US2156103A - Spraying device for airplane propellers - Google Patents

Description

April 25, 1939. H. D. AUSTIN SPRAYING DEVICE FOR AIRPLANE PROPELLEHS Filed Dec. 27, 1935 2 Sheets-Sheet 1 gMM.

ATTORNEY April 25, 1939. H. o. AUSTIN SPRAYING DEVICE FOR AIBPLANEPROPELLERS 2 Sheets-Sheet 2 Filed Dec. 27, 1935 HFRVFY D HUSTIN Gum Patented Apr. 25, 1939 sraarmc DEVICE raorsunas Austin, Akron, Ohio, assignor to Bendix Corporation, a corporation of Dela- Harvey D.

Aviation ware FOR AIRPLANE Application December 27, 1935, Serial No. 56,825

Claims.

This invention relates to aircrafts and more particularly to propellers for aircrafts. As well known, propellers for airships and planes are designed to fit therequirements of the airorafts,

5 such as their speed, the R. P. M. and H. P. of

their engines, etc. These requirements necessitate a predetermined pitch of the propeller blades, generally called the geometric pitch and proportionate to the effective pitch, which latter in pitch includes the slip ratio of the propeller per revolution. It is also,known, that a change of the pitch of the propellerunbalances the aircraft by changing its thrust and rolling moments. Undesirable changes in the pitch of a. it propeller are often caused by the formattion of icelayers on the propeller blades during cold weather and storms, particularly, when the propeller is made of metal, such as steel, duralumin, etc.

It is the primary object of this invention to provide a propeller with means adapted to prevent the formation of ice-layers on its blades and dissolve ice-layers previously formed or while being formed.

Another object of the invention is the provision of a propeller with means adapted to discharge an anti-freeze liquid upon the propeller blades, so as to prevent the formation of icelayers on the blades.

A further object of the invention is the provision of a propeller with liquid discharge means adapted to be controlled for selectively discharging an anti-freeze liquid upon the propeller blades, so as to prevent the formation of ice- 35 layers on the blades of the propeller.

In addition the invention has other marked improvements and superiorities, which radically distinguish it from presently known structures. These improvements or superior characteristics 40 embodying certain novel features of construction are clearly set forth in the appended claims, and a preferred form of-embodiment of the invention is hereinafter shown with reference to the accompanying drawings, forming part of the 5 specification.

In these drawings:

Figure l is a perspective View of an airplane embodying a propeller and means for preventing ice formation on the propeller blades, all in 50 accordance with the invention.

Figure 2 is an enlarged transversal sectional view through the head of the propeller of the airplane shown in Fig. 1, the fuselage and the motor being shown diagrammatically, and the 55 section being taken on line 2-4 of Figure 3.

the propeller head shown in Figure 2, the section being taken on line 1-4 of Figure 2.

Figure 5 is a cross sectional view through the head of the propeller when disconnected from the crank shaft of the engine, the section being taken on line 55 of Figure 4.

Figure 6 is a side view of a propeller head, similar to the propeller head shown in Figure 2 t0 5, this propeller head being in communication with a liquid storage tank, adapted to feed an anti-freeze solution to the head.

Figure 'l is an enlarged transversal sectional view through the head shown in Figure 6, the

view disclosing the feeding of the antifreeze solution to the revolving head.

Figure 8 is a cross sectional view taken on line 8-8 of Figure 'l, and

Figure 9 is a cross sectional view taken on line 99 of Fi e '7.

Referring more particularly to the drawings reference numeral 2 represents an airplane of standard construction embodying a propeller 3, secured to the crank shaft 4 of an engine 5. The propeller 3 has rigidly or rotatably secured to its hubmember 6 two blades I and 8, and

the hubmem er being secured to the crank shaft 4 in any suitable manner.

The hubmember B is partly enclosed by a substantially cone-shaped, preferably cast, liquid storage member 9, which member is splined to the crank shaft 4. Thus the liquid storage member 9 is diametrically recessed to form a w member 6, so as to and ii into proximity of the base l2 of the liquid ide channel II for the hubbring the propeller blades I storage container or member 9. The member ll embodies a central, grooved sleeve portion ll, which portion extends from the bottom wall ii of channel ii to and through the base l2 and thus permits of sleeving the liquid storage mem-- her 9 upon the splined crank shaft 4. A packing ring it in a smiling box I'I prevents liquid from escaping through the grooves it of the sleeve portion it. This sl eeve portion is perforated at 22 at the front en d of the shaft 4 closes the m is at rest, and permit of discharge of a fine stream of liquid upon the blade. when the propeller is rotating and the liquid in the liquid storage member 8 is under the influence of centrifugal forces. A plate 25 attached to the storage member 9 by 15 screws 26, arranged at opposite sides of the channel II, bridges the hubmember I and reenforces the front end of the container 8.

