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3 and tips as shown. Each disk isprovided with a keying lug 174, such that when a stack of the disks are assem bled on the shaft, stacked with the lugs 1'74 keyed in a helical key way 176, the slots between the blades pro vide a plurality of helical passage ways through the stack. The helical passageways are disposed at an angle correspondingtothatofthecircumferentialpathofthe high velocity steam or other gaseous medium discharged into the primary stage chamber from the jets148. 4 to be used. Where smaller diameter disks and shallower grooves are required, a circular die of the correct diameter can be employed economically to trim the disks to such diameter as desired. If desired, the serated blades 164 of the stampings forming the rotor 158 may have rounded sinusoidal edge formations, for example as indicated at 266, 268, and 270 in the typical blade or ?nger 264 shown in FIG. 11a. In the modi?cation of FIG. 12, fuel is introduced afteraircompression, but priortodeliveryofthecom bustible mixture to the combustion chamber. As shown, there is provided a cylindrical casing 220 hav ing an end bell 322, and an annular plate member 324 clamped therebetween by bolts 326. The casing 220 and member 224 de?ne a combustion chamber 228. 3,692,421 Referring to FIGS. 3-5 there is shown in greater detail the tangential inlet 128, and the helical jet port 148 having enlarged openings 170 at their inlet ends, gradually reducing in cross section as at 172 at their outlet ends. A suitable ratio of reduced cross section from inlet 170 to the outlet 172 may be in the order of 5 to 1. It will be seen that with the tangential jet velocity, the rotor 152 will be subjected to the steam velocity and will be caused to accelerate, and rotate at 20 236 closely surrounded by the internal cylindrical wall a high speed, dependent upon the jet velocity. Further the steam in issuing into the second stage will undergo expansion and administer torque to the rotor 160 as it escapestotheexhaustend 180ofthechamberthrough thehelicalslots1S4boundedbytheseratededgesand 25 the stepped offsets resulting from the disks being for wardly offset slightly with respect to each other from the inlet side to the outlet side of the rotor. In order to simplify the construction of the helical tangentialjets,theturretjetplatemay taketheform shown in FIG. 6, wherein the periphery of the plate is provided with helical reducing cross section grooves which may be readily milled economically. As shown the plate 200 has a plurality of helical grooves 202 of convergingcrosssectionfrominletends204totheout 35 let ends 206. Such disk has a shaft aperture 208, and is adapted to be bolted as at 210 to the central annulus 125 of the end bell. The exterior surface 211 of the plate 200 has a close fitwith the interior cylindrical sur face 212 of the stage 222, and ifdesired, radial bolts 224 may secure the plate in position, such radial bolts extending through the thickened ?ange 226 of the stage 222, and threaded into apertures 230 disposed betweenadjacentjetslotsorgrooves202.Inpractice45 the jet slots may have an inlet depth of one-fourth to three-eighths inch on a 3 inch radius, and a circum ferential opening of three—fourths of an inch or more, with the slot tapering down on a helix to a discharge openingaboutone-fourthinchdeepandone-fourth50 inch wide as measured along the circumference. If desired a compressor such as indicated in the modi?cationofFIG. 1may beemployed inplaceofthe steam inlet chamber, and jet plate, and ignition and in jectionmeansprovidedaheadoftherotorinstage1of55 FIG. 2, or ?rst and second stages as in FIG. 2 may take place of the single stage indicated on either side of the exhaust in FIG. 1. It will be understood that while equalized thrust on the shaft is a feature of the form shown in FIG. 1, such feature may be eliminated ifsim~ pli?cation isrequired, which may be had by eliminating the compressor and power rotor or rotors, and ignition and injection means on one side of the center line, A 238 of the end bell. The rotor 236 is provided with a plurality of helical grooves 240, having a semicircular cross section or an equivalent. Immediately adjacent the rotor 236 is an air and fuel compressing and deliveryrotor242oflesserdiameter,andclosely?tting within the cylindrical bore 223 of the sleeve portion 225 of plate member 324. The rotor 242 is provided with a plurality of helical grooves 244 of semi-circular cross section or the equivalent. There isthus provided a ?rst and second stage of air compressing with fuel in troduced between the stages. The shaft 234 extends into the combustion chamber and isshown as provided with a power rotor 68 of the type having radial wires and helical grooves, although the disk type may be em ployed.A suitableignitiondeviceintheformofaplug 64isprovided. The end bellchamber isprovided with a suitable air inlet 310, and immediately adjacent the plate member 324,thereisprovidedafuelinlet212.The mixedfuelis then advanced into the combustion chamber by the im peller effect of the grooves 242 in the rotor 244. To enhance the cyclonic effect, a disk 200 such as shown inFIG.9or146asinFIG.2maybedisposedinthe chamber228spacedfromandbetweentheendofthe sleeve 225 and rotor 68, the disk being secured to the casingwallinanysuitablemanner. In the internal combustion forms of the invention, starting is effected by rotating the shaft, injecting fuel inapropermixture,andeffectingignition,whereupon the expansion of the burning gases provides a cyclonic effect driving the power rotor 62, whereupon accelera~ tiontohighspeedsisattained.By introducingairunder pressure into the inlet 36 of FIG. 1 or 310 of FIG. 12, startingrotationmaybeinducedbyinitial?uidpres sure acting on the rotor 51, or 238 so that by thereafter introducing fuel and effecting ignition, combustion and expansion takes place in the combustion chamber ap plying the cyclonic action to the power rotor to ac celerate the rotor up to fullpower speed. It will be seen that in each form of the inventions a rotor provides compression of the inlet air forcing the same into the combustion chamber, where ignition is effected. While in FIG. 1, fuel is injected directly into the combustion chamber, in FIG. 12 the fuel is in troduced between the initial compression state. The compressing effect of the rotor 240, delivers the com A. Itwill readily be seen that the disks from which the diskrotorisformedmay allbecuteconomicallyfroma single die, designed to cut disks of the largest diameter 65 Journalledasat231 and232intheendbell,isashaft 234, having a helically grooved air compressing rotorPDF Image | CYCLONIC TURBINE ENGINES
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