GB2244525A - Propeller blade hub assembly - Google Patents

Propeller blade hub assembly Download PDF

Info

Publication number
GB2244525A
GB2244525A GB9007673A GB9007673A GB2244525A GB 2244525 A GB2244525 A GB 2244525A GB 9007673 A GB9007673 A GB 9007673A GB 9007673 A GB9007673 A GB 9007673A GB 2244525 A GB2244525 A GB 2244525A
Authority
GB
United Kingdom
Prior art keywords
propeller blade
propeller
assembly
hub assembly
hub
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB9007673A
Other versions
GB9007673D0 (en
GB2244525B (en
Inventor
Michael Poucher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Smiths Aerospace Gloucester Ltd
Original Assignee
Smiths Aerospace Gloucester Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Smiths Aerospace Gloucester Ltd filed Critical Smiths Aerospace Gloucester Ltd
Priority to GB9007673A priority Critical patent/GB2244525B/en
Publication of GB9007673D0 publication Critical patent/GB9007673D0/en
Publication of GB2244525A publication Critical patent/GB2244525A/en
Application granted granted Critical
Publication of GB2244525B publication Critical patent/GB2244525B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/54—Systems consisting of a plurality of bearings with rolling friction
    • F16C19/546—Systems with spaced apart rolling bearings including at least one angular contact bearing
    • F16C19/547—Systems with spaced apart rolling bearings including at least one angular contact bearing with two angular contact rolling bearings
    • F16C19/548—Systems with spaced apart rolling bearings including at least one angular contact bearing with two angular contact rolling bearings in O-arrangement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
    • F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
    • F16C35/06—Mounting or dismounting of ball or roller bearings; Fixing them onto shaft or in housing
    • F16C35/067—Fixing them in a housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
    • F16C19/14—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load
    • F16C19/16—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
    • F16C19/163—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls with angular contact
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/34—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load
    • F16C19/36—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with a single row of rollers
    • F16C19/364—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with a single row of rollers with tapered rollers, i.e. rollers having essentially the shape of a truncated cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2326/00—Articles relating to transporting
    • F16C2326/43—Aeroplanes; Helicopters

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Rolling Contact Bearings (AREA)

Abstract

A propeller blade hub assembly comprises a hub 1 within which is located a propeller blade 2. The assembly includes a radially innermost bearing comprising races 7, 9 with a number of angular bearings eg ball bearings 3a, and a radially outermost bearing comprising races 8, 10 with a number of roller bearings 4a. The roller bearings 4a are positioned so that their longitudinal axes are inclined outwardly from the longitudinal axis of the propeller blade root assembly, enabling a preloading force to be applied by a preloading ring 12 without causing a large increase in the frictional forces induced by rotational movement of the propeller blade 2 with respect to the hub (1). <IMAGE>