When the propeller and the liquid storage member are rotated, then the antifreeze liquid in the 20 storage member is forced under the centrifugal forces outwardly and forcibly discharged through the spouts 23, 23' until the vacuum created in the storage member balances the centrifugal forces, which act upon the liquid in said storage member '25 and force the liquid through the spouts. At this time a further discharge of liquid through the spouts 23, 23' is impossible, however such a discharge of liquid can easily be effected. Thus a slight throttling of the engine will decrease the rotary speed of the engine and therewith the centrifugal force acting upon the liquid in the storage member 9, and then the atmospheric pressure will force air through the spouts 23, 23' into the storage member. An increase in the rotary speed of the engine will step up the centrifugal forces acting upon the liquid and therefore effect a new discharge of liquid until the vacuum in the storage member again balances the centrifugal forces acting upon the liquid. I In this way the operator may readily control the amount of liquid to be discharged from the storage member 9.

In the structure shown in Figures 6 to 9 the storage member 8 is coupled and communicates with a tank 21, having an antifreeze liquid stored therein. Preferably the liquid in tank 21 is under pressure to more readily feed liquid into the storage member 9. A valye member 28 in a pipe line 28 controls the feed of liquid from the tank 21 to the storage member 8, and a valve 30 in a pressure line 3| controls the amount of pressure acting upon the liquid in the tank 21'. The liquid, discharged from the tank 21 into the line 28 flows into a housing 32, which housing is preferably secured to the motor block. This housing communicates through a longitudinal bore 33 and crossbores 34, 35 in the crank shaft I with the container or storage member 8, from where the liquid is discharged in the manner described above.

Having thus described my invention:

What I claim is:

1. In an aircraft an engine, a propeller secured to the engine for rotation thereby, a liquid storage means adapted to be secured to said engine, and liquid supply means communicating between the storage means and to the blades of said propeller, said liquid supply means being adapted to feed an anti-freeze liquid from said storage means to the blades of said propeller.

2. In an aircraft an engine, a propeller including blades having front and rear faces secured to said engine for rotation thereby, a liquid storage means associated with the engine for rotation with said propeller, and liquid leads extending from said storage means to the blades of said' propelier adapted to feed a liquid from said storage means to the front faces of the blades of said propeller.

3. In an aircraft an engine having a driving shaft, a propeller having blades including front and rear faces secured to said shaft, a circular liquid storage member secured to said shaft behind said propeller and adjacent thereto, and liquid guiding means extending from the periphery of said storage member to the blades of said propeller opposite the front faces thereof, said liquid guiding means being adapted to spray an anti-freeze liquid upon the blades of said propeller during its rotation.

4. In an aircraft an engine having a main shaft, a propeller including blades having front faces secured to said shaft, a cone-shaped liquid storage member adapted to be secured to said shaft behind and adjacent to said propeller, and tubular liquid guiding means extending from the periphery of said storage member to the blades of said propeller opposite the front faces thereof,

said liquid guiding means being adapted to spray an anti-freeze liquid upon the blades of said propeller, when liquid is discharged by centrifugal force from said storage member into said liquid guiding means. a a

5. The invention described in claim 4, wherein the cone-shaped liquid storage member is diametrically recessed to permit of the inner ends of the blades of said propeller being brought into proximity of the peripheral edge of said chamber.

6. The invention described in claim 3, wherein the circular liquid storage member embodies a central sleeve portion extending through said chamber, to permit of said storage member being sleeved upon and secured to the main shaft of said engine, and wherein said sleeve portion and said shaft communicate with each other through bores, one of said bores extending longitudinally through said shaft to the front end thereof to permit of filling of said storage member at the exposed front end of said main shaft. 'l. The invention described in claim 4, wherein the outlets of said tubular guiding means are of capillary size to prevent leakage of liquid from said storage member, when said storage member is not rotating.

