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Publication numberUS2272358 A
Publication typeGrant
Publication date10 Feb 1942
Filing date2 Dec 1940
Priority date2 Dec 1940
Publication numberUS 2272358 A, US 2272358A, US-A-2272358, US2272358 A, US2272358A
InventorsEdward C Steinhaus
Original AssigneeEdward C Steinhaus
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Airplane propeller
US 2272358 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

Feb. 10, 1942. E. c. STEINHAUS AIRPLANE PROPELLER Filed Dec. 2, 1940 Edward 6; Stel'lzham:

INVENTOR BY amyamwza.

ATTORNEYS WITNESS Patented Feb. 10, 1942 Application December 2, 1940, Serial No. 368,241

g 4 Claims. ('01. 170-172) This invention relates to airplane propellers and more particularly to those which are hollow and utilize a flow of compressed air'through ducts on the surface thereof.

In the conventional type of propeller, the high rate of speed at which the blade rotates tends to'create a vacuum or partial vacuum on its forward or low-pressure surface and the effect of this vacuum is to exert a retarding force on the rotationof the propeller.

r Various means, such 'as ridges, fins, etc. have been utilized to break up this vacuum but, so far as I am aware,

no one has as yet developed a device which makes use of a stream of compressed air which not only abolishes this vacuum but will assist the motor of the propeller as will the specific advantageous combination of elements embodied in my invention.

Said shaft is hollow, and has ducts positioned so that air may be forced bya compressor, not shown, therethrough and into the hollowblades Ill.

Positioned on the forward, or low-pressure surface of the blades are convexities l6, shaped in a backwardly tapering form similar to the back The object of this invention is to decrease the air resistance in airplane propellers.

Another object is to abolish the vacuum, which forms on the low-pressure surface of airplane propellers.

Still another object is a means of assisting the rotation of airplane propellers.

These and other objects may be accomplished by my invention which embodies among its features a propeller having hollow blades, a hollow shaft for said propeller having air ducts leading to' the interior of said blades, a plurality of convexities arranged on the forward or low-pressure surface of each blade,said congexities having a tapering shape to decrease air resistance, an air outlet positioner directly in front of each convexity and consisting of astamped-up portion of the surface of the blade, semi-circular in crosssection and directed toward the convexity so that,

when air is forced therethrough, it will overcome any vacuum and also will produce a force to augment the drive of the propeller.

Other objects and features will become evident from the following disclosure when taken in connection with the accompanying drawing in which: a

Figure l is a front elevation of a hollow propeller blade including my invention,

Figure 2 is a cross-section taken on line 2-2 of Figural, and

figure 3 is a cross-section taken on line 3-3 of Figure 2.

' Referring to the drawing in detail, my propeller consists of two hollow blades l0, each held in a socketiiby clamps' l2. ihe socket II is made integral with hub l3 which is securely fixed in conventional manner on under forced pressure therein, a plurality of con--.

of a spoon or a' drop of oil falling through air to thus minimize air resistance. The spaces be-' tween thes'e'convexities may, if desired, be slightly concave, and the convexities are positioned so that their surfaces taper. down to the trailing edge of the blade. Directly in front of the convexlties are air outlets l1 stamped out of the blade, the same being semi-circular in crosssection, as shown, and positioned to direct jets of air back over the convexities. when air is forced through the shaft l4 into the hollow blades, these backwardly directed jets not only obviate the formation of a vacuum on the-lowpressure side of the blade, but exert a considerable force to cause the .blades to rotate;

Therefore, it will be noted that I have produced a blade which can be rotated at a greater rate of speed with the expenditure ofv less horsepower and in general has greater efficiency than the blades now in use. Although a preferred embodiment is described herein I do not wish to appended claims:

What I claim is:

1. In a device of the class described, a hollow propeller blade open at one end to receive air vexities formed transversely on the low-pressure side of the said blade, the said blade having air outlet openings forwardly of the said convexities, and means projecting from the blade for directing the air escaping from the said openings toward the said convexitles.

2. In a propeller, a hollow blade open at one end for the admission of air under forced pressure, a plurality of convex protuberances formed drive shaft H. 5

on the blade, ,the said protuberances being tapered longitudinally and arranged transversely of the blade, the said blade having outlet aper-' tures adjacent the ends of the said protuberances, and projections formed on the blade partially covering the said outlet apertures and shaped to direct the air blowing outward of the apertures on to the said protuberances.

3. In a propeller. a hollow elongated blade open at its inner end for connection with a passage for supplying fluid under pressure into the bladr' a plurality of transversely disposed protuberances formed on one side of the blade, the

' said protuberances being tapered and having one end terminating at the trailing edge of the blade, the said blade having fluid discharge apertures in one side thereof immediately'forward of the discharge apertures adiacent one end of each of the protuberances, a semi-circular deflecting member formed about a portion of each aperture to direct the fluid escaping therefrom toward the protuherances, a hollow shaft having a plurality of side outlet ducts, and a plurality of radial socketsmounted on the shaft for connecting the blade to the shaft so that the inner open ends of the blade register with the ducts whereby fluid may be forced through the shaft and into the blades, and discharged through the apertures in the blades. 7


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US2522955 *14 Sep 194419 Sep 1950United Aircraft CorpMeans for heating hollow propeller blades
US2553218 *1 May 194415 May 1951Gen Motors CorpAnti-icing of variable pitch propeller blades
US2556736 *22 Jun 194512 Jun 1951Curtiss Wright CorpDeicing system for aircraft
US2800291 *20 Oct 195123 Jul 1957Stephens Arthur VeryanSolid boundary surface for contact with a relatively moving fluid medium
US4830315 *22 Dec 198716 May 1989United Technologies CorporationAirfoil-shaped body
US5110560 *25 Jul 19895 May 1992United Technologies CorporationConvoluted diffuser
US5860626 *18 Oct 199419 Jan 1999Moser; JosefSurface of a body exposed to circumfluent fluid
US5988568 *22 Sep 199723 Nov 1999Drews; Hilbert F. P.Surface modification apparatus and method for decreasing the drag or retarding forces created by fluids flowing across a moving surface
US6431498 *30 Jun 200013 Aug 2002Philip WattsScalloped wing leading edge
US7857597 *28 May 200928 Dec 2010General Electric CompanyBoundary layer fins for wind turbine blade
US853500818 Oct 200517 Sep 2013Whale-Power CorporationTurbine and compressor employing tubercle leading edge rotor design
US8573541 *13 Sep 20105 Nov 2013John SullivanWavy airfoil
US9464532 *5 Mar 201311 Oct 2016Bell Helicopter Textron Inc.System and method for reducing rotor blade noise
US20090074578 *18 Oct 200519 Mar 2009Whale-Power CorporationTurbine and compressor employing tubercle leading edge rotor design
US20100143144 *28 May 200910 Jun 2010General Electric CommpanyBoundary layer fins for wind turbine blade
US20120061522 *13 Sep 201015 Mar 2012John SullivanWavy airfoil
US20130224037 *13 Sep 201229 Aug 2013Dennis SimpsonCompound airfoil
US20140255184 *5 Mar 201311 Sep 2014Bell Helicopter Textron Inc.System and Method for Reducing Rotor Blade Noise
WO2006042401A1 *18 Oct 200527 Apr 2006Whalepower CorporationTurbine and compressor employing tubercle leading edge rotor design
U.S. Classification416/20.00R, 244/200, 416/236.00R, 415/914
International ClassificationB64C11/24
Cooperative ClassificationY10S415/914, B64C11/24
European ClassificationB64C11/24