Description

A PROPELLER HUB ASSEMBLY This invention relates to a propeller hub assembly and, in particular, a propeller hub assembly which is capable of being preloaded.
In Dowty Rotol European Patent Application No.
324617 there is disclosed a propeller hub assembly having a propeller blade root assembly which comprises: - an inner race of angular contact bearings, for example ball bearings; and - an outer race of roller bearings; wherein the roller bearings have longitudinal axes of rotatIon substantially parallel to the longitudinal axis of a propeller blade mounted therein. This particular design of propeller hub was developed to provIde an assembly which cold.
whilst maintaining a stable operational base to cope with the higher sideways moments and centrifugal loadings being experienced with compositely formed propellers in particular.
Preloading of this form of propeller hub assembly is not normally carried out because of the design adaption and alteration required. The heavy preloading of the propeller hub assembly in turn prevents the individual propeller hub assemblies of a multi-engined aircraft from being synchronised and synchrophased. The problems of non-synchronised or non-synchrophased multiengined aircraft are well known in the aircraft industry.
The present invention is concerned with providing a propeller hub assembly including propeller blade root assetries which can be preloaded so enabling synchrophasing whilst maintaining the ability to cope with high sideways moments and centrifugal loadings.
In its broadest aspect the invention comprises â propeller blade hub assembly for mounting of propeller blades in propeller blade root assemblies, in which each propeller blade root assembly has a longitudinal central axis extending therethrough from the hub assembly, and comprises: - an inner race of bearings suitably orientated so as to enable preloading of the propeller blade root assembly; and - an outer race of roller bearIngs; wherein the inner and outer races are longitudinally spaced apart from one another, and the roller bearings of the outer race are positioned so that the longitudinal axes thereof are inclined outwardly with respect to the longitudinal axis of the propeller blade root assero In order to enable the bearing arranement to be preloaded without large increases in the frictional forces induced vi rotational movement of the propeller blades with respect to the propeller hub.
A propeller blade hub asse:twly made in accordance with the present invention incorporates all of the advantages, to a similar degree, associated with the hub assembly described in European Patent Application No. 324617, and detail thereof is incorporated herein by way of reference.
In addition thereto a propeller blade hub assembly made in accordance with the present invention incorporates a further advantage in that the frictional forces induced by the rotational movement of the roller bearings are greatly reduced. This enables the propeller blade root assemblies to be preloaded without the frictional forces becoming so great that they prevent the synchronising or synchrophasing of the engines of a multi-engined aircraft.
The reduction in the frictional forces induced by the rotational movement of the roller bearings results frorn the fact that the shoulder frict wr.
loads of the bearings is reduced to a minimurn.
In a preferred example of the present invention the outer race of roller bearings are inclined outwardly with respect to the longitudinal axis of the propeller blade root assembly at a shallow angle, preferably, the longitudinal axis of the roller bearings and the longitudinal axis of the propeller blade root assembly are at an angle of between 50 to 250 to one another, most preferably 100 to 200.
Preferably, the roller bearings of the outer race are slightly tapered, and when positioned in the outer race the roller bearing taper inwardly towards the propeller hub assembly.
The shallow angle at which the roller bearings are inclined to the longitudinal axis of the propeller blade root assembly provides, or enhances, the following benefits of the present invention: - sunder preloading the roller bearings refrain in contact with the race mergers in which they run at a true geometry; and - the shoulder loads exerted on the roller bearIngs are significantly reduced, for a required radial load preventing high end loading of the roller bearings and therefore keeping the frictional forces experienced during operation of the propeller hub assembly low.
The net effect of this is that lower axial preloading of the propeller blade root assembly is required to generate the required radial preload, and therefore lower frictional forces are present.
In combination with the tapered roller bearings a further benefit is experienced in that the roller bearing taper angle is correspondIngly shallow enabling the shoulder loads experienced by the roller bearings to be further reduced, and therefore keepIng down the frictional forces experienced during operation of the propeller hub assembly.
In a preferred embodiment of the present invention the inner race of bearings comprises a race of a,~lar contact bearings.
In an alternative embodiment of the present invention the inner race of bearings comprises a race of roller bearings which are inclined outwardly with respect to the longitudinal central axis, so that the longitudinal axis of the roller bearings and the longitudinal central axis of the propeller blade root assembly are inclined at an angle of between 250 and 650 to one another.
