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I CYCLONIC TURBINE ENGINES This invention relates to cyclonic engines and more particularly to such engines having power rotors with 2 bearings 28 and 30. Each of the end bells 26 isprovided with an annular closure plate 40 seated in an annular offset 42 in the casing end, and is secured in place by the end bell. The plate 40 has an annular sleeve 4-1 pro powered by gas pressure created by internal com bustion or by high pressure steam, the gas pressure being impressed upon one or more rotors having helical torqueinducingpassageways.Inpracticetherotormay comprise a hub with a plurality of closely compacted radial stifwires through which a plurality of helical grooves are cut or otherwise formed, or itmay com prise a plurality of like metal stampings having a plu rality of radial slots with serated edges, helically stacked as by keying in a helical shaft key way. The 'helically grooved rotors may be employed in a single stage or series of stages of enlarging diameter, and a radial wire rotor, or rotors may be employed as com binations of radial wire and helically displaced disk r0 tors. 20 shaft38. Within each of the end bells and keyed to the shaft 38 as at 44 is an air compressor rotor 46 comprising an annular hub 48 keyed to the shaft 38 as at 44, and from which extend a plurality of sti? straight wires 49, as closely spaced as possible at their root ends in the hub. The wires are cut away as at 50 to provide a plurality of helicalpaths51,preferablyuniformlyspacedangularly about the hub for the reception of air induced into the end bell from the air inlet 36, the rotation of the rotor 46 compressing air in the end bell and forcing the air - into the power internal combustion chamber 52 throughtheannularopening54betweenthesleeve41, and shaft38. At each end of the combustion chamber 52 is a fuel injection inlet nozzle 60 fed by a fuel pump, not shown, and adjacent thereto, but having a guard baffle 62 is a spark plug 64 or other suitable ignition device. Keyed totheshaft38,asat66isapowerrotor68havingahub 70, from which radiates a ?eld of stiff radial wires, 72 as closely spaced at the hub end as space will permit. The ?eld of wires is provided with a plurality of uniformly spaced helical passages 74 extending from the ignition side of the motor to the central exhaust area 76, and the exhaust 24. The rotor construction is similar to the rotor 46 in the end bell, except that to re sistcorrosion,andthehightemperatureoftheburning fuel, the rotor wires would preferably be of a titanium alloystainlesssteel. While the use of a fuel injection system is referred to, fuel such as gasoline may be mixed with the air drawn into the compressor chamber through the port 36, pro vided a sufficient wire gauze annular back ?re prevent ingscreenbeintroducedintotheannularopening54. Referring to FIG. 2,there isshown a casing 120 com prising stepped stages 122 and 124 of increasing diame ter, an end bell 126 having an annular chamber 127 withatangentialinletport128forhighpressuresteam or other medium under pressure. The enlarged stage 124 isprovided with an end plate 130 having suitable exhaust ports as at 132. The end bell 126 is provided with a bearing plate 127, which with the end plate 130 areprovidedwithbearings134,136,138and140hav ing seals 142 and 144. Secured between the end bell and the primary stage casing 122 is a circular turret jet plate 146 having a plurality of tapering jet forming apertures 148 each disposed on a helical axis suitably oriented with respect to the tangential inlet, the jets beingadaptedtoemithighvelocitysteamtangentially and helically into the primary stage 122 of the casing 120. Keyed to the shaft 150 as at 151 is a primary stage rotor 152 in the casing 122, which may correspond to the rotor 68 in FIG. 1, comprising radial stiffwires 153 with helical slots 154. A secondary stage rotor 158 composed of a plurality of corrosion resistant like stampings160(SeeFigure11),eachhavingahubpor— tion 162, and each having a plurality of like serated blades 164, the serations being in the form of uniform notches 166, 168 and 170, formed in their side edges The above and other novel features of the invention will appear more fully hereinafter from the following detailed description when taken in conjunction with the accompanying drawings. It is expressly understood thatthedrawingsareemployedforpurposesofillustra tion only and are not designed as a de?nition of the limitsoftheinvention,referencebeinghadforthispur pose to the appended claims. In the drawings, wherein like reference characters in dicatelikeparts: FIG. 1 is a longitudinal sectional view of a gas turbine operating on internal combustion gases, with rotor partsshown inhalfsection and halfelevation; FIG. 2 is a longitudinal sectional view of a two stage turbine adapted for high pressure steam or other source ofhighpressuregas; FIG. 3 isa transverse section taken on the line 3-3 ofFIG. 2; FIG. 4 isatransversesectiontakenon theline4-4 of FIG. 2; FIG. 5 is a developed section through several jets takenonacylindricalcutindicatedat5-5 inFIG.4; 25 FIG. 6 is a perspective view of an alternative form of jetdiskwithhelicaljetforminggroovesmilledintothe 45 externalsurface; FIG. 7 is a fragmentary sectional view of a mounting ofsuchdiskintheboreoftheexpansionchamber; FIG. 8 is a fragmentary plan view of a section of the outersurfaceofthemilledjetdisk; FIGS. 9 and 10 are fragmentary plan views of the inlet and outlet sides of the disk showing the jet groove cross sections; FIG. 1 l is a fragmentary plan view of a disk rotor. 50 FIG. 11a is illustrative of a modi?ed blade contour; 55 and FIG. 12 isamodi?ed form ofturbine. Referring to FIG. 1,there isshown a turbine utilizing internal combustion to provide the motive power. There isprovided a central casing 20 having a cylindri cal internal wall 22, and symmetrical about a center lineA onwhichtheexhaustport24islocated.Ateach of the opposite ends of the casing 20 there is provided anendbell26havinganti-frictionbearings28and30,65 with an intervening seal 32, the cap having a cylindrical cavity 34, and an inlet 36 to provide an air compressor housing.A shaft38isrotatablymountedintheendbell 3,692,421 helicalpassageways. More particularly the invention is adapted to be 5 jecting into the combustion area, in spaced relation toPDF Image | CYCLONIC TURBINE ENGINES
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