US1788263A

US1788263A - Variable-pitch propeller

Info

Publication number: US1788263A
Application number: US354597A
Authority: US
Inventors: William S Williams
Original assignee: Individual
Current assignee: Individual
Priority date: 1929-04-12
Filing date: 1929-04-12
Publication date: 1931-01-06
Anticipated expiration: 1948-01-06

Description

Jan. 6, 1931. w. s. WILLIAMS 1,788,263

VARIABLE PITCH PROPELLER Filed April 12, 1929 2 Sheets-Sheet 1 ill/02%] Wzzzzm A: Wllz'ams,

INVENTOR WITNESS: ATTORNEY Jan. 6, 1931. w. s. WILLIAMS VARIABLE PEIITCH PROPELLER Filed April 12, 1929 2 Sheets-Sheet 2 I zany,

INVENTOR Will William ATTORNEY WITNESS:

Patented Jan. 6, 1931 UNITED STATES WILLIAM S. WILLIAMS, SAN LUIS OBISPO, CALIFORNIA VARIABLE-ZPITCH rnorELLEa Application filed April 12, 1929. Serial No. 354,597.

This invention relates to mountings for propeller blades and the like.

An object of the invention comprehends twist mountings for the blades whereby the latter in and of themselves will var their own pitch commensurate with the riving velocity and centrifugal force attained.

Another object of the invention contem plates means for retracting the blades when I the velocity and centrifugal force is decreased.

More specifically stated the twist mountings and retracting means are separated by bearing members to relieve binding action therebetween.

With the above and other objects in view,

the invention further consists of the following novel features and details of construction, to be hereinafter more fully described, illustrated in the accompanying drawings and pointed out in the appended claim.

In the drawings Figure 1 is an elevation of my improved type of propeller.

Figure 2 is a fragmentary longitudinal sectional view taken therethrough.

Figure 3 is a horizontal sectional view taken on line 33 of Figure 2.

Figure l is a detail sectional view taken on line :4-4 of Figure 2 and illustrating the connection of the blades with the twist mountings.

Figure 5 isa view similar to Figure 2 illustrating the extended position of one of the blades when the twist mountings are called into use.

Referring to the drawin s in detail, wherein like characters of re erence denote corresponding parts, the reference character 0 10 indicates generally the hub for the propeller in the nature of a drum and having closure plates 11 upon the sides thereof. Annular shoulders, provided upon the inner sides and adjacent the peripheries of the closure plates 11, are adapted to accommodate the peripheral edges of the drum, substantially as illustrated in Figures 2, 3 and 5 of the drawings. The closure plates 11 are furthermore provided with central apertures 13 adapted to accommodate the forwardly projecting end of a crank or other shaft, not shown. Fastenlng elements 14 are employed to oin the closureplates and drum and to prevent weaving action of the completed structure.

Sleeve members 15, laterally projected in oppositely disposed relation upon diametrically opposite sides of the drum, are interiorly threaded, as indicated at 16, to accommodate the squared spirally arranged threads 17 upon the innermost projecting ends of shaft members 18. The outermost ends of the shaftv members are projected within openings 19 axially aligned with the longitudinal centers of blade members 20 and upon the innermost ends thereof. The openings 19 are centrally located within socket openings 21 in the aforementioned ends of the blades 20 and which accommodate the outermost projecting ends ofthe sleeves 15 in the manner illustrated in Figures 2 and 5 of the drawmgs.

Reduced extensions 22, formed upon the in nermost ends of the shaft members 18 within the drum 10, are adapted to carry bearing members 23 which abut the shoulder portions defined between the shaft members proper and said extensions. Collars, such as indicated at 24, lying flush against the bearing members 23, are adapted to receive the innermost end convolutions of compression springs 25 within seats 26 formed within the outer sides thereof, the springs 25 having contacting engagement at their opposite and outer ends with the inner side walls of the drum.

Cross pins 27, horizontally disposed through the innermost ends of the blades 20, are adapted for spaced intersecting relation within the outermost ends of the shaft members 18 within the openings 19.

At the outset, I desire to make it clear that I do not limit myself to the embodiment of the invention shown, for aeroplanes, inasmuch as the present construction could be effectively employed upon fan members for the cooling systems of internal combustion engines, screw propellers etc.

In the application of the resent invention upon the hub constructions or aeroplane propellers, it is to be noted that initially, the

2 memes two blades are disposed nearly straight tions of the sliaft members within the hub whereby the pllots mechamcmn may stand and having contacting engagement at the o directly in front of the propeller to crank same instead of standing to one side of the blades and re uire a helper to grasp his other hand and pul him out of the way when the blade is pushed down and the motor kicks over.

At idling speed, the springs will be strong enough to prevent changing of the blade pitch and the entire fuselage will remain stationary.

When taking off, the motor is accelerated to greater than that of idlin s eed while taxiin down the runway and t e centrifugal orce attained through the velocity of the engine crank shaft will cause the shaft members 18 in conjunction with the blades 20 to twist and move outwardlyagainst the compression of the springs 25. The greater the velocity, the greater the centrifugal force and greater the pitch of the blades with resulting acceleration of speed.

When employed'for automobile use, that is, for the cooling systems therefor, it is to be noted that the advanced speed of the motor will in turn increase the pitch of the fan blades whereby more air will be drawn and thrown against the engine commensurate with the speed.

In either case, whether the invention is employed upon the blades for aeroplanes or for the cooling systems of internal combustion engines, it is noted that overheating of the engines incident to acceleration will be avoided inasmuch as in the instance of aeroplane use, the changing of the blade members will increase the speed which could not ordinarily be attained unless the motor was actuated more R. P. M.; whereas greater draft would be developed upon the increased acceleration of the internal combustion engine.

The invention is susceptible of various changes in its form, proportions and minor details of construction, and the right is herein reserved to make such changes as properly fall within the scope of the appended claim.

Havin described the invention, what is claimed 1s:

A propeller construction comprising a hub having sleeve members laterally pro'ecting in oppositely disposed relation upon iametrically opposite sides thereof, shaft members spirall threaded within the bores of the sleeves, blade members having openings within their innermost ends to accommodate the outwardly projecting ends of the shaft members, said blades being further provided with socket openings within their innermost ends adapted to receive the outwardly rojectin ends of the sleeves, bearing mem ers carri shaft members within the hub, collars arranged upon each of the bearing members, and compression springsencircling those porupon theinnermost free ends of the osed end convolutions thereof with the co ers and adjacent portions of the sleeves.

In testimony whereof I aflix m signature. 7o

WILLIAM S. WI LIAMS.