Preferably, in this alternative embodiment the roller bearings of the inner race are slightly tapered and when positioned in the outer race the roller bearings taper inwardly towards the propeller hub assembly.
In a preferred embodiment o the present invention the propeller hub assembly is 2 split hub assembly.
A p opernle hub assembly rade in accordance with the present InventIon enables the assembly to be manufactured without screw threads present in, or near, for components. Therefore, preferably, a propeller hub assembly made in accordance with the present invention contains no screw threads in or near major components.
The invention will now be illustrated by way of description of an example with reference to the accompanying drawings in which: Figure 1 shows a schematic view of a propeller hub assembly in its assembled state and made in accordance with the present invention; and Figure 2 shows the propeller hub assembly shown ifl Figure during assembly.
Now referring to Figure 1 of the drawings, there is shown a propeller blade hub assembly In its assembled state made in accordance With the -isert inentIon. The propeller blade hub assembly includes a two piece hub member 1 and a plurality of propeller blade root assemblies positioned in the propeller hub assembly, each of which propeller blade root assemblies is capable of accepting and securing in position a propeller blade 2, and has a cetral longitudinally extending axis from the centre propeller blade hub assembly.
The propeller blade root assemblies each comprise: - an inner race 3 of angular bearings 3a for example, ball bearings; and - an outer race 4 of roller bearings 4a, which roller bearings taper towards the centre of the propeller blade hub assembly.
The propeller blade 2 which can be located in the propeller blade root assembly may, for example, be a compositely formed propeller blade having a supportIng insert 5 positioned therein, and a bearing skirt 6, which act in unison to provide the compositely formed propeller blade with a solid root section capable of taking the forces which will be acting in that region during flit.
The bearing skirt 6 circumferentially surrounds the root section of the compositely formed propeller blade and includes two inserts 7, 8 of hard wearing steel material. These inserts 7, 8 act as the inner race members of the inner race 3 and the outer race 4 respectively, and are longitudinally spaced apart from one another.
Further, the propeller blade root assembly includes: - an outer race member 9 of the inner bearing positioned, and held in position, against the hub member 1; - an outer race member 10 of the outer bearing which extends outwardly from the hub member 1, and which on the outer face of the outwardly extending porticn has 2 screw threaded portion and - a preloading ring 12 which has a screw threaded portion which engages ith the screw thread portIon 11 of the outer race member 10 of the outer bearing.
The preloading ring 12 has in association therewith a lock washer 13 which is secured in position by a number of dowels 14, and which acts to prevent the outer bearing member 10 of the outer bearing from rotating during operation.
The outer race member 10 of the outer bearing is provided with a seal member 15 which sealingly engages with the hub member 1. A seal member 16 is also provided on an outwardly extending ring 17 of the bearing skirt 6 of the propeller blade 2, which seal member 16 sealingly engages with the inner facing section of the outer race member 10 of the outer bearing.
The two seal members 15 and 16 prevent ingress of unwanted material into the hub assembly as well as eg-ess or lubricant therefrom under operational conditions.
The angular bearings 3a and roller bearing 42 are mounted in respective cages 18 and 19 between the respective race members 7 and 9, and, 8 and 10.
Now referring to Figure 2 of the drawings there is shown a propeller hub assembly as described with reference to Figure 1 above, however in a partially assembled state.
The propeller hub assembly is assembled as described below: - the propeller blade having the supporting section 5 and bearing skirt 6 in position has the inner race members 7, 8 of the inner and outer races securely fitted in the bearing skirt 6; - the angular bearings 3G are fitted into the cage 18 and positioned appropriately about the root section of the propeller blade 2; - the roller bearings 4a are fitted into cage 19 and positioned approprIately about the root section of the propeller blade; the outer race member 9 of the inner race 3 is securely fixed within the hub member 1; the outer race member 10 of the outer race 4 is positioned within the propeller hub, inwardly displaced from its final working position; ; the propeller blade is now positioned in the propeller blade root assembly so that the angular bearings 3a of the inner race 3 are engaged with both the inner race members 7, 9; the outer race member 10 of the outer race is moved into its correct position se that the roller bearings e engage both of the outer race members 8, iO; and - the preloading ring i2 is tightened to the appropriate degree and then lock into position by the locking washer 13 and dowel 14.

