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US999992A - Propeller for aeroplanes. - Google Patents

Propeller for aeroplanes. Download PDF

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Publication number
US999992A
US999992A US56128710A US1910561287A US999992A US 999992 A US999992 A US 999992A US 56128710 A US56128710 A US 56128710A US 1910561287 A US1910561287 A US 1910561287A US 999992 A US999992 A US 999992A
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United States
Prior art keywords
propeller
blades
rods
aeroplanes
spoke
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Expired - Lifetime
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US56128710A
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Thaddeus Sidney Harris
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Individual
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Priority to US56128710A priority Critical patent/US999992A/en
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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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical
    • B64C11/34—Blade pitch-changing mechanisms mechanical automatic
    • B64C11/343—Blade pitch-changing mechanisms mechanical automatic actuated by the centrifugal force or the aerodynamic drag acting on the blades

Definitions

  • Patented Au fs, 1911 Patented Au fs, 1911.
  • FIG. 1 is a longitudinal sectiouof a propeller constructed in accordance with the present invention
  • Fig. 2 is a cross section taken on the line 22 in Fig. 1, of the driving shaft, showing in rear elevation one of the propeller blades, and supporting and operating means connected therewith;
  • Fig. 1 is a longitudinal sectiouof a propeller constructed in accordance with the present invention
  • Fig. 2 is a cross section taken on the line 22 in Fig. 1, of the driving shaft, showing in rear elevation one of the propeller blades, and supporting and operating means connected therewith
  • Fig. 1 is a longitudinal sectiouof a propeller constructed in accordance with the present invention
  • Fig. 2 is a cross section taken on the line 22 in Fig. 1, of the driving shaft, showing in rear elevation one of the propeller blades, and supporting and operating means connected therewith
  • Fig. 3 is a longitudinal section of the driving shaft and of the sleeye and thimble forming the'bearing for the control of the propeller, taken on the line 33 in Fig; 2, and Fig. 4 is a cross section of one of the propeller blades taken on theline 44 in Fig. 2.
  • a driving shaft 5 is suitably mounted in abearing collar 6, mounted in a frame work 7 of any usual type of aeroplane.
  • the sleeve 9 is vided at or near the outer end thereof with perforations tapered and alined to receive a taper pin' 10.
  • the taperpin 10 is driven through the said perforations in the end of thesleeve 9, and through the shaft 5 in a suitable perforation formed in the end thereof, as seen in Fig. 1 of the drawings.
  • the sleeve 9 is provided with two or more boss-like extensions 11, 11.
  • the extensions 11, 11 are provided with holes screw tapped to receive the threaded ends 12, 12 of spoke rods 13,13.
  • the rods 13, 13 are p the extensions 11, 11 by lock nuts 14, 14.
  • the spoke rods 13 are constructed from hollo'w tubing of lightbut strong construction proadjusted in adapted to stand the propelling strain to which the propeller is'subjected. Slidably mounted upon the rods 13, 13 are molded or the rods 13 after the same have been extended through the sockets 16.
  • the compression of the springs 19, 19 sets the governing strain for the shift of the blades 15, 15.
  • the compression of the springs 19 is set and regulated by collars 20, 20.
  • the collars 20, 20 are held in position by connecting rods21, 21.
  • rods 21, 21 are provided with outer screw threaded ends 22, 22, which are extended through perforated ears 23, 23 and there provided with set nuts 24, 24, the screwing up of which lengthens or shortens the distance between the cars 23, 23 on the collars 20, 20, and the-pins 25, 25 which are fixedly secured to thimbles 26.
  • the compression of the springs 19 is regulated so that the force necessary for starting the shift of the blades 15, 15 is varied. It is evident that the rotation of the thimble 26 would have a similar The connecting.
  • a propeller for aeroplanes comprising a plurality of radially extended spoke rods; 'a hub for said spoke rods rigidly connected thereto; a plurality of rigid propeller blades pivotally and slidably mounted-on said'spoke rods; means embodying cam members interposed between the said spoke rods and blades and arranged to rotate thesaid blades to' extend the same transversely across the path of rotation of said propeller when the said blades are moved centrifugally on said spoke rods; and resilient members operatively connecting said slidable blades and the fixed members of said propeller to normally move said blades centripetally.
  • a propeller for aeroplanes comprising a plurality of radially extended spoke rods; ahub for said spoke rods rigidly connected thereto; a plurality of rigid propeller blades pivot-ally and slidably mounted on said spoke rods; means embodying cam members interposed between t-he said spoke rods and blades and arranged to rotate the said blades to extend the same transversely across the path of rotation of said propeller when the said blades are moved centrifugally on said spoke rods; resilient members operatively connecting said slidable blades and the fixed members of said propeller to normally move said blades centripetally; and manually operable means for varying the tension of said resilient members.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Piles And Underground Anchors (AREA)

Description

T. S. HARRIS. PROPELLEE FOR AEROPLANES. APPLICATION FILED MAY 14,1910.
Patented Au fs, 1911.
na. III
MIA/E8858:
ATTORNEYS 'TI-IADDEUS SIDNEY HARRIS, OF WAVERLY, ILLINOIS.
specification of Letters Patent.
PROPELLER FOR AEROPLANES.
Patented Aug. 8, 191-1.
Application filed May 14, 1910. Serial No. 561,287.
To all whom it may concern:
Be it known that I, THADDEUS S. HARRIS, a citizen of'the United States, and a resident of "averly, in the county of Morgan and State of Illinois, have invented a new and Improved Propeller for Aeroplanes, of which the following is a' full, clear, and exact description.
Among the principal objects which the present invention has in view are: to provide apropeller wherein the rotation of the same is automatically governed; to proy'ide means for manually controlling the adjustment of the governor; and to provide a simplitied, efiicient and durable construction for a propeller of the character specified.
One embodiment of the present invention is disclosed in the structure illustrated in the accompanying drawings, in which like characters of reference denote corresponding parts in all the views, and in which- Figure 1 is a longitudinal sectiouof a propeller constructed in accordance with the present invention; Fig. 2 is a cross section taken on the line 22 in Fig. 1, of the driving shaft, showing in rear elevation one of the propeller blades, and supporting and operating means connected therewith; Fig.
3 is a longitudinal section of the driving shaft and of the sleeye and thimble forming the'bearing for the control of the propeller, taken on the line 33 in Fig; 2, and Fig. 4 is a cross section of one of the propeller blades taken on theline 44 in Fig. 2.
A driving shaft 5 is suitably mounted in abearing collar 6, mounted in a frame work 7 of any usual type of aeroplane. The collar 6 is provided with a head 8, which forms a thrust bearing at the end for a sleeve 9 forming the hub =of the wheel-like arrangement of the propeller. The sleeve 9 is vided at or near the outer end thereof with perforations tapered and alined to receive a taper pin' 10. The taperpin 10 is driven through the said perforations in the end of thesleeve 9, and through the shaft 5 in a suitable perforation formed in the end thereof, as seen in Fig. 1 of the drawings.
The sleeve 9 is provided with two or more boss- like extensions 11, 11. The extensions 11, 11 are provided with holes screw tapped to receive the threaded ends 12, 12 of spoke rods 13,13. The rods 13, 13 are p the extensions 11, 11 by lock nuts 14, 14. The spoke rods 13 are constructed from hollo'w tubing of lightbut strong construction proadjusted in adapted to stand the propelling strain to which the propeller is'subjected. Slidably mounted upon the rods 13, 13 are molded or the rods 13 after the same have been extended through the sockets 16.
Having a construction such as shown in the accompanying drawings and herein above described. it is obvious that if the blades 15, 15 are shifted lengthwise of the extension of the rods 13 they are caused to rotate about the said rods. The grooves 17, 17 are disposed in inclined relation to the rods 13, the inclination being such that the pin 18 by its engagement with the said grooves, compels the sockets 16 in which the grooves are formed, and the blades 15, 15 connected with the said sockets, to rotate about the sockets of the said rods as the sockets and blades are'moved lengthwise of the said rods. The angle of the grooves is such that as the blades are shifted outward on the rods, the said blades are turned across the rotary path of the rods 13 or propeller.
In the operation of.) the propeller the centrifugal force due to the rotation of the propeller shifts the blades outwardly. The
blades are shifted inwardly by spiral springs 19, 19. The compression of the springs 19, 19 sets the governing strain for the shift of the blades 15, 15. The compression of the springs 19 is set and regulated by collars 20, 20. The collars 20, 20 are held in position by connecting rods21, 21. rods 21, 21 are provided with outer screw threaded ends 22, 22, which are extended through perforated ears 23, 23 and there provided with set nuts 24, 24, the screwing up of which lengthens or shortens the distance between the cars 23, 23 on the collars 20, 20, and the-pins 25, 25 which are fixedly secured to thimbles 26. By manipulating the screw nuts 24, 24 the compression of the springs 19 is regulated so that the force necessary for starting the shift of the blades 15, 15 is varied. It is evident that the rotation of the thimble 26 would have a similar The connecting.
on the hub of said propeller; connecting rods pivotally attached to said collars and said thimble, disposed on said thimble in such a manner as to extend said rods when said thimble is rotated; cam actuating means disposed between said hub and said thimble to rotate the latter when moved lengthwise'on the former; and manually operative means for shifting said thimble.
3. A propeller for aeroplanes comprising a plurality of radially extended spoke rods; 'a hub for said spoke rods rigidly connected thereto; a plurality of rigid propeller blades pivotally and slidably mounted-on said'spoke rods; means embodying cam members interposed between the said spoke rods and blades and arranged to rotate thesaid blades to' extend the same transversely across the path of rotation of said propeller when the said blades are moved centrifugally on said spoke rods; and resilient members operatively connecting said slidable blades and the fixed members of said propeller to normally move said blades centripetally.
4. A propeller for aeroplanes comprising a plurality of radially extended spoke rods; ahub for said spoke rods rigidly connected thereto; a plurality of rigid propeller blades pivot-ally and slidably mounted on said spoke rods; means embodying cam members interposed between t-he said spoke rods and blades and arranged to rotate the said blades to extend the same transversely across the path of rotation of said propeller when the said blades are moved centrifugally on said spoke rods; resilient members operatively connecting said slidable blades and the fixed members of said propeller to normally move said blades centripetally; and manually operable means for varying the tension of said resilient members.
In testimony whereof I have signed this specification in the presence of two subscribing witnesses.
THADDEUS SIDNEY HARRIS.
Witnesses:
A. C. MOFFET, WM. A. DENNIS.
US56128710A 1910-05-14 1910-05-14 Propeller for aeroplanes. Expired - Lifetime US999992A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2437330A (en) * 1944-01-24 1948-03-09 Alexander S Mullgardt Variable incidence wing control for aircraft of the rotaly wing or airplane sustained type

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2437330A (en) * 1944-01-24 1948-03-09 Alexander S Mullgardt Variable incidence wing control for aircraft of the rotaly wing or airplane sustained type

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