US1675527A - Combined propeller and rotor - Google Patents

Description

July 3;, I928 1,675,522-7 J. c, BENNETT COMBINED PROPELLER AND ROTOR July 3, 1928. 1,675,527

J. c. BENNETT 4 COMBINED PRPELLER AND ROTOR J1/wanton Patented July 3, 1928.'

uNirED STATES PATENT oF-FicE.

Jamas c. nimm, or' NEW Yonx, N. Y., AssIGNon or ronrr ran oEN'r rowILLnur i1. man. or lmw Yonx, N. Y.; FIVE PER cEN'r rro GoNzALo oNEILL, or naar ORANGE, NEW JERSEY; BAYONNE, NEW JERSEY.

AND FIVE PER CENT TO ARTHUR A. DE BONNEVILLE, I'

COMBINED PBOPELLEB AND BOTOB.

Y animation mea september r, 192e. serial No. maeva.

This invention relates to combined-propellers and rotors. p

The object of the invention 1s theproduction of a rotor that is turned by streams of 5 air, that have functioned' with the blades of a propeller, and-which function with a second propeller as theyare discharged from the rotor, whereby the air compressed by the first pro eller is used expansively 1n the rotor an again expansively 1n the second propeller. The second ob]ect of the invention is the bined propel ers and rotors that are operated by air discharged to the rearof a main propeller. v

The third' object of the lnvention is the productionof a pair 'of combi-ned propellers and rotors, that function with the main propeller of-an aeroplane toturn the shaft 2o of said-main propeller. The fourth object of the invention is the production of a pair of combined propellers and rotor, that function' as stabilizers for an aeroplane..

In the accompanying drawings Fig. 1 represents a top plan view of a fragmentary portion of an aeroplane witha p lan view of an exempliication of the combined propeller and rotor; Fig. 2 -shows a section of Fig. 1 on the line 2, 2 and Fig. 3 indicates 3o a section of Fig. 1 on the line 3, 3.

An aeroplane is indicated with the' fuse lage 20 having the usual' opening 21 1n its crown. The main propeller is indicated at 22, the engine lat 23 having the shaftl 24. Thel top and bottom wings are respectively indicated at 28 and 29.

Between the wings 28 and 29 are located the similar cylindricalsleeve casings 3() and 31. Each ofsaid casings has formed there- `4o with the conical shaped inlet duct 32 and the conical shaped outlet duct 33. A pair` of straps 38, preferablyof metal, bear on the top face of the top wing 28, and each has formed therewith the bent up ends 39. Similar straps 40 bear against the lower face of the wing 28 andl have formed therewith the bent up end duct 32 and the outlet duct 33. Rivets 42 connect said ducts 33 and the said ends 39 su and 41. A pair of straps 46 similar to 38 bear on the top face of the bottom wing 29,

roduction of' a 4pair of com-l s 41 which bear onl the inlet ends 47 and 48, which bear against the ducts 32 and 33.l `A pair of straps 49 bear against .the bottom face of the bottom wing '29 and each is indicated with bent ends 50 and 51.- Rivets 52 connect the endsof the latter pair of straps to. the straps 46v and the ducts 32 and 33.v A strap 55 has its ends connected tothe straps 38 and a strap 56 has its ends connected to the straps 49. Screws 58 extend through the strap 55 and engage frames 3,1 is located a' rotor.` The said rotors comprise the similar sleeves 63 and 64. Within each of the sleeves 63 and 64 is shown'the barrel 65. A plurality of right handed helical blades 66 are located between and connected to the sleeve 63 and its barrel-65, and a' plurality of left handed helical blades 67 are connected to the sleeve 64 and its bar- A shaft 72 is located in the axial center of each of the sleeves 63 and 64. A airf discs 73 arek fastened to each shaft 2 and support the barrels 65.

A front propeller 74 and a rear propeller 75 arel fastened to each shaft 72.

A rear supporting frame comprises the topl anglejirons 81 which extend through the fuselage 20. A bottom angle iron 82 bears up against the bottom of the fuselage v ertically below the angle iron 81. The vertical angle irons 83 connect the angle irons 81 and 82, and struts 84 extend between the angle irons 81 and 83. Angle irons 85 connect the angle irons 80 and. 81.-

A front supporting frame similar to the rear supporting frame is' indicated with the top angle irons 90, 91 similar to 80 and 81. A bottom angle iron, not shown, similar to 82 is located vertically below the angle iron 91. Vertical angle irons 93 similar to 83 and struts not shown similar to 84 are provided. Angle irons 95 similar tol 85 connect` the angle irons and 91.

Upon each of the angle irons 81' and 91 are fastened the similar journal bo'xes 160 in which are journaled the shafts 72. A tight ullefy 101 and a loose pulleyv 102 are provided or one of the shafts 2 and 'a tight pulley 103 and loose pulley 104 are provided for the other shaft 72.

A platform 105 is secured in the fuselage and supports the similar journal brackets 106, and 107 and 108. A shaft 109 is journaled in the journal brackets 1 06 and 107. A pulley 110 is fastened to the shaft 109 between the journal brackets 106 and 107. AA straight belt 112 is provided for the pulleys 101, 102 and 110 and a cross belt 113 is provided for the pulleys 110, 103 and 104. A belt shifter 115 is provided for the beltI 112 and a belt rshifter 116 is provided for the belt 113. An electric generator 120 is supported upon the platform 105 and one end of its armature shaft 121 is journaled in the journal bearings 108. One member 122 of a -friction clutch is slidably connected to the armature shaft 121, and the second member 123 of the said clutch is connected to the shaft 109 in the usual way. A journal bracket 125 supports one end of the shaft 24 and the lattervhas fastened thereto the spur ear 126. An electric motor 128 is supporte 1n the fuselage and on its armature shaft 129 is rot-atively supported one member 130 .of a friction clutch. A spur gear 131fis fastened to the member 130. Thesecond member 132 `of 'the friction clutch is slidably supported on the armature shaft 129. A journal bracket 133 supports one end ofthe armature shaft 129.