Claims (1)

1. A propeller blade hub assembly for mounting of propeller blades in propeller blade root assemblies, in which each propeller blade root assembly has a longitudinal central axis extending therethrough from the hub assembly, and comprises: - an inner race of bearings suitably orientated so as to enable preloading of the propeller blade root assembly; and - an outer race of roller bearings; wherein the inner and outer races are longitudinally spaced apart from one another, an the roller bearings of the outer race are positioned so that the ior.ctucnal axes thereof are inclined outwardly with respect to the longitudinal axis of the propeller blade root assembly in order to enable the bearing arrangement to be preloaded without large increases in the frictional forces induced b rotational movement of the propeller blades with respect to the propeller hub.
GB9007673A 1990-04-04 1990-04-04 A propeller hub assembly Expired - Fee Related GB2244525B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9007673A GB2244525B (en) 1990-04-04 1990-04-04 A propeller hub assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9007673A GB2244525B (en) 1990-04-04 1990-04-04 A propeller hub assembly

Publications (3)

Publication Number Publication Date
GB9007673D0 GB9007673D0 (en) 1990-05-30
GB2244525A true GB2244525A (en) 1991-12-04
GB2244525B GB2244525B (en) 1994-09-21

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251896A (en) * 1990-12-05 1992-07-22 Dowty Aerospace Gloucester A propeller mounting arrangement
US5415527A (en) * 1992-10-08 1995-05-16 Dowty Aerospace Gloucester Limited Propeller assembly
WO1997006056A1 (en) * 1995-08-09 1997-02-20 Dowty Aerospace Gloucester Limited Bearing preload
WO1999008928A1 (en) * 1997-08-15 1999-02-25 United Technologies Corporation Preloaded bearing assembly for aircraft propeller blade retention
EP0822137A3 (en) * 1996-08-01 1999-03-24 The Timken Company Propeller blade root bearing assembly
FR2817233A1 (en) * 2000-11-30 2002-05-31 Roulements Soc Nouvelle Mounting for aircraft propeller blade end in hub comprise roller and ball bearings which allow end to revolve in hub chamber
US6443701B1 (en) 1999-01-29 2002-09-03 MüHLBAUER LUFTFAHRTTECHNIK GMBH Blade root for propeller and rotor blades
FR2862609A1 (en) * 2003-11-21 2005-05-27 Roulements Soc Nouvelle Blade mounting device for propeller of aircraft, has demountable flange integrated with rotating hub of propeller of aircraft to block axial displacement of conical rollers towards outer side of chamber of hub
GB2429247A (en) * 2005-08-17 2007-02-21 Hamilton Sundstrand Corp Propeller blade retention assembly
US7845910B2 (en) 2007-06-05 2010-12-07 Hamilton Sundstrand Corporation Propeller blade retention system with tapered roller bearing cartridge assemblies
DE102010060431A1 (en) 2009-11-27 2011-06-01 GE Aviation Systems Ltd., Cheltenham Prestressed propeller blade arrangement
EP2481670A1 (en) 2011-01-31 2012-08-01 Eurocopter Blade and method for manufacturing said blade
DE102013214240A1 (en) 2013-07-22 2015-01-22 Schaeffler Technologies Gmbh & Co. Kg Propeller blade bearing
CN104344930A (en) * 2013-08-05 2015-02-11 哈尔滨飞机工业集团有限责任公司 Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table
US9809299B2 (en) 2013-04-22 2017-11-07 Rolls-Royce Plc Propeller blade retention
US20220372884A1 (en) * 2021-05-24 2022-11-24 General Electric Company Preload sleeve for a collet-mounted blade dovetail

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB485102A (en) * 1936-11-13 1938-05-13 Arthur Frederick Evans Improvements in variable-pitch airscrews for aircraft
GB637238A (en) * 1947-01-20 1950-05-17 Rotol Ltd Improvements in or relating to variable-pitch propellers
GB718127A (en) * 1951-02-01 1954-11-10 Paolo Terzi Improvements in or relating to variable pitch propellers
GB2192943A (en) * 1986-07-26 1988-01-27 Rolls Royce Plc A variable pitch blade assembly

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4863352A (en) * 1984-11-02 1989-09-05 General Electric Company Blade carrying means

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB485102A (en) * 1936-11-13 1938-05-13 Arthur Frederick Evans Improvements in variable-pitch airscrews for aircraft
GB637238A (en) * 1947-01-20 1950-05-17 Rotol Ltd Improvements in or relating to variable-pitch propellers
GB718127A (en) * 1951-02-01 1954-11-10 Paolo Terzi Improvements in or relating to variable pitch propellers
GB2192943A (en) * 1986-07-26 1988-01-27 Rolls Royce Plc A variable pitch blade assembly

