US1991378A - Wing rotor - Google Patents

Description

Feb. 19,1935. J cHmsfi Ns N 1,991,378

WING ROTOR Original Filed Oct. 28, 1931 2 Sheets-Sheet 1 1935- J. CHRISTIANSEN 1,991,378

WING gowon Original Fild Oct. 28, 1931 2 Sheets-Shet 2 Jwuentoc.

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Patented Feb. 19, 1935 UNITED STATES t WING :ROTOR Johannes Christiansen,

n igno of on -hal e Washington, -D. C,

sorup- 'scha u by, I Gerl i 9P A plication October as; 1e31,;sen 1 511, 49, Renewed May 15,1934. In Germany October -i- 16 Claims (01. #44 16) This invention relates to improved means for moving conveyances of various description, whether on land, on water or in the:air,and has forits-objectto' provide a wing-rotor for flying vessels, and the arrangement of such rotors,'especially inconnection with aeroplanes. J

The present invention does not make use i of the Magnus efiect and differs from Gyrocepters and, the known type of screwirotors. i 1

The principal difierentiating feature and one of ,the salient objects of the invention consists in the; :c.onstruction and arrangement ,oftwo rigid planes, one of which ,isilocated .nearuthe center of :the wing rotor, the other one constituting the: top or cover. of the rotor.

{The invention further consists of the novel construction, combination and arrangement 1 of parts, as'jhereinaftertmore,. specifically-described and illustrated 1 the V accompanying \edrawing's, wherein isshownlan embodiment ofth'e invention; itpbeingzunderstoodthat changes, ..variations and; modifications; can be. resorted to within the scope-f otheelaims. i

ssimilar characters .of reference s. indicate v simi lar partsthroughout the several views. ;:Figure;l isoaperspective-front;view of an aeroplane equipped with two: laterallytdisposedwingrotors. 1 v r a v v v I ;Figure;2; isia perspective side \view' of Figure '1. Figure ;,3 represents .a a i 'lo'ngitudinal sectional View of -.a .wing.-irotor. I 1

Figures 4, 5 and ,s6wrepresentcross-sectional views of different positionsnf .a pendulum.

.Figure"? islalitransversesectionaloview of a wingrrotor withsaLpreferredform of the inner semiecircular-rigid.plane. w 7

Figure Siisfa transverse sectional view of a wing-rotorwiththe innerlrigid plane at a'nega tiveanglelin regards'to the upper or outerrigid' plane; i i- :Figure 59 .:is a transverse sectional view ,.of a wing-rotor WhenLdescendingor falling. sEigureiearis.across-sectional view of-the inner rigid plane of a wing-rotor of a shape difierent fromthose'illustratedin Figures 7,: 8;- 9-and 10. 1 .Figure 10 shows 5.9, transverse sectional out through :two rotorslarranged in series,..one behind theother. V 1

1':In.-1 igures.11 and 12a modificationiofithe-device iscshown I .in which a vertical, power-driven, rotating shaft is provided at each side ,of' Jtherbody and a a plurality of. rotor devices are mountedon each shaft. r is r.=Figure-. 11; is a planeiwiew; of a r lift vesse .iof thei'gyi'oa type: iequippedrwithswing-rotors.

Fi r 1 s affr nt view. o Figu 1 i R er in more p rt cula l o t e dr win s (a5 indicates an assembly or crown of wings-pr prope lade p i n tudi a l froth aft a is o t W nsoto he b ade (a) v are held in position by lateral-circulargiiscs (b), which are either soldered o r welded to the blades. Z-Theparts (a) and,(b),-may be forged-or Cas i o pi -i n r igi nlano n t ax s (k) may a so be W lded ,o i s ld red 10 o e o iaoastor for ed-a ne p ece! The o o new lan (d) i thickened at its nt r o on at and. .oe oenea its osterior-e list (QT romthe ou aoiroum o no o h. W o w ne i ordo the very end of its posterior ,part. The outer isi rmn arb atta he it odyie) otthe vess l-by:moansoii rew o Jo t to othe wis indioai dr i h ohara (b in-Ennis 3;. ii

