US1998152A

US1998152A - Variable pitch propeller mechanism

Info

Publication number: US1998152A
Application number: US624743A
Authority: US
Inventors: Zipay John Rapp
Original assignee: Individual
Current assignee: Individual
Priority date: 1932-07-26
Filing date: 1932-07-26
Publication date: 1935-04-16
Anticipated expiration: 1952-04-16

Description

April 16, 1935 J. R, IPAY 1,993,152

VARIABLE PITCH PROPELLER MECHANISM Filed July 26, 1932 INVENTOR Patented Apr. 16 1935 unrrao stares PATENT orrice John litapp Zippy, Pittsburgh, Pa.

Application July 26, race, Serial No. 624,743

(ill. 170-163) 9 Claims.

In variable pitch propellers for aeroplane and. like uses the stems of the propeller blades are usually journaled in the bores of the propeller bushing, which bushing is mounted on and dis posed transversely of the propeller shaft.

Means are usually provided whereby the pitch of the propeller blades is automatically increased with the speed of rotation of the propeller, the increase of pitch with the increasing speed of rotation being produced by the use or centrifugally acting weights which revolve'wlth the propeller. Frequently these weights are supported by arms or levers extending radially of the stems of the propeller blades and thus the weights increase the air-resistance to the rotation of the propeller, and wherever located the weights tend to destroy the balance of the propeller mechanism.

One of the objects which I have in view is to provide for the. automatic control of the variation in propeller blade pitch in accordance with the speed of rotation, without the use of weights or other like means which tend to impair or de= stroy the balance or which increase the air-resistance.

For this purpose I employ the pressure of the forced feed of oil to the motor of the aeroplane or other air craft.

In motors used for this purpose the oil is supplied under pressure to the bearings and their moving parts by an oil pump which is driven from the motor, the pump pressure increasing with the speed of the motor and consequently with the speed of rotation of the propeller.

In my invention as the oil pump pressure in creases with the speed of rotation of the propeller the pitch of the propeller blades is automatically increased and, likewise, as the speed of the motor and consequently the speed oi rotation of the propeller and also the pressure of the oil decreases the pitch of the propeller blades is likewise decreased.

I provide means whereby both the minimum and the maximum pitch of the propeller blades may be adjusted so that the greatest efiiclenoy may be obtained.

Again I provide means whereby the operator in the cockpit or control car of the air craft may at will throw the automatic pitch varying means into and out of operation while in flight.

Other novel features of construction and of ar rangement of parts will appear from the following description.

In the accompanying drawing wherein I have illustrated a practical embodiment of the principles of my invention, Fig. l is a broken plan view partially in horizontal section along the 1i 3 I-l in Fig. 2, showing the front end-of the p opeller shaft of an aeroplane, the 'partible propeller bushing and the propeller blades having their stems jaurnaled in the bores of the bushing.

nature Fig. 2 is a vertical crosssection along the line 2-2 in Fig. 1.

Fig. 3 is atvertical section along the line 3-3 in Fig. 1.

Fig. 4 is a detail partially in section of one of the head members secured to one of the propeller blade stems.

Fig. 5 is a detail in section ally operated control valve.

Fig. 6 is a diagrammatic view showing the motor, the oil pump, and the propeller of an aeroplane.

showing the manu- Referring to the drawing, i represents the propeller shaft which is driven by the motor 2 and the motor also drives the oil pump 3 which supplies oil under pressure to the moving parts.

The partible propeller bushing shown at tar-4t: is fixed on and disposed transversely to the shaft l, the, bushing parts being held together as by the clamping bands 5.

t represents the propeller blades whose stems l are journaled in the bore of the propeller bushi 8 represents heads which are provided withintegrally and axially disposed tubular necks 9 which have central axial openings i ii contracting in diameter from the outer ends of the necks and extending through the heads 8. The neclrs are split longitudinally as illustrated at it, four of said splits equally distant apart being shown.

The necks 9 are inserted in the ends of the stems l and the necks are provided with an an= till nularly arranged series of longitudinally disposed I ribs l2 which mate with slots is cut in the bores of the stems to prevent relative rotary movement between, the stems and the heads.

, It represents tapered bolts fitting the openings of the necks 9 so that when the necks have been inserted into the stems with the heads beari against or adjacent to the ends of the stems, nuts it may be screwed up tight on the threaded ends of the bolts H and against the heads, thus wedging the split necks into fixed engagement with the stems so that each of the stems and the corresponding head will rotate in unison.

Suitable locks are applied to the nuts it to prevent them from loosening.

' Each of the heads 8 is provided with a pair oi radially extending and preferably diametrically opposed fingers l6 and il. The bushing is circum= ferentially enlarged as at M to provide clearance for the heads 8 and the fingers iii and ll.

l8 and iii-represent opposed abutment bolts screwed through threaded holes in the wall of the bushing and with their inner ends disposed at either side of the lower finger it of each of the heads. By adjusting the bolts the head may be permitted the desired arc of rotary movement and consequently the degree otpitch variation.