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251896A (en) * 1990-12-05 1992-07-22 Dowty Aerospace Gloucester A propeller mounting arrangement
GB2251896B (en) * 1990-12-05 1994-08-17 Dowty Aerospace Gloucester Propeller arrangement
US5415527A (en) * 1992-10-08 1995-05-16 Dowty Aerospace Gloucester Limited Propeller assembly
WO1997006056A1 (en) * 1995-08-09 1997-02-20 Dowty Aerospace Gloucester Limited Bearing preload
US6220820B1 (en) 1995-08-09 2001-04-24 Dowty Aerospace Gloucester Limited Bearing preload
EP0822137A3 (en) * 1996-08-01 1999-03-24 The Timken Company Propeller blade root bearing assembly
WO1999008928A1 (en) * 1997-08-15 1999-02-25 United Technologies Corporation Preloaded bearing assembly for aircraft propeller blade retention
US6015264A (en) * 1997-08-15 2000-01-18 United Technologies Corporation Preloaded retention assembly for aircraft propeller blade retention
US6443701B1 (en) 1999-01-29 2002-09-03 MüHLBAUER LUFTFAHRTTECHNIK GMBH Blade root for propeller and rotor blades
FR2817233A1 (en) * 2000-11-30 2002-05-31 Roulements Soc Nouvelle Mounting for aircraft propeller blade end in hub comprise roller and ball bearings which allow end to revolve in hub chamber
FR2862609A1 (en) * 2003-11-21 2005-05-27 Roulements Soc Nouvelle Blade mounting device for propeller of aircraft, has demountable flange integrated with rotating hub of propeller of aircraft to block axial displacement of conical rollers towards outer side of chamber of hub
GB2429247B (en) * 2005-08-17 2008-01-09 Hamilton Sundstrand Corp Propeller blade retention system
US7422419B2 (en) 2005-08-17 2008-09-09 Hamilton Sundstrand Corporation Propeller blade retention system
GB2429247A (en) * 2005-08-17 2007-02-21 Hamilton Sundstrand Corp Propeller blade retention assembly
US7845910B2 (en) 2007-06-05 2010-12-07 Hamilton Sundstrand Corporation Propeller blade retention system with tapered roller bearing cartridge assemblies
DE102010060431A1 (en) 2009-11-27 2011-06-01 GE Aviation Systems Ltd., Cheltenham Prestressed propeller blade arrangement
US9302764B2 (en) 2011-01-31 2016-04-05 Airbus Helicopters Blade and method of fabricating said blade
EP2481670A1 (en) 2011-01-31 2012-08-01 Eurocopter Blade and method for manufacturing said blade
US9809299B2 (en) 2013-04-22 2017-11-07 Rolls-Royce Plc Propeller blade retention
WO2015010691A1 (en) 2013-07-22 2015-01-29 Schaeffler Technologies Gmbh & Co. Kg Propeller blade mounting system
JP2016527135A (en) * 2013-07-22 2016-09-08 シェフラー テクノロジーズ アー・ゲー ウント コー． カー・ゲーＳｃｈａｅｆｆｌｅｒ Ｔｅｃｈｎｏｌｏｇｉｅｓ ＡＧ ＆ Ｃｏ． ＫＧ Propeller blade support device
DE102013214240A1 (en) 2013-07-22 2015-01-22 Schaeffler Technologies Gmbh & Co. Kg Propeller blade bearing
RU2652287C2 (en) * 2013-07-22 2018-04-25 Шеффлер Текнолоджиз Аг Унд Ко. Кг Propeller blade mounting system
US10322795B2 (en) 2013-07-22 2019-06-18 Schaeffler Technologies AG & Co. KG Propeller blade mounting system
CN104344930A (en) * 2013-08-05 2015-02-11 哈尔滨飞机工业集团有限责任公司 Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table
US20220372884A1 (en) * 2021-05-24 2022-11-24 General Electric Company Preload sleeve for a collet-mounted blade dovetail

Also Published As

Publication number Publication date
GB9007673D0 (en) 1990-05-30
GB2244525B (en) 1994-09-21

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PCNP Patent ceased through non-payment of renewal fee

Effective date: 20070404