ma alsoib i oldini os i by m a s o s ars o the like connected to the axis (is) (see Figurefl; ohorao i d Therw sown (a) and; (1 .:r0- f o-tot i ool a ou d h xi (1c) an i the inne gi plan 'c ib ,-me ns o b beor ns tsh w vFisu 3 ;hy..i ohara te A pe dul mio sioonnectedto ax 1c :i su a a ner that l' w -l fi ndlto st t inn ,r idip aneaic). heneve it i out o yit 1 no ma posi ion upper shaft of this pendulum; passes through the a i ,(JQ- ,qropr s t -a.io n j n p heiulc umma -b read l e n-how pendu umif n tion ir mfl s esfii i;5.and. i6- "fi ure 3show n th pe du um in pos n a ta h d to. the axis 9 l ndi h body. i e) i of, the .flvinsnesseL and F e -A, d ;6 showin a oro rs ot nalaview o thop n ulumin normal position and: atatn sat ve and positive angl Thei hara teriw rep esents a wing-rotor. A dynamo ir) attached {to holh d of th lyin vessel i tao onso d. to awheelis) engaging the lateral endzdisctb) or 5 5 therotor hy .means .011 a. drivin'g}shaft (s QIhis wheelie) .inaytact as a braklto'reduceitlieimmher of revolutions of the wing manger, it ,rnayjhe used to drive the wing-rotonJoy means of 'the d oemo h l t r b n me ia 'ij i io QTh s propeller of the flying vessel'jis marked; (hfl When a vessel of the gyro typeisequippedfwith wing-rotors as shown inj-Fig'ures 11' share;- the rotors are rotated horizontally around a vertical axis (2'), which is engaged rby a shaft (t) by 35 means of gears (t). The shaft t) is driven hy theimotor'. driving the propeller (hloof the flying vessel: or;by any other motor .jofrtheivesselt The cha act rs a n iii dicate theqfl wofiairn i th v Win ro orsio oiin onor tionso-ls" to re me it i o m vpositiona 1 the outer rigid plane (it) will prevent any air from; pressing down into these spaces especially while the vessel is ascending.

These two rigid planes eliminate all resistance to lift and forward motion of the vessel.

The airlines clearly indicate the flow of air.-

The air flow indicated at x" is forced through the center of the rotor where it is compressed due to the narrowing of the channel and will thus exert a lifting power by pressing upward against the blades which happen to be in the position of the blades characterized by the numerals (1) and (2). The air striking the vessel above blade 1 will pass over the surface of the outer upper rigid plane as indicated by line marked (1.). Due to the outward bend at (03") the flow of this current of air is finally directed towards the anterior part of the wing rotor thus increasing the forward thrust of the vessel. It will be noted that the blades of the rotors are curved in such a way that the blades exposed to the air current in the lower section of the rotor receive the air on their concave surface, moving with the air-current, while those in the upper section, moving in a direction opposite to the on-rushing air current, present their convex side toward the air current. The direction in which the air vessel moves is indicated by an arrow marked (2).

Any number of wing rotors/may be used in series. In Figure 10 the flow of air through two rotors, one behind the other, is clearly illustrated by the lines a: and :r'--:1: and needs no further explanation. v

In order that the wing-rotor may not rotate at a rate where the blades (a) would interfere with the on-rushing air current a" brake (s) connected to a dynamo (r) by means of a transmission rod (s') is provided. The excess of power may be used for'other purposes. This dynamo may also be used as a motor in order to increase the number of revolutions of the rotors. i It is understood that the wing-rotors on either side of the flying vessel may be operated independently so that stabilization may be effected and rolling or banking avoided. One orseveral rotors on one side of the vessel may have the rigid inner plane at an angle favoring lift, while'the corresponding rotor or rotors on the opposite side of the vessel may havethe inner rigid plane at an angle favoring descent.

The function of the pendulum (o) is to stabl lize the flying vessel in fore and aftdirection by operation or maintaining the inner rigid planes If the plane (0) is in an inclined position, positive or negative, as in Figures 5 and 6, the pendulum will tend to resume the position shown in Figure 4 and rotate the inner rigid plane (c) until it assumes normal position.

