US2366795A - Propeller - Google Patents

Propeller Download PDF

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Publication number
US2366795A
US2366795A US461583A US46158342A US2366795A US 2366795 A US2366795 A US 2366795A US 461583 A US461583 A US 461583A US 46158342 A US46158342 A US 46158342A US 2366795 A US2366795 A US 2366795A
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Prior art keywords
propeller
blades
annulus
view
lamoreaux
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Expired - Lifetime
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US461583A
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George R Lamorcaux
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Individual
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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
    • B64C11/001—Shrouded propellers

Definitions

  • the principal object of the present invention is to provide a propeller constructed in such a manner that substantially perfect static and dynamic balance can be obtained.
  • Figure 1 represents a side elevational view of one form of propeller showing .the blade adjustably mounted.
  • Figure 2 is a fragmentary top plan view.
  • Figure 3 is a fragmentary enlarged sectional view on the line 3-3 of Figure 1.
  • Figure 4 is a front elevational view of a. modification of the invention showing fixed blades.
  • Figure 5 is a fragmentary top plan view of the structure shown in Figure 4. a
  • FIG. 6 is a fragmentary detailed sectional view.
  • numeral 5 denotes a hub structure from which radiates a plurality of'adjustable blades 6 having conventional means for adjusting the pitch of the blades, each blade having a lubricant duct 1 therethrouzh.
  • each blade 8 At the outer end of each blade 8 is a projection 8 terminating in a pintle ,9. These pintles l are disposed into bearing formations l0 located on an annulus II.
  • the annulus II has threaded openings at the bearings III which are normal] closed by threaded plugs l2.
  • the ring I I serves to prevent any tendency of the blades to work loose in the hub 5 and also defines a support for the outer ends of the blades.
  • adjustable weight members l3 are provided on the annulus ll, each being in the form of a sleeve having a suitable detent l4;-
  • Figures 4,. 5 and 6 disclose a modification of the'lnvention. reference character to defining a hub from which rigid blades to project and are rigidly secured at their outer ends to an annulus Ila.
  • sleeve-like weight members l3a On the annulus Ha are sleeve-like weight members l3a provided with suitable detent means a which can be adjusted to achieve substantially perfect static and dynamic balance.
  • V A propeller of the character described com- GEORGE R. LAMOREAUX.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Jan. 9, 1945. G. R. ,LAMOREAUX 2,366,795
PROPELLER Filed Oct. 10, 1942 2 Sheets-Sheet 1 I ll/ Inventor 620g? Elam/15010.15
and flaw Z? M35 1945- G. R. LAMOREAUX 2,366,795
PROPELLER Filed Oct. 10, 1942 2 Sheets-Sheet 2 Inventar 'eoye Z? Lamar-sauna Jfi WW 1?. m
Patented Jan. 9. 1945 UNITED STATES PATENT OFFICE This'inventlon relates to new and useful improvements in propellers for aircraft and other vehicles.
The principal object of the present invention is to provide a propeller constructed in such a manner that substantially perfect static and dynamic balance can be obtained.
Other objects and advantages of the invention will become apparent to the-reader of the 7 following description.
In the drawings- Figure 1 represents a side elevational view of one form of propeller showing .the blade adjustably mounted.
Figure 2 is a fragmentary top plan view.
Figure 3 is a fragmentary enlarged sectional view on the line 3-3 of Figure 1.
Figure 4 is a front elevational view of a. modification of the invention showing fixed blades.
Figure 5 is a fragmentary top plan view of the structure shown in Figure 4. a
Figure 6 is a fragmentary detailed sectional view.
Referring to Figures 1, 2 and 3, it can be seen that numeral 5 denotes a hub structure from which radiates a plurality of'adjustable blades 6 having conventional means for adjusting the pitch of the blades, each blade having a lubricant duct 1 therethrouzh.
At the outer end of each blade 8 is a projection 8 terminating in a pintle ,9. These pintles l are disposed into bearing formations l0 located on an annulus II. The annulus II has threaded openings at the bearings III which are normal] closed by threaded plugs l2.
Obviously, the ring I I serves to prevent any tendency of the blades to work loose in the hub 5 and also defines a support for the outer ends of the blades.
, In order to achieve substantially perfect static and dynamic balance, adjustable weight members l3 are provided on the annulus ll, each being in the form of a sleeve having a suitable detent l4;-
Figures 4,. 5 and 6 disclose a modification of the'lnvention. reference character to defining a hub from which rigid blades to project and are rigidly secured at their outer ends to an annulus Ila.
On the annulus Ha are sleeve-like weight members l3a provided with suitable detent means a which can be adjusted to achieve substantially perfect static and dynamic balance.
While the foregoing specification sets forth the invention in specific terms, it is to be understood that numerous changes in the., shape, size and material may be resorted to without departing from the spirit and scope of the invention as claimed hereinafter.
Having described the invention, what is claimed as new is:
V A propeller of the character described com- GEORGE R. LAMOREAUX.
US461583A 1942-10-10 1942-10-10 Propeller Expired - Lifetime US2366795A (en)

