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2,417,600 34. provided a construction which is far simpler thanheretoforebyemployingrelativelyrotatable disk-like members, either of which may be a rotorandtheotherastator,orbothmaybe rotors, wherein provision is made for multi-stage radial flow, instead of axial peripheral ?ow while employing both reaction and impulse principles. Preferably, the outlet channels increase in size towards the exhaust, in accordance with the in crease in volume of the expanding steam or 10 3. The housing 6 is provided with a number of ?uid. , spacedoutletsl5.The?uidpressureininlet Preferably a sufficient number of inlet and out let channels are provided so that each inlet chan~ nel crosses a plurality of link channels, and each link channel crosses a plurality of outlet chan nels, whereby an impulse thrust is provided at each of the various crossing points. || produces rotation of rotor 2, the ?uid passing through the cooperating rotor channels l6 and stator channels H to the exhaust IS. The rotor channels l5 and stator channels |l may be arranged as shown in Figs, 2 to 6. Figs. 2 and 3 show a preferred form wherein ?uid under pressure enters inlet l8 and passes through certain channels, later described, in Another object of the invention is to ?oat the rotor and the thrust imposed on it by its work on the ?uid pressure between the rotor and stator. 20 rotor l9 and stator 20 to a number of spaced While in the above description and hereafter reference is speci?cally made to a turbine, it is understood that such description is intended to apply in an analogous manner to a pump, com pressor, or blower because the apparatus of this 25 at their outer ends, and (b) an outer array 23 invention may be employed as one or the other. For further details of the invention, reference may be made to the drawings, wherein Fig. 1 is a vertical sectional view of a turbine of link channels closed at their opposite ends. As each of the rotor channels in the array 22 is closed at its outer ends, as indicated at 24, and as each rotor link channel in the array 23 or compressor according to the present invention, 30 is closed at its inner end as is indicated at 25 schematically showing a typical arrangement of channels in the stator and rotor. Fig. 2 is a schematic plan view of a preferred arrangement of channels. and also at its outer end 26, the rotor channels 22, 23 provide only a part of the path from inlet il to the outlets 2|, the remainder of that path being in the stator as follows: The stator grooves Fig. 3 is an enlarged sectional view on the 35 in Fig. 2 are shown in dotted lines and comprise brokenline3-3 inFig.2. Fig. 4 is a schematic plan view partly in sec tion of a modi?ed channel arrangement. Fig. 5 is a schematic plan view of a further modi?cation. Fig. 6 is an enlarged sectional view on line 6-6 inFig.5. The feature of dead end channels to provide (a) an inner array 27 of link channels closed at both ends, and (b) an outer array 28 of channels closed at their inner ends as indicated at 29 and open at their outer ends and serving as outlets 40 2|, in communication with outlets such as I5 in Fig. 1, the housing 6 of Fig. 1 being omitted in Fig.3. The rotor channels 22 are curved in one direc tion, being convex in the direction of rotation a part of the ?uid path in the rotor, and the remainderinthestator,isdisclosedandclaimed ;whichisclockwiseasindicatedbythearrow38, in co-pending application S. N. 575,163, ?led January 29, 1945, for “Turbine.” Generally speaking, the present case is an improvement thereon in obtaining multi-stage operation by the use of link channels closed at both ends. Copending application S. N. 622,521, filed October 16, 1945, for Radial ?ow turbine discloses and claims a turbine or compressor wherein one or more of the channels are straight instead of curved, a feature disclosed herein and later de scribed. and they cross a plurality, here shown as four, of the inner stator link channels 27 which are curved in the opposite direction. Stator link channels are each crossed by a plurality of the outer rotor link channels 23 which are convex in the direction of rotation and arranged at a greater angle to the radius than the inner rotor channels22. Eachoftheouterrotorlinkchan nels 23 crosses a plurality of the outer stator channels 28 which are curved oppositely to rotor channels 23. The ?uid path branches from a channel in array 22 to a plurality of channels in the array 21, at the crossing points thereof, such as indi Referring in detail to the drawings, the tur bine or compressor herein described is illustrated in a simpli?ed form in order to more clearly illustratetheworkingprinciple. Theturbineor60catedat3|,thepat-h-furtherbranchingfrom compressor I comprises a rotor disk 2 and a stator disk 3 having adjacent surfaces in close face to face relation and separated from each other by a very thin ?lm of steam or vapor or other ?uid, on which the rotor 2 is adapted to 65 array 28, at the crossing points thereof, such as float. The rotor 2 has a coaxial shaft 4 sup portedbyabearingIinthehousing6. Bear ing l0 ispreferably both a radial and thrust bearing and, for example, may have a‘sleeve 5 whichisadjustablelongitudinallyontheshaft70tionofrotorl9. Alsothewidespreadbranchings 4 by means of adjusting nuts or bolts 8. The bearing Il has spaced ball bearings of which one race 1 is ?xed to shaft ‘4 and a comple mentary race 9 secured to the sleeve ‘5. By ad justing the nuts or. bolts 8, a desired clearance 75 each of the crossing points such as 3|, 32. 33, may be obtained between the under face of rotor 2 and the top face of stator 3. The stator 3 has a coaxial inlet H for the steam or vapor, orother?uid. Inlet|iextendsthroughthesur face in which stator channels I‘! are arranged to communicate with the center portion of the rotor channels i. The housing 6 is provided with a ?ange I2 so that bolts such as l3 may secure this flange to the ?ange Il on the stator outlets such as shown at~2| in the stator 20. In Fig. 2 the rotor channels are shown in full lines and comprise (a) an inner array 22, open at their inner ends to stator inlet l8, and closed each channel in the array 2'! to a plurality of channels in the array 23, at the crossing points thereof, such as indicated at 32, and from each channel in array 23 to a plurality of channels in indicated at 33. All such crossing points 3|, 32, 33progressradiallyoutwardasrotorI9rotates when passage I8 is an inlet. They progress radi ally inward when 2| is an inlet for reverse rota make possible a high velocity of fluid for a low speed of rotation ofthe rotor as well as multi stage expansion. . The ?uid from inlet l8 changes direction atPDF Image | AGE RADIAL FLOW TURBINE
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