An electric storage battery 135 is supported in the fuselage. A wire 140 with the fuse 141 connects the storage battery and the electric enerator 120. An electric switch 142 is provided for the wire 140. Awire 143 with the fuse 146 connects lthe battery 135 and the electric motor 128. An electric switch 149 is provided forV the wire 143. A wire 150 connects the electric generator 120 and the electric motor 128. l

In thepresent exemplifcation of the invention with-the aeroplane, when the main propeller 22 thereof is started by the engine 23, the aeroplane rises in the usual manner and the air dischar blades of the main propeller impin es against the blades ofthe propellers 74 which causesthe latter to turn. The tstreams of air discharged to the rear of the blades of the propellers 74 enter the inlet ducts 32 and engage the helical blades 66 and 67 of the rotors. Streams of air are discharged from the blades 66 and 67 and impinge against ged tothe rear of the the blades of the propellers 75. By this means the rotors with their shafts turn in opposite directions and fuhction as stabilizers for the aeroplane. The rotations of the shafts 72 through the belts 112 and 113 are transmitted to the shaft 109, and 'from the latter to the armature shaft 121,'by virtue of which the electric generator 120 isturned.

By vthis means the storage batte 135 Yis charged. The belt shifters 115 an 116 enand 123, the electric generator 120 may be started or stopped. The electric current furnished by the wire 143 turns the electric motor 128. The rotations of the armature shaft -129 of the said motor are transmitted to the shaft 24 by means of the gears 126 and 131. The rotations of the two rotors With their propellers, assist the main shaft 24 in' turn# ing in addition to the rotation imparted to the shaft 24 b the engine 23.

Various mo ifcations may be made in the invention and the present exemplication is to be taken as illustrative and not limitative thereof.V v j Having described my invention what I desire to secure by Letters Patent and claim 1s:

1. The combination of a sleeve casing, an inletduct extending from one end of the casing, an outlet duct extending from the other `end of the casing, a rotor in the casing and coaxial therewith, means to'direct streams of compressed air to the said inlet duct, the air rotating the rotor and expanding, and means to again expand the air when dischar ed fromthe outlet duct.

2. The comi inlet duct extending from one end of said casing, an outlet duct extending from the other end of the casing,y a shaft coaxial with the sleeve casing, a'rotor sup orted on said' shaft, a propeller fastened to t e shaft atl one end of said casing adjacent to i-ts inlet duct and a second propeller fastened to the shaft adjacent to its outlet duct.

3. The combination of a rotor comprising a sleeve casing, an inlet duct extending from one end of the sleeve casing, an outlet duct extending from the other end of the sleeve casing, a shaft coaxial with the sleeve casing, a sleeve within and coaxial with the sleeve casing, a plurality of helical blades,` interposed between said sleeve and the'shaft, a propeller fastened to the shaft at one end ination of a sleeve casing, anV

of 'thesleeve casing adjacent tovsaidinlet f duct and a propeller fastened to said shaft adjacent to said outlet duct.

v4. The combination of a rotor comprising a sleeve, a shaft coaxial with the sleeve, a'

pair of discs fastened to the shaft,a barrel fastened to the discs and a pluralit of helical blades interposedy between the s eeve and the barrel, the outer circumferential portion of each helical blade fastened to the sleeve and the innercircumferential portion of each blade fastened to the barrel.

Y 5. The combination of a rotor comprisin a c lindrical sleeve casing, a shaft' coaxia w1t the sleeve casin ai sleeve within the casmg, a barrel within the sleeve, connectlng means between the barrel and theshaft, e plurality of helical blades with their outer lll portions fastened to they sleeve and their inner portions-fastened to the barrel and propellers fastened to the shaft at the oppofl 'sleeve casings to said Wings, a shaft coaxial with each sleeve casinngla sleeve within each sleeve casing, a barrewithin each sleeve, a shaft within each barrel, connecting means between each barrel and its shaft, a plurality of helical blades interposed between each sleeve and its coaxialbarrel and meansl to connect the shaftl of each rotor with theA main shaft of the aeroplane; Y'

7. In combination an laeroplane lage for the. aeroplane, an engine a fusehaving a main shaft in the fusela'e, a propeller connected to said main shaft, a pair of wings for the aeroplane, a pair of rotors between the wings of the aeroplane on opposite sides of the fuselage, a sleeve casing for each rotor, means to connect the sleeve casings to said wings, a shaft coaxial with each sleeve l casing, right handed helical blades turning with the shaft of one rotor and left hande helical blades turning with lthe shaft of the other rotor and means to connect the shaft of each rotor and the main shaft of the aeroplane. y

8. In combination an aeroplane, a fuselage for the aeroplane, an engine having a main shaft in the fusela e, a propeller connected to said main sha t, a pair of wings for the aeroplane, a pair. of rotors between the wings onoppositesides .of the fuselage,

la shaft for each* rotor,an electric'generator in the fuselage,.adjustable means connecting the shafts ofthe rotors and the armatures shaft of the electric generator, a storage battery in the fuselage, electric connections between the storage battery and the electric generator,v an electric motor in the fuselage, electric' connections between the motor and battery and adjustable connections between the motor and the main shaft of the engine in the aeroplane.

In testimony whereof I alix my signature.

JAMES c. BENNETT.

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