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5 The same concept of the two~dimensional radial flow only in combination with the rotating diffuser may be used in a dual entry turbine as shown in FIGURE 3. Similar reference numerals in the one hundred series are applied to similar but not identical parts and, with dual gas entry, it is believed that the arrangement is self explanatory.Balancingproblemsaresimpli?edinthedual arrangement and the problem of getting the gas?ow throughthe“eye”oftheturbineimpeller,thatis,thecir cular opening 23 is reduced. In a single entry turbine this dimension 23 becomes a limiting one. The opening 23 must be of a certain diameter in order to let the gas?ow pass into the rotor at a low enough velocity so that losses aresmall.By usingthedualentry,thislimitationisgreatly alleviated. It provides the rotor buckets at a smaller di ameter as well as allowing the location of the rotor dis charge at a smaller radius. In very small high speed tur bines this can be signi?cant in the overall efficiency of the machine. FIGURE 4illustratespartiallythenozzle,bucket,and vane layout of the dual entry arrangement showing the outlet guide vanes 18 pivotable as previously described although it is to be understood that this adjustable fea turemay ormay notbeusedasnecessary. boundary layer problem. It may be desirable to provide more diffusion or pressure rise in the vaneless diffuser and less in the vaned area and this may be accomplished by varying the passage width of the chamber 25 and the vaneddiffuser218shownofequalwidthinFIGURE 6. Similarly, itwill be understood that vaneless chamber 25 may beusedinthefreelyrotatabledi?userofFIGURE 5 merely by shortening vanes 18 as shown at 218 in FIG URE 7.Thus,thediffusingchamber25withvaneddif fuser218asshowninFIGURE 7ismadefreelyrotatable likethatofFIGURE 5. It can be seen that the instant invention provides for all the advantages of a two-dimensional ?uid ?ow ma chine such as a turbine in combination with a rotating 70 said chamber having a radial depth of substantially ten percent of the radial distance from the shaft center to the periphery of said discs. 7. Apparatus as described in claim 6 wherein said vane lessdiffusingchamberandsaidvaneddiffuserarefreely rotatable about said shaft. 8.A radialout?owturbinecomprising, a rotor disc, a shaft carrying said disc for rotation thereon, second discs concentric with and axially spaced from said rotor disc one on each side thereof, said second discs being spaced radially from said shaft and formed to de?ne with said rotor disc on unob structed curved inlet ?uid passage between the rotor 3,378,229 6 diffuser resulting in a simple single stage construction to obtain work output and high efficiencies obtainable here tofore only in multistage axial turbines. Very high work output can be obtained by employing supersonic flow in the turbine nozzles and supersonic ?ow relative to the turbine buckets rotating at high speed. Both centrifugal pressure rise and the usual aerodynamic pressure rise are present with the rotating diffuser in combination with the two-dimensional ?ow to recover most of the kinetic energy of the exhaust gases. The sealing and tip leakage prob lems are reduced and the boundary layer is centrifuged and energized in the rotating diffuser means. While there have been described preferred forms of the invention, obviously many modi?cations and varia tions are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced other wise than as speci?cally described. I claim: 1.A radialout?owturbinecomprising, a rotor disc, a shaft carrying said disc for rotation thereon, a second disc concentric with and axially spaced from said rotor disc, saidseconddiscbeingspacedradiallyfromsaidshaft and formed to de?ne with said rotor disc an unob structed curved inlet ?uid passage between said discs to direct ?uid radially outward between the discs, stationary turbine nozzles in said ?uid passage to re ceiveradially?owing?uidonlyandimparttangen tialvelocitythereto, seriate means arranged radially outward including, highly cambered turbine buckets secured to said discs at a radial distance from said shaft so that the buckets receive substantially radial ?owing ?uid only, said discs and buckets rotating as a unit opposite to thedirectionofcamberofthebuckets, acasingsurroundingsaidunit, said discs extending radially beyond the periphery of said buckets to form a rotating vaneless diffuser pas sage, a vaned diffuser radially spaced from said diffuser pas sage, and collecting means following said vaned diffuser for col lecting the ?uid therefrom. 2. Apparatus as described in claim 1 wherein said tur bine buckets are of constant untwisted cross-section. . 3. Apparatus as described in claim .1wherein said tur bine nozzles are adjustable and carried by said casing in said inlet ?uid passage inward of said turbine buckets, and seal means on each disc between the disc and easing 3nddisposedradialyinwardoftheperipheryofthe be rotating as shown in FIGURE 7 if desired. Thus, FIGURES 5 and 7 may be the modi?ed outer end of FIGURES 1and3.Itisdesirablethatthischamber25 have a radial depth of substantially ten percent of the radial distance from the center of rotation of the shaft to the periphery of the discs 10 and 12 in order to pro vide satisfactory ?ow characteristics by avoiding exces sivefrictionlossonthewallsduetoboundarylayerbuild 60 ofthediscsandsaidvaneddiffuser, up. Additionally, rotation, as noted above, reduces the A furthermodi?cationthatmightbeemployedinorder 25 to overcome boundary layer problems in vaned diffuser 18 is illustrated in FIGURE 5. As previously explained in connection with FIGURE 1, it may be necessary to provide suction boundary layer control means in vaned diffuser18forthereasonsgiven.Ifsuctionboundarylayer control is used as opposed to boundary layer blowing it will be apparent that the gas removed is from the cycle itself. The result of bleeding gas from the cycle is lost energy. Modi?cation of FIGURE 1 to the structure of FIGURE 5 provides a freely rotatable vaned diffuser 24 that may rotate about the casing 21 in any suitable man ner as diagrammatically illustrated. This achieves a boundary layer control without bleeding the gas from the cycle. Again, rotation provides means for energizing the boundary layer in the vaned diffuser by centrifugal force on the boundary layer. Of course, the rotating diffuser 24 might be used to provide shaft power by connecting it to a suitable load. In the event that the required diffusion is not obtain able in the rotating diffuser passage 17 and vaned diffuser 18 of FIGURES 1 and 3, another feature may be used in combination with the structure herein as shown in FIGURE 6.Inthis?gure,whereinthetwohundredseries isusedtoidentifysimilarbutnotidenticalparts,asshown, a separate stationary vaneless diffusing chamber 25 is provided between vaned diffuser 218 and vaneless diffuser passage 17. It will be understood that chamber 25 could 30 4. Apparatus as described in claim 1 wherein the vanes in said vaned diffuser are adjustable. 5. Apparatus as described in claim 1 wherein said vaned diffuser is freely rotatable about said shaft. 6. Apparatus as described in claim 1 wherein a vane less diffusing chamber isprovided between the peripheryPDF Image | ERWIN RADIAL FLOW TURBINE
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