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3,465,518 34 lowed by a rotating compressor vaneless diffuser 22 to provide a very high pressure ratio compressor all as fully described in said co-pending application. In order to drive the compressor, there is provided axially spaced and in a ‘back-to-back arrangement, a radial outflow turbine generally indicated at 24. As such, it is provided with a curved inlet 26 and highly cambered buckets 28 radially out from the inlet to receive sub stantiallyradiallyfiowingfiuidonly. Suitablenozzles30may beprovided,asrequired,and these may be variable by a pivot means 32 in two parts, as shown. Similarly, the turbine buckets are followed by a rotating turbine vaneless diffuser 34. This arrange ment provides a radial outflow turbine of the type de scribed in said co-pending application Ser. No. 472,486, now Patent No. 3,378,229. most of the time and the regenerator may be omitted if desired. Referring next to FIG. 2, a modification is shown which is quite similar with the exception that the combustor 62 may be more flatly rearranged as shown and, more im portantly, the disc 36 is provided with an additional turbine lbucket stage 64 radially outward from buckets 40. This may require the use of variable nozzles 66 for the same purpose as nozzle y42 in FIG. l. Thus, a series of'stagesisprovided.Theuseoftheadditionalstagesper mits the extraction of the same amount of power at lower speed reducing any transmission or gearing and permit ting a closer match to a fan if one is used in an air craft powerplant. In other words, the additional stages permit power extraction at lower speeds. The rest of the power plant shown in FIG. 2 is substantially the same asFIG. 1. Inordertoprovidepowertakeoffmeansfromthecom bination of the radial outñow compressor driven by the radial outflow turbine, a free-wheeling power turbine disc 36 is disposed on shaft 10 sandwiched between the corn 20 No. 273,003, filed Apr. l5, 1963, now Patent No. pressor and turbine and independently rotatable about shaft 10. To extract and transmit power, the disc must extend radially 'beyond the compressor and turbine dif fusers as shown at 38. Power is extracted by means of turbine buckets 40 located in the turbine exhaust and carried by the disc extension. Proper entrance to the turbine buckets may be obtained by variable nozzles 42 carried by the housing beyond the diffuser 34. Thus, the free-wheeling disc 36 extracts the work in the turbine ex haustbymeansofbuckets40andistherebydrivenby30 ingairfiowthroughpassage70.Thismannerofcooling the turbine exhaust. Any suitable power takeoff may be provided and the compact arrangement described lends itself very well to a power takeoff of a concentric shroud 44 that may be carried from extension 38 by struts or additionalcompressorstages46andissupportedbybear ings 48 through struts 50 to drive the power takeoff means l52 which may be hollow to start the engine through shaft 10. is generally shown and described in said co-pending ap plication. The air is then funneled out through the re generator 58 and continues back through the turbine buckets 28 in the same manner as the modifications of FIGS. land2.Suchanarrangementprovidesaregenera tive system which does not require that the cooling air be lost to the cycle since all the cooling air in passage ’70 is subsequently heated by the combustor and used. Additionally, the heat that is removed from buckets 28 Since the free-wheeling power turbine disc 36 is inde pendentoftheothercomponents,itmaybeco-rotating40 bytheliquidmetalistransferredtotheincomingcooling in which case the various turbine airfoils assume the con figuration shown at the side of FIG. 1 or preferably, it may be counter-rotating as also shown projected in FIG. l. The counter-rotation has advantages of reducing the rotation of the bearings about shaft 10 and thus the wear. Also,inaircraftapplicationsthecounter-rotationcancels gyroscopic effects within the framework of the compres sor and may provide additional pressure ratio when a two stage compressor having blades 20 and 46 is used. It should also be noted that this structure permits the use of an additional rotating diffuser 54 at a large radius ratio which is efficient in reducing the high Velocity fiow in the compressor before the final stators `56 in the housing 14. air in passage 70 so that heat is not lost to the cycle. In other words, this general arrangement provides that the cooling air and the heat extracted are Iboth maintained in the cycle to reduce losses. The general combination of the radial outfiow compres sor and the radial outflow turbine with the freely ro tating power turbine disc between, with or Without the re generation, thus permits a very compact, high efficiency, low SFC engine that has wide application for either low power extraction or high power extraction for a wide va riety of uses. This general combination is common to all three of the figures disclosed and the general combina tion may be modified by multi-staging the compressor or the turbine or both and by rerouting the compressor The arrangement just described provides for a very closecoupledcommonoutletorexitfromthecompressor 55 airsothatitisusedforcoolingwhentheapplicationde» and turbine as shown. This lends itself to the use of a regenerator 58 in the exhaust to preheat the compressor air ahead of the turbine inlet. The high pressure ratio air from compressor 18 is directed to the turbine inlet by suitable connecting means 60 and this compressed air has energy added by combustor ‘62 in the connecting means. By the close coupled exit arrangement, regenera tor 58 may ‘be disposed in the connecting means and con nected to the turbine exhaust. By being disposed in the connecting means, it can be seen that the turbine exhaust preheats the compressor fluid before it has its energy level raised by combustor 62 and is directed into the tur bine. All this is provided by the close coupled exits from the compressor and turbine and provides an over allcompactandflatpowerplantpackagethatmaybe70 meansinsaidpassagewaymeansforburningfuelto used with or Without the regenerator. The use of this engine in a military tank requires much running at low power. The regenerator 58 is a way of considerably re ducing the fuel consumed during low power operation. In anaircraftapplicationtheenginewouldrunathighpower 75 charge to the hot gas stream inlet, generateahotgasstream, said first and second rotors having radially aligned, concentric blades forming a radial outflow turbine, said first rotor comprising a shaft journaled at one endonthehotgasinletbearingandapairofaxially Referring to FIG. 3, an arrangement employing the general concept disclosed in co-pending application Ser. 3,314,649, of common assignment, may be used. This application illustrates the use of a thermosyphon wherein liquid sealed cooling means 68 such as liquid metal may ybeused. This modificatiin requires a reverse flow arrange ment through passage 70 which brings the compressor air in close to the axis of rotation where it is then passed across an extension portion 72 to the turbine blades where, by means of fins 74 the heat picked up in the ex haust gas passage of the turbine is removed by the cool mands. While there have been described preferred forms of the invention, obviously modifications and variations are possibleinlightoftheaboveteachings. What isclaimed is: 1.A turboshaftenginecomprising, a main housing having spaced, coaxial bearings at its opposite ends and air and hot gas inlets, respectively, surrounding said bearings, first and second rotors, said first and second rotors hav ing radially aligned, concentric impellers forming a radial outflow compressor, passageway means for ducting the compressor dis~PDF Image | RADIAL OUTFLOW TURBOSHAFT ENGINE
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