I claim as my invention:

1. In combination with an aircraft body a fixed member extending substantially horizontally transversely of said body, a turbine-like wing rotor surrounding said member and having its axis transversely of said body, blades extending outwardly from said fixed member to the periphery of said rotor and a plane mounted exteriorly of said rotor and substantially covering the upper portion thereof.

2. A device such as that described in claim 1 having in combination lateral circular discs supporting and connected to turbine like rotor blades.

3. A device such as that described in claim 1 having an inner rigid plane so constructed that the upper side is stronger curved than the lower side and having the external rigid plane so arranged'that the front rim of same is substantially thickened so that the plane fits in circular form over the upper part of the turbine like rotor wheels in such a manner that it fits closely to the rotor blades near its interior part exposed to the attack of the air current while it recedes from the rotor blades towards its end in order to turn sharply again towards the rotor blades at or near its end, as above described and illustrated.

4. An arrangement of wing rotors such as described in claim 1 where a number of wing rotors are arranged in series one behind the other parallel to each other and facing the direction of the current of air in the direction in which the vessel moves.

1, having a wing rotor on each side of the body,

the member of each rotor independently movable in oppositedirections, for stabilizing purposes.

7. A device such as described in claim 1, wherein the rotors are driven against the air by means of a propeller or propellers or any suitable vehicle, whereby the air-current necessary for the rotation of the wing rotors is created.

8. A device such as claimed in claim 1 wherein the wing rotor is driven by the air current set up by the moving vessel where the wings may rotate at a speed differing from that normally produced by said air current having in combination a dynamo so connected with the rotor as to actas a brake in order to reduce the number of revolutions of the rotor.

9. A device as claimed in claim 1, wherein the wing rotor is driven by the air current set up by the moving vessel where the wings may rotate at a speed differing from that normally produced by said air current. having in combination a dynamo so connected with the rotor as to act as a brake in order to reduce the number of revolutions ofthe rotor and having in combination a rotor or rotors coupled with a dynamo.

10. 'A device such as described 'in claim 1,

wherein the wing rotor is driven by the air current set up by the moving vessel where the wings 5. A device such as described in claim 1 driveni consisting of a member mounted on and transversely of said shaft, turbine-like wing rotors surrounding said member, blades extending outwardly from said member tothe periphery of said rotor and a plane mounted exteriorly of said rotor and substantially covering the upper part thereof.

12. In combination with an aircraft body, a

vertical, power-driven shaft provided at each side of the body, a plurality of rotor devices mounted on each shaft, each rotor device including a member mounted on and transversely of said shaft, turbine-like wing rotors surrounding said member, blades extending outwardly from said member to the periphery of said rotor and a plane mounted exteriorly of said rotor and substantially covering the upper portion thereof, the rotor devices being so arranged that they are driven by said shaft in a direction opposite to the flow of air. I t

13. In combination with an aircraft'body, a vertical shaft providedat each side of the body, a plurality of rotor devices mounted .on each shaft, each rotor device including a member mounted on and transversly of said shaft, turbine-like wing rotors surrounding said member, blades extending outwardly from said member to the periphery of said rotor anda plane mounted exteriorly of said rotor and substantially covering the upper portion thereof, wherein the rotor devices are driven against the air by means of a propeller or propellers or anysuitable vehicle,

whereby the air current necessary for the rotation of the wing rotors is created.

14. In combination with an aircraft body, a

.fixed member extending substantially horizontally transversely of said body, a turbine-like wing rotor surrounding said member and having its axial transversely of said body, blades extending outwardly from said fixed member to the periphery of said rotor and a plane mounted exteriorly I of said rotor and substantially covering the upper portion thereof, said member constructed with an upper side stronglycurved and a lowerside practically flat and presenting a profile of substantially semi-circularform.

15. A wing rotor such as described in claim 14, characterized in that said member together with said plane mounted exteriorlyof the rotor and covering substantially the upper portion of said rotor are so arranged and constructed that the rotor blades near its interior part exposed to the attack of the air current while it recedes from the rotor blades at or near its end, characterized in that the said inner rigid plane is movable over its axis in such a way as to prevent the current of air rushing thru a selected number of the rotor wheels, as above described and illustrated.

J O HANNES CHRISTIANSEN.

wheels in such a manner that it fits closely to

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