Thus by adjusting the bolt l8 the minimum pitch of the corresponding propeller blade may be regulated and likewise the bolt it determines the maximum pitch of the blade.

it represents a helical spring mounted in a socket 2i formed in the wall of the bushing and the inner end of said spring bears against the finger ii. This spring is arranged so that it tends to rotate the head 8 to reduce the pitch of the corresponding propeller blade to the minimum determined by the adjustment of the bolt i8.

22 represents a cylinder also formed in the wall of the bushing at each enlargement 8a and opposed to the corresponding spring socket ill. The outer ends of each of the cylinders are closed and 23 represents a piston working in the cylinder and provided with a suitable packing such'as the expanding cup 2%.

25 represents a piston rod having one end pro vided with a ball 25 which is received in a cupsocket in the inner end of the piston while the other end of the rod is provided with a second ball 2'3 which is seated in a similar socket in the finger ii.

28 is an outwardly flaring hole extending from the socket through the finger and 29 is an extension of the rod working in said hole, thus preventing the rod from dropping out of place while permitting its flexible action between the piston and the finger.

As may be seen in Fig. l the arrangement of the spring and the piston is reversed in the case of the two propeller stems.

The closed ends of the two cylinders 22 are connected by passages 3E3, preferably formed in the walls of the bushing parts with longitudinal grooves 3i cut in the perimetral surface of the shaft l, and said grooves are connected by radially disposed passages 32 in the shaft with the longitudinal passage at the axis of the shaft. The outer end of said passage is closed.

The passage extends rearwardly in said shaft for a short distance and then ends or is blocked. 3 1 is a radial passage formed in the shaft and connected at its inner end with the passage A short distance in the rear of the passage 3G said shaft is provided with a second radial passage which connects at its inner, end with a second axial passage 36 whose rear end is connected with the oil pressure system of the motor.

represents a valve casing which is fixed. For instance it may be mounted on a portion of the motor frame. The casing is provided with a horizontal bore through which the shaft 11 extends, packing rings or gaskets 3% being em played to prevent the escape of oil from the valve casing along the shaft in either direction.

The casing 3? is provided with a horizontal passage dil having its ends connected by vertical portions with annular grooves ll cut in the wall of the bore ill and registering respectively with the radial passages 3 and 35 in the shaft.

12 represents a valve plug seated in a valve seat 43 which intersects the passage ll), so that the oil pressure may be admitted to the cylinders 22, be cut oil therefrom, or by a partial closing of the valve the oil pressure effective at said cylinders may be regulated.

The valve plug .82 is preferably perated from the cockpit or control station of the aeroplane or other air craft. Thus I have indicated the valve plug provided with a crank M and the lever d5 extending rearwardly past the motor 2 so that the operator may open or close or regulate the valve while the aeroplane is in flight.

it is obvious that as the speed of rota ion in= creases with the increasing speed of the motor, the oil pressure effective in the cylinders 22 will increase, thus increasing the pitch of the propeller blades, the springs 28 being compressed. Likewise as the speed of rotation of the propeller decreases with the decrease of the speed of the motor, the oil pressure effective in said cylinders will decrease and the pitch of. the propeller blades will correspondingly decrease owing to the expansion or the springs Ell.

By means of the abutment bolts is and it] the minimum pitch and the maximum pitch may be adjusted to obtain the desired efiects.

By means of the manually operated valve in the pressure supply passage, the oil pressure may be cut off from the cylinders 22 for taking ofi and/or for landing and by the adjustment of the valve any desired pressure may be rendered eifective in said cylinders.

It is obvious that my invention may be used in connection with any suitable manual control of the pitch.

I claim:-

1. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with an oil supply under pressure which varies with the speed of the motor, a shaft driven by said motor and provided with a longitudinally disposed oil passage in communication with the oil supply, a bushing fixed on and disposed transversely to said shaft, the ends of said bushing being provided with bores, propeller blades having stems journaled in said bores and arranged for rotation relative to the bushing to vary the pitch of said blades, a cylinder in said bushing adjacent each of said bores and communicating with the latter, the outer ends of each of said cylinders being connected by a passage in. the bushing communicating with the shaft passage, pistons working in said cylinders and provided with piston rods, a radially disposed finger carried by each of said stems and engaged by the piston rod of the corresponding piston, the arrangement being such that as the oil pressure increases with the increasing speed of the motor the stems are rotated to increase the pitch of the blades, and means for automatically decreasing the blade pitch as the oil pressure decreases.

2. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with an oil supply under pressure which varies with the speed of the motor, a shaft driven by said motor and provided with a longitudinally disposed oil passage in coirxnunication with the oil supply, a bushing fixed on and disposed transversely to said shaft, the ends of said bushing being provided with bores, propeller blades having stems journaled in said bores and arranged for rotation relative to the bushing to vary the pitch of said blades, a cylinder in said bushing adjacent each or" said bores and communicating with the lat er, the outer ends of each of said cylinders being connected by a passage in the bushing communicating with the shaft passage, pistons working in said cylinders and provided with piston rods, a radially disposed linger carried by each of said stems and engaged by the piston rod of the corresponding piston, the arrangement being'such that as the oil pressure increases with the increasing speed of the motor the stems are rotated to increase the pitch of the blades, and a spring working against each of said fingers and opposed to the corresponding piston whereby to decrease the blade pitch as the oil pressure decreases.

3. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with an oil supply under pressure which varies with the speed of the motor, a shaft driven by said motor and provided with a longitudinally disposed oil passage in communication with the oil supply, a bushing fixed on and disposed transversely to said shaft, the ends of said bushing being provided with bores, propeller blades having stems journaled in said bores and arranged for rotation relative to the bushing to vary the pitch of said blades, a cylinder in said bushing adjacent each of said bores and communicating with the latter, the outer ends of each of said cylinders being connected by a passage-in the bushing communicating with the shaft passage, pistons working in said cylinders and provided with piston rods, a radially disposed finger carried by each of said stems and engaged by the piston rod of the corresponding piston, the arrangement being such that as the oil pressure increases with the increasing speed of the motor the stems are rotated to increase the pitch of the blades, means for automatically decreasing the blade pitch as the oil pressure decreases, and means for regulating the oil pressure effective against the pistons.

4. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with an oil supply under pressure which varies with the speed of the motor, a shaft driven by said motor and provided with a longitudinally disposed oil passage in communication with the oil supply, a bushing fixed on and disposed transversely to said shaft, the ends of said bushing being provided with bores, propeller blades having stems journaled in said bores and arranged for rotation relative to the bushing to vary the pitch of said blades, a cylinder in said bushing adjacent each of said bores and communicating with the latter, the outer ends of each of said cylinders being connected by a passage in the bushing communicating with the shaft passage, pistons working in said cylinders and provided with piston rods, a radially disposed finger carried by each of said stems and engaged by the piston rod of the corresponding piston, the arrangement being such that as the oil pressure increases with the increasing speed of the motor the stems are rotated to increase the pitch of the blades, means for automatically decreasing the blade pitch as the oil pressure decreases, and means for limiting the increase of the blade pitch in response to increasing oil pressure.

5. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with an oil supply under pressure which varies with the speed of the motor, a shaft driven by said motor and provided with a longitudinally disposed oil passage in communication with the oil supply, a bushing fixed on and disposed transversely to said shaft, the ends of said bushing being provided with bores, propeller blades having stems journaled in said bores and arranged for rotation relative to the bushing to vary the pitch of said blades, 2. cylinder in said bushing adjacent each of said bores and communicating with the latter, the outer ends of each of said cylinders being connected by a passage in the bushing communicating with the shaft passage, pistons working in said cylinders and provided with piston rods, a radially disposed finger carried by each of said stems and engaged by the piston rod of the corresponding piston, the arrangement being such that as the oil pressure increases with the increasing pitch of the motor the stems are rotated to increase the pitch of the blades, means for automatically decreasing the blade pitch as the oil pressure decreases, means for limiting the increase of the blade pitch in response to increasing oil pressure, and means for varying the minimum pitch of the blade.

6. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with a lubricating oil supply under pressure'which varies with the speed of the motor and also having its crank shaft provided with an axial bore connected with the pressure lubricating system, a bushing fixed on the crank shaft and propeller blades having their stems journaled in the bushing, of fluid-pressure cylinder and piston mechanism carried by the bushing and connected to the stems of the propeller blades, said mechanism being connected to the bore of the shaft and arranged to increase the pitch of the propeller blades as the pressure of the lubricant in the bore increases, and means for decreasing said pitch as said pressure decreases.

7. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with a lubricating oil supply under pressure which varies with the speed of the motor and also having its crank shaft provided with an axial bore connected with the pressure lubricating system, a bushing fixed on the crank shaft and propeller blades having their stems 'journaled in the bushing, of fluid-pressure cylinder and piston mechanism carried by the bush ing and connected to the stems of the propeller blades, said mechanisms being connected to the bore of the shaft arranged to increase the pitch of the propeller blades as the pressure of the lubricant in the bore increases, and spring means engaging the pistonsand moving the same to reduce said pitch as said pressure decreases.

8. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with a lubricating oil supply under pressure which pressure varies with the speed of the motor, a bushing fixed on the crank shaft of the motor and propeller blades having their stems journaled in the ends of the bushing, of

fluid pressure cylinder and piston mechanism operatively connected to said stems for rotating the latter relative to the bushing, and direct connection between the pressure oil supply and said cylinder and piston mechanism whereby the pitch of the propeller blades is automatically coordinated with the speed of the motor.

9. In variable speed propeller mechanism for aeroplane and like uses, the combination with a motor provided with a lubricating oil supply'under pressure which pressure varies with the speed of the motor, a bushing fixed on the crank shaft of the motor and propeller blades having their stems journaled in the ends of the bushing, of fluid pressure cylinder and piston mechanism operatively connected to said stems for rotating the latter relative to the bushing, and direct connection between the pressure oil supply and said cylinder and piston mechanism whereby the pitch of the propeller blades is automatically increased as the speed of the motor increases, and 1 means for automatically decreasing said pitch as the speed of the motor decreases.

JOHN RAPP ZIPAY.