US1517461A

US1517461A - Pump

Info

Publication number: US1517461A
Application number: US251070A
Authority: US
Inventors: Hugh A Robinson
Original assignee: Aeromarine Plane & Motor Co In
Current assignee: Aeromarine Plane & Motor Co In; Aeromarine Plane & Motor Co Inc
Priority date: 1918-08-23
Filing date: 1918-08-23
Publication date: 1924-12-02
Anticipated expiration: 1941-12-02

Description

Dec. 2, 1924-A 1,517,461

H. A. ROBINSON PUMP Original Filed Aug. 23, 1918 #www Patented Een 2, i924.

narran stares earner aerien.

HUGH A.. ROBINSON, OF KEYPORT, NEW 3ER-SES?, ASSIGNOR TO AEROMARINE PLANE @a MOTOR CO, INC., A GO'RORA'IIGN 'OF NEW YORK.

EUMP.

Application filed August 23, 191.8, Serial No. 251,070 Renewed April 28, 1924.

To all ywhom it may cm2-cern.' c

Be it known t-hat I, InIUGr-r A. ROBINSON, a citizen of the United States, residing at Keyport, in the county of Monmouth and State of New Jersey, have invented certain new and useful Improvements in Pumps, of which the following isa specification, reference being had therein to the accompanying drawing.

rIhe invention relates to wind-operated pumps of the class of gasoline-pumps used on aircraft, and the object is to provide a pump of this nature characterized by great simplicity, reliability and durability.

In the accompanying drawings, I have illustrated in Fig. 1 in perspective partly broken away and partly in cross-section, a suitable form of pump embodying an application of my invention. Fig. 2 is a crosssection through. the upper part of Fig. 1, and Fig. 8 is an enlarged sectional detail showing the method of mounting the gears.

4t indicates a suitable bracket by which the pump is attached to an aeroplane, dirigible or other vehicle adapted to travel through the air. The onrushing atmosphere acts upon the hemispherical anemometer cups 5 upon the ends of the arms 6 which are mounted upon the shaft 7 which passes through the tubular casing 8. Said shaft is enlarged at the bottom and top as indicated at 9-9, leaving asnbstantial clearance 10 forming a deep annular reservoir between said shaft 7 and the shell 8, which may be replenished occasionally with grease or tallow from the cup 11 secured to the casing in communication with the reservoir. The upper end of this shaft passes through the bottom of the gear casing 12 which is recessed to receive the hardened steel washer 13 over which is secured the gear 14. upon the end of said shaft 'i'. This gear meshes with the gear 15 upon the shaft 7 and the casing 12 is formed with the passagesl-l. The gasoline or oil is drawn into the passage 15 by the action of the gears from which point it is passed by the gears through the outlet 16 to the engine. The pin 17 is preferably passed through the washer into the plate 12 to prevent the wear of the plate, thus any wear is taken up by the gear which may be renewed.

With this arrangement a constant pu1nping of gasoline is provided while the plane is in movement or the engine is in operation,

the back draft from the propeller serving to keep the pump in operation even though the plane or other vehicle is standing still and the arrangement provided is so simple of construction and few of parts as to insure against getting out of order.

The aneinoineter motor has a comparatively narrow range of speeds for diderent speeds of flight, so that the pump is never driven at destructive speeds on the one hand, or on the other hand ever operated at so low a speed as to fail to deliver the requisite quantity of gasoline or oil. Atvthe speeds at which the gear-pump element is driven by the direct-connected anemometer it is exceptionally durable and does not cut out in the presence of gasoline. The pump therefore remains positive in its action, and it is not subject to leakage. Further advantages are lightness, and the capability of the device of being placed in a variety of positions on the plane with equal efficiency of operation. The gasoline from the interior of the casing works into the lubricating material in the reservoir 10, dissolving it gradually and causing it to reach the gears, which are thereby lubricated. In this way an automatic reservoir diffusion feed is provided, which enables the pump to operate without injury or attention over long flights, and which as an element of an aviation pump is very simple, compact and light.

Of course it will be understood that various modifications may be made in the construction and arrangement of parts without departing from the spirit of the invention as claimed.

I claim:

1. A pump suitable for supplying gasoline to a moving engine so as at all speeds to supply its needs, comprising a casing with inlet and outlet ports, intermeshing gears nested in the casing; a spindle for one of the gears, and an anemometer connected to the spindle to operate the same whereby the pump will be operated at low speeds of translation of thev engine but the range of speed at which it is driven will be kept within desirable limits notwithstanding high speeds of translation of the engine.

2. A pump for supplying gasoline to a moving engine so as at all speeds to supply its needs to the' engine, comprising a casing with inlet and outlet ports, interineshing gea-rs nested in the casing; a spindle for one oithe gears, an aneznoineter connected to the spindle to operate thesaine whereby the pump will be operated at low Speeds of translation of the engine but the range of speed at which it is driven will be kept within desirable limits notwithstanding excessive speeds of translation of the engine, and lubricating ineans around the spindle, there being a communication between the gasoline passed through the puinp and the lubricant.

3. A pump for supplying gasoline to an aircraft engine, comprising a horizontal cas ing with inlet and outlet ports, horizontal gears resting on the bottoni of the casing, a vertical spindle for one oit the gears and an aneinoineter on the spindle to operate the saine whereby the puinp will be operated at all speeds of the engine but the rangel of speed at which it is driven will be kept within desirable limits notwithstanding high speeds of motion oi the aircraft.

4L. A pump of the class described comprising zi casing having a gear-case part and a tubular part, meshing gear-pump members in said gear-oase part, a driving shatt in said tubular part connected-to one oit said gear members, and an aneinoineter wind-inotor for driving said shaft, there being formed between said shaft and tubular casing part an elongated annular reservoir into which the liquid troni the gear-case part can pene-- trate to carry lubricant gradually by ditfusion to the gear ineinbers.

In testimony whereof hereunto attix in v signature in the presence of two witnesses HUGH Si. ROBINSON.

Titnesses DAvID H. DoUGLAss, THOMAS A. HILL.