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Publication numberUS2396811 A
Publication typeGrant
Publication date19 Mar 1946
Filing date10 Dec 1943
Priority date10 Dec 1943
Publication numberUS 2396811 A, US 2396811A, US-A-2396811, US2396811 A, US2396811A
InventorsBathras James E
Original AssigneeBathras James E
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Airplane propeller
US 2396811 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

' March 19; 1946.

J. E. BATHRAS AIRPLANE PROPELLER Filed Dec. 10, 1943 Man/55 5A7 7/7 25 5 Inventor ttorneys FFICE AIRPLANE PROPELLER James E. Bathras, Portland, Maine Application December 10, 1943, Serial No. 513,760

1 Claim.

This invention relates to an airplane propeller,-

and particularly to the formation of the blades. thereof.

Airplane propellers are of relatively large size or have long blades, and they ordinarily create a loud humming noise when operating at high speed. Also, with the ordinary airplane propeller, there is noticeable loss of efliciency at the tip portion of the blade, due to centrifugal slippage.

The primary objects of the present invention, therefore, are to provide an airplane propeller which, through its particular blade formation. will be relatively quiet when operating at high speed, as well as highly efiicient, and which will nullify tip loss resulting from centrifugal slippage, by causing a centripetal movement of air, through 9, particular arrangement and form of fin on the tip portion of the blade.

A specific object of the invention is to increase the efilciency of the -propeller.and bring about quiet operation through a particular fin formation on the trailing edge of the blade, respectively along the major intermediate portion of the trailing edge and on the trailing'edge at the tip of the blade.

The present invention consists in the novel form, combination and arrangement of features and parts hereinafter more fully described, shown in the accompanying drawing and claimed.

in the drawing, wherein like reference characters indicate corresponding parts throughout the several views:

Figure 1 is a rear elevational view of an airplane propeller constructed in accordance with the present invention.

Figure 2 is a transverse section taken on the line 2-2 of Figure 1, and

Figure 3 is a section taken on line 8-8 of Figure 1.

Referring in detail to the drawing, I have shown an airplane propeller having two blades 5 of similar form and extending from opposite sides of a central hub 8. Each blade has a pressure side 1 and a non-pressure side 8. The leading edge is indicated at 9, and the trailing edge at ill. As usual, the blades are disposed at a desirable pitch or angle to the axis of rotation, which may be on the line H. The direction of rotation is indicated by the arrows l2 and the direction of air movement by the arrows It. The line I is the plane of rotation of the trailing edge and the line it the plane of rotation of the leading edge.

As shown clearly in Figure l, the leading edge 9 is substantially parallel to a line extending lon-. gitudinally of the blades and through the axis of rotation, while the trailing edge is bowed out considerably to give sumcient blade area at the different sections. In accordance with the present invention, a fin i8 is provided to extend along the major intermediate portion of the trailing edge it, and this fin is turned outwardly and forwardly toward the direction of travel of the air-'- plane, as shown in Figure 2. Another smaller fin ii is provided on the trailing edge at the tip end portion of the blade, said fin I7 being turned outwardly and rearwardly in the direction of air 20 tively thick adjacent the nose or leading edge and tapers thinner toward the trailing edge, but the cross sectional or airfoil shape of the blade may vary to some extent. The effect of fin i8 is to lead the air from the pressure side outwardly and forwardly 'for gradually diminishing turbulence and thereby resulting in a considerable reducti n in the loud humming noise ordinarily cause by an airplane propeller when operating at high speed. The fin i'l causes acentripetal movement oi. air and thereby nullifies tip loss from centrifugal slippage.

Although a specific embodiment of the invention is illustrated and described, it will be understood that various changes may be made within the scope of the invention as claimed.

What I claim as new is:

An airplane propeller adapted to berotated about an axis for displacing air and comprising a hub, a plurality of blades of similar form extending from the hub and disposed at an angle to the axis of rotation, each of said blades having an outwardly bowed trailing edge, a fin curved forwardly from the major intermediate portion oi.

the trailing edge oi each blade, and having an outwardly bowed trailing edge, and a second fin on the trailing edge at the tip end of each blade, the lastnamed fin being curved rearwardly and having an outwardly bowed trailing edge.

JAMES 1:. names.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2682925 *19 Jan 19506 Jul 1954Solar Aircraft CoAerodynamic improvement in fan blades
US2952320 *30 Apr 195613 Sep 1960Bensen Aircraft CorpAirfoil
US4618313 *6 Oct 198321 Oct 1986Cofimco S.R.L.Axial propeller with increased effective displacement of air whose blades are not twisted
US4722608 *30 Jul 19852 Feb 1988General Signal Corp.Mixing apparatus
US5219272 *2 Dec 199115 Jun 1993Brunswick CorporationVariable pitch marine propeller with hydrodynamic shifting
US5290147 *2 Dec 19911 Mar 1994Brunswick CorporationVariable pitch marine propeller with shift biasing and synchronizing mechanism
US5492448 *8 Mar 199420 Feb 1996Westland Helicopters LimitedRotary blades
US6390776 *30 Mar 200021 May 2002David GruenwaldMarine propeller
US6699016 *12 Jun 20022 Mar 2004Peter DeanBoat propeller
US7458777 *22 Sep 20052 Dec 2008General Electric CompanyWind turbine rotor assembly and blade having acoustic flap
US7549839 *25 Oct 200523 Jun 2009United Technologies CorporationVariable geometry inlet guide vane
US8764403 *1 Jan 20091 Jul 2014Technion Research & Development Foundation Ltd.Fan and propeller performance enhancements using outsized gurney flaps
US20070065290 *22 Sep 200522 Mar 2007General Electric CompanyWind turbine rotor assembly and blade having acoustic flap
US20070092372 *25 Oct 200526 Apr 2007Carroll Christian AVariable geometry inlet guide vane
US20110123348 *1 Jan 200926 May 2011Technion-Research &Development Foundation Ltd.Fan and propeller performance enhancements using outsized gurney flaps
US20140093380 *3 Oct 20123 Apr 2014General Electric CompanyNoise reduction tab and method for wind turbine rotor blade
WO2016068730A1 *20 Oct 20156 May 2016Savedra Pacheco PedroPsp blades with dihedral angles, comprising a longitudinal depression
U.S. Classification416/235, 416/243, 416/242
International ClassificationB64C11/00, B64C11/16
Cooperative ClassificationB64C11/16
European ClassificationB64C11/16