8. In an airplane an engine, a propeller secured to said engine for rotation thereby, means adapted to be secured to said engine for rotation with said propeller and adapted to feed an anti-freeze liquid to the blades of said propeller, and storage means for said liquid communicating withsaid first named means and adapted to feed an antifreeze liquid to said first means.

9. In an aircraft an engine having a main shaft, a propeller secured to said main shaft, a circular centrally sleevedliquid discharge memher having its sleeve portion perforated and secured to said shaft behind said propeller, liquid guiding means extending from the periphery of said discharge means to the blades of said propeller, stationary storage means for an antifreeze liquid in communication with said discharge means, and means associated with said engine and shaft adapted to effect communication between said stationary storage means and cascade with the periorations in the sleeve portion of said discharge means.

11. In an aircraft embodying an engine the combination of a propeller with liquid storage and discharge means, said propeller and said means being adapted to be secured to said engine ior joint rotation, and said discharge means being adapted to discharge anti-freeze liquid upon the blades of said propeller, when said means and said propeller are rotating.

12. In an aircraft having a propeller, power a means to drive the propeller, eentrifugally acon the propeller,

, It is hereby certified that 14. In an aircraft, a propeller having blades, power means associated with the propeller to drive the aircraft, and centrifugaliy actuated means associated with the propeller to prevent the pitch of the blades from changing due to the formation of ice thereon, and manually operable means to control said centrifugally actuated means.

15. In an airplane including a propeller having blades, variable speed power means to rotate the propeller, a reservoir for anti-freeze liquid rotatable with the propeller, means including ducts interconnecting the reservoir and blades of the propeller to transfer the anti-freeze liquid from the reservoir to the blades, said reservoir being otherwise closed to the atmosphere in the vicinity of the propeller, the quantity of liquid discharged from the reservoir to the blades being controlled by the relation between the cen trifugal force due to the rotation of the propeller and reservoir and the negative pressure created within the reservoir due to the discharge of anti-freeze liquid therefrom, and means to control the pressure within said reservoir.

HARVEY D. AUSTIN April 25, 1939.

HARVEY D. AUSTIN.

error appears in the printed specification or the above nmnbered patent requiring correction follows: Page 1, first column, line 15, for "formattion" read formation; page 2, first column, line 66, claim 1, strike out the word "to"; andsecond column, line k9,

claim 8, for Y'airplane' rend aircraft; and that the said Letters Patent should be read with this correction therein that the same may conform to the record of the case in the Patent Office- Signed ma sealed this 12th day of Mai-en, A. 1). 191,0.

sum

em vain Airedale, acting Gouni seioner ot. Patentscascade with the periorations in the sleeve portion of said discharge means.

11. In an aircraft embodying an engine the combination of a propeller with liquid storage and discharge means, said propeller and said means being adapted to be secured to said engine ior joint rotation, and said discharge means being adapted to discharge anti-freeze liquid upon the blades of said propeller, when said means and said propeller are rotating.

12. In an aircraft having a propeller, power a means to drive the propeller, eentrifugally acon the propeller,

, It is hereby certified that 14. In an aircraft, a propeller having blades, power means associated with the propeller to drive the aircraft, and centrifugaliy actuated means associated with the propeller to prevent the pitch of the blades from changing due to the formation of ice thereon, and manually operable means to control said centrifugally actuated means.

15. In an airplane including a propeller having blades, variable speed power means to rotate the propeller, a reservoir for anti-freeze liquid rotatable with the propeller, means including ducts interconnecting the reservoir and blades of the propeller to transfer the anti-freeze liquid from the reservoir to the blades, said reservoir being otherwise closed to the atmosphere in the vicinity of the propeller, the quantity of liquid discharged from the reservoir to the blades being controlled by the relation between the cen trifugal force due to the rotation of the propeller and reservoir and the negative pressure created within the reservoir due to the discharge of anti-freeze liquid therefrom, and means to control the pressure within said reservoir.

HARVEY D. AUSTIN April 25, 1939.

HARVEY D. AUSTIN.

error appears in the printed specification or the above nmnbered patent requiring correction follows: Page 1, first column, line 15, for "formattion" read formation; page 2, first column, line 66, claim 1, strike out the word "to"; andsecond column, line k9,

claim 8, for Y'airplane' rend aircraft; and that the said Letters Patent should be read with this correction therein that the same may conform to the record of the case in the Patent Office- Signed ma sealed this 12th day of Mai-en, A. 1). 191,0.

sum

em vain Airedale, acting Gouni seioner ot. Patents-

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