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UnitedStatesPatentO 1ice 1 3,465,518 Patented Sept. 9, 1969 2 3,465,518 RADIAL OUTFLOW TURBOSHAFT ENGINE .lohn R. Erwin, Cincinnati, Ohio, assignor to General Electric Company, a corporation of New York Filed Dec. 14, 1966, Ser. No. 601,669 Int. Cl. F02g 3/00; F02c 7/08, 3/08 blades. Adjacent the compressor there is provided a free wheeling power turbine disc that is axially spaced on the shaft .and this, in turn, is followed in axial spacing by a radial outflow turbine that is connected to drive the com pressor. Means are provided to connect the compressor outlet and the turbine inlet and a combustor is disposed in the connecting means. The turbine has a curved inlet and highly cambered buckets radially out from its inlet to receive substantially radially flowing fluid only and is alsofollowedbyarotatingturbinevanelessdiiiuserex tending beyond the cambered buckets. The free-wheeling power turbine disc extends radially beyond both the coni pressor and turbine diffusers and is provided with turbine buckets on the disc which are disposed in the turbine ex haust for work extraction. The other side of the disc may be provided with additional compressor stages to raise the static and total pressure. A power takeoff means is suitably connected to the disc so that the turbine drives the compressor and the turbine exhaust drives the disc. Additional refinements including regenerator means dis posed`in the connecting means for preheating the com pressor liuid may be provided in combination with a thermosyphon for bucket cooling. While the specification concludes with claims particu larly pointing out and distinctly claiming the subject mat ter which is regarded as the invention, it is believed the invention will be better understood from the following de scription taken in connection with the accompanying drawing inwhich: FIG. 1isapartialcross-sectionalviewillustratingthe general compact turboshaft engine with the airfoil blading projected to show its positioning; FIG. 2 is a view similar to FIG. 1 showing a modiñca tionemployingturbinestaging;and FIG. 3 is another modiiication of a cooling flow ar rangement that retains the bucket cooling air in the cycle as well as the heat that is extracted from the turbine buckets. The present invention uses a known radial outiiow com pressor of the type disclosed and claimed in co-pending application Ser. No. 243,561, filed Dec. 10, 1962, now abandoned, and of common assignment. It also uses a radial outflow turbine of the type shown in co~pending ap plication Ser. No. 472,486, ñled July 16, 1965, now PatentNo.3,378,229,andofcommonassignment.These co-pending applications relate to a unique compressor and turbine respectively and are thoroughly described in said applications. Consequently, the terms radial outflow com pressor and radial outflow turbine used herein are in tended to be components of the type described in said co-pending applications. To these known components there is added a free-wheeling power turbine disc in a unique combination to provide the compact engine of the presentinvention. -Referring ñrst to FIG. l, there is shown the compact engine that comprises a shaft 10 that is mounted for rotation in bearings 12 suitably supported from an outer housing 14 through struts 16. In order to provide air compression and a high pressure ratio, there is disclosed US. Cl. 60-39.16 ABSTRACT OF THE DISCLOSURE 3 Claims 10 A turboshaft engine comprