actuating means
US4474533A (en) * 1981-02-23 1984-10-02 Kawasaki Jukogyo Kabushiki Kaisha Controllable pitch propeller assembly
US4575309A (en) * 1983-05-25 1986-03-11 James Howden & Company Ltd. Wind turbines
US5159620A (en) * 1990-09-28 1992-10-27 Thomas Bordelon Variable pitch propeller apparatus
EP0945626A3 (de) * 1998-03-26 2001-04-04 Hägele GmbH Lüfterrad, insbesondere im Kühlsystem von Brennkraftmaschinen einsetzbares Lüfterrad
US6439850B1 (en) 1998-07-15 2002-08-27 Flexxaire Manufacturing Inc. Variable pitch fan
US6443701B1 (en) * 1999-01-29 2002-09-03 MüHLBAUER LUFTFAHRTTECHNIK GMBH Blade root for propeller and rotor blades
US20060188375A1 (en) * 2005-02-18 2006-08-24 Mario Bussieres Rotor for a turbomachine
US20090016896A1 (en) * 2007-05-25 2009-01-15 Hill Daryl G Conical washer system for propeller stabilization
US20110189018A1 (en) * 2008-09-17 2011-08-04 Berg Propulsion Technology Ab Propeller
US20110206519A1 (en) * 2010-02-24 2011-08-25 United Technologies Corporation Fastener aperture having an elongated geometry
US20110236212A1 (en) * 2010-03-29 2011-09-29 Snecma Feathering device for the fan blades of a turboprop engine
US12253005B2 (en) * 2022-06-17 2025-03-18 General Electric Company Rotating airfoil with a spring damper system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2140096B (en) * 1983-05-13 1987-04-29 Wilfred Thomas Bellew Marine propeller pitch control system
FR3157353A1 (fr) * 2023-12-26 2025-06-27 Safran Helicopter Engines Ensemble propulseur hybride electrique pour aeronef

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NL283406A (enrdf_load_stackoverflow) *
DE666385C (de) * 1936-10-14 1938-10-18 Karlstad Mekaniska Ab Nabe mit in ihr gelagerten, waehrend des Betriebes verdrehbaren Schaufeln fuer Wasserturbinen, Pumpen oder Schiffsschrauben
US2255920A (en) * 1937-02-01 1941-09-16 Englesson John Elov Ship propeller having rotatable blades
US2612229A (en) * 1945-03-06 1952-09-30 Tornes Ferdinand Variable pitch propeller blade root construction
US3103978A (en) * 1960-09-24 1963-09-17 Slack & Parr Marine Ltd Variable pitch marine screw propellers
US3393749A (en) * 1967-08-25 1968-07-23 Feroy Arne Controllable pitch propellers
US3393748A (en) * 1966-07-22 1968-07-23 United Aircraft Corp Propeller with spring actuated variable pitch
US3501251A (en) * 1967-03-22 1970-03-17 Karlstad Mekaniska Ab Variable pitch propeller
US3534703A (en) * 1967-01-09 1970-10-20 Saab Scania Ab Outboard propelling system comprising an adjustable propeller
US3637323A (en) * 1968-07-08 1972-01-25 Dowty Rotol Ltd Variable-pitch bladed rotors
US3645644A (en) * 1970-01-22 1972-02-29 Hydro Drive Corp Interlocking variable-pitch propeller assembly
US3676016A (en) * 1970-09-21 1972-07-11 Arne Feroy Controllable pitch propellers

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL283406A (enrdf_load_stackoverflow) *
DE666385C (de) * 1936-10-14 1938-10-18 Karlstad Mekaniska Ab Nabe mit in ihr gelagerten, waehrend des Betriebes verdrehbaren Schaufeln fuer Wasserturbinen, Pumpen oder Schiffsschrauben
US2255920A (en) * 1937-02-01 1941-09-16 Englesson John Elov Ship propeller having rotatable blades
US2612229A (en) * 1945-03-06 1952-09-30 Tornes Ferdinand Variable pitch propeller blade root construction
US3103978A (en) * 1960-09-24 1963-09-17 Slack & Parr Marine Ltd Variable pitch marine screw propellers
US3393748A (en) * 1966-07-22 1968-07-23 United Aircraft Corp Propeller with spring actuated variable pitch
US3534703A (en) * 1967-01-09 1970-10-20 Saab Scania Ab Outboard propelling system comprising an adjustable propeller
US3501251A (en) * 1967-03-22 1970-03-17 Karlstad Mekaniska Ab Variable pitch propeller
US3393749A (en) * 1967-08-25 1968-07-23 Feroy Arne Controllable pitch propellers
US3637323A (en) * 1968-07-08 1972-01-25 Dowty Rotol Ltd Variable-pitch bladed rotors
US3645644A (en) * 1970-01-22 1972-02-29 Hydro Drive Corp Interlocking variable-pitch propeller assembly
US3676016A (en) * 1970-09-21 1972-07-11 Arne Feroy Controllable pitch propellers

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4037986A (en) * 1975-09-04 1977-07-26 Dowty Rotol Limited Bladed rotors having control means for effecting blade pitch adjustment
US4221541A (en) * 1977-02-28 1980-09-09 Axial International Aktiengesellschaft Fan comprising a blade pitch control mechanism
US4428716A (en) 1977-06-10 1984-01-31 Maloof Ralph P Variable pitch propeller hub with fluid motor actuating means
US4362467A (en) * 1979-02-08 1982-12-07 Elliott Morris C Variable pitch propeller device
US4365937A (en) * 1979-11-26 1982-12-28 Hiebert Harold L Adjustable pitch propeller drive
US4474533A (en) * 1981-02-23 1984-10-02 Kawasaki Jukogyo Kabushiki Kaisha Controllable pitch propeller assembly
US4575309A (en) * 1983-05-25 1986-03-11 James Howden & Company Ltd. Wind turbines
US5159620A (en) * 1990-09-28 1992-10-27 Thomas Bordelon Variable pitch propeller apparatus
EP0945626A3 (de) * 1998-03-26 2001-04-04 Hägele GmbH Lüfterrad, insbesondere im Kühlsystem von Brennkraftmaschinen einsetzbares Lüfterrad
US6644922B2 (en) 1998-07-15 2003-11-11 Flexxaire Manufacturing Inc. Variable pitch fan
US6439850B1 (en) 1998-07-15 2002-08-27 Flexxaire Manufacturing Inc. Variable pitch fan
US6443701B1 (en) * 1999-01-29 2002-09-03 MüHLBAUER LUFTFAHRTTECHNIK GMBH Blade root for propeller and rotor blades
US20060188375A1 (en) * 2005-02-18 2006-08-24 Mario Bussieres Rotor for a turbomachine
US7214035B2 (en) 2005-02-18 2007-05-08 Mario Bussières Rotor for a turbomachine
US20090016896A1 (en) * 2007-05-25 2009-01-15 Hill Daryl G Conical washer system for propeller stabilization
US20110189018A1 (en) * 2008-09-17 2011-08-04 Berg Propulsion Technology Ab Propeller
US20110206519A1 (en) * 2010-02-24 2011-08-25 United Technologies Corporation Fastener aperture having an elongated geometry
US9863250B2 (en) * 2010-02-24 2018-01-09 United Technologies Corporation Fastener aperture having an elongated geometry
US20110236212A1 (en) * 2010-03-29 2011-09-29 Snecma Feathering device for the fan blades of a turboprop engine
US8696303B2 (en) 2010-03-29 2014-04-15 Snecma Feathering device for the fan blades of a turboprop engine
US12253005B2 (en) * 2022-06-17 2025-03-18 General Electric Company Rotating airfoil with a spring damper system

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Publication number Publication date
FR2112447B1 (enrdf_load_stackoverflow) 1974-09-27
GB1363426A (en) 1974-08-14
FR2112447A1 (enrdf_load_stackoverflow) 1972-06-16

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