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2558737A (en) * 1946-12-13 1951-07-03 Master Electric Co Rotor balancing means
US3028072A (en) * 1958-05-05 1962-04-03 Torrington Mfg Co Air impelling fan and associated part
US4109549A (en) * 1976-06-28 1978-08-29 Vincent Raymond A Dynamic balancer for rotating bodies and method of manufacturing same
US4767270A (en) * 1986-04-16 1988-08-30 The Boeing Company Hoop fan jet engine
US5011374A (en) * 1987-11-17 1991-04-30 General Electric Company Method and apparatus for balancing turbine rotors
US5044884A (en) * 1989-09-05 1991-09-03 Trustees Of The University Of Pennsylvania Safety propeller
US5380156A (en) * 1993-04-12 1995-01-10 Iacovino; Robert Ceiling fan balance apparatus
US5415524A (en) * 1993-06-01 1995-05-16 Gamble; Christopher L. Fluid propulsion device
US5620153A (en) * 1995-03-20 1997-04-15 Ginsberg; Harold M. Light aircraft with inflatable parachute wing propelled by a ducted propeller
US5988978A (en) * 1997-12-18 1999-11-23 Hunter Fan Company Method and apparatus for balancing a ceiling fan
US20020168266A1 (en) * 1999-05-21 2002-11-14 David Reinfeld Vortex attractor without a backplate
US20060067826A1 (en) * 2004-09-30 2006-03-30 Valeo Electrical Systems, Inc. Cooling fan for vehicles
US20110027085A1 (en) * 2009-07-30 2011-02-03 Glasspoole David F Axial balancing clip weight for rotor assembly and method for balancing a rotor assembly
US20110078901A1 (en) * 2009-10-01 2011-04-07 Glasspoole David F Radial balancing clip weight for rotor assembly
US20160176532A1 (en) * 2014-12-22 2016-06-23 Airbus Operations (Sas) Propeller for an aircraft turbomachine, including a blade retaining structure through which the aerodynamic part of each blade passes
FR3030445A1 (en) * 2014-12-22 2016-06-24 Airbus Operations Sas AIRCRAFT TURBOMACHINE PROPELLER, COMPRISING A BLADE RETENTION STRUCTURE CONNECTED TO THE EXTERNAL RADIAL END OF EACH BLADE
US20160363050A1 (en) * 2015-06-10 2016-12-15 General Electric Company Pitch change mechanism for shrouded fan with low fan pressure ratio

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2558737A (en) * 1946-12-13 1951-07-03 Master Electric Co Rotor balancing means
US3028072A (en) * 1958-05-05 1962-04-03 Torrington Mfg Co Air impelling fan and associated part
US4109549A (en) * 1976-06-28 1978-08-29 Vincent Raymond A Dynamic balancer for rotating bodies and method of manufacturing same
US4767270A (en) * 1986-04-16 1988-08-30 The Boeing Company Hoop fan jet engine
US5011374A (en) * 1987-11-17 1991-04-30 General Electric Company Method and apparatus for balancing turbine rotors
US5044884A (en) * 1989-09-05 1991-09-03 Trustees Of The University Of Pennsylvania Safety propeller
US5380156A (en) * 1993-04-12 1995-01-10 Iacovino; Robert Ceiling fan balance apparatus
US5415524A (en) * 1993-06-01 1995-05-16 Gamble; Christopher L. Fluid propulsion device
US5620153A (en) * 1995-03-20 1997-04-15 Ginsberg; Harold M. Light aircraft with inflatable parachute wing propelled by a ducted propeller
US5988978A (en) * 1997-12-18 1999-11-23 Hunter Fan Company Method and apparatus for balancing a ceiling fan
US6960063B2 (en) * 1999-05-21 2005-11-01 Vortexhc, Llc Vortex attractor without a backplate
US20020182077A1 (en) * 1999-05-21 2002-12-05 David Reinfeld Vortex attractor with propellers
US20020168266A1 (en) * 1999-05-21 2002-11-14 David Reinfeld Vortex attractor without a backplate
US20060067826A1 (en) * 2004-09-30 2006-03-30 Valeo Electrical Systems, Inc. Cooling fan for vehicles
US7189061B2 (en) * 2004-09-30 2007-03-13 Valeo Electrical Systems, Inc. Cooling fan for vehicles
US8353670B2 (en) 2009-07-30 2013-01-15 Pratt & Whitney Canada Corp. Axial balancing clip weight for rotor assembly and method for balancing a rotor assembly
US20110027085A1 (en) * 2009-07-30 2011-02-03 Glasspoole David F Axial balancing clip weight for rotor assembly and method for balancing a rotor assembly
US20110078901A1 (en) * 2009-10-01 2011-04-07 Glasspoole David F Radial balancing clip weight for rotor assembly
US8631578B2 (en) 2009-10-01 2014-01-21 Pratt & Whitney Canada Corp. Radial balancing clip weight for rotor assembly
US20160176532A1 (en) * 2014-12-22 2016-06-23 Airbus Operations (Sas) Propeller for an aircraft turbomachine, including a blade retaining structure through which the aerodynamic part of each blade passes
FR3030444A1 (en) * 2014-12-22 2016-06-24 Airbus Operations Sas AIRCRAFT TURBOMACHINE PROPELLER, COMPRISING A BLADE RETENTION STRUCTURE CROSSED BY THE AERODYNAMIC PART OF EACH BLADE
FR3030445A1 (en) * 2014-12-22 2016-06-24 Airbus Operations Sas AIRCRAFT TURBOMACHINE PROPELLER, COMPRISING A BLADE RETENTION STRUCTURE CONNECTED TO THE EXTERNAL RADIAL END OF EACH BLADE
US9902501B2 (en) * 2014-12-22 2018-02-27 Airbus Operations (Sas) Propeller for an aircraft turbomachine, including a blade retaining structure through which the aerodynamic part of each blade passes
US20160363050A1 (en) * 2015-06-10 2016-12-15 General Electric Company Pitch change mechanism for shrouded fan with low fan pressure ratio
US9963981B2 (en) * 2015-06-10 2018-05-08 General Electric Company Pitch change mechanism for shrouded fan with low fan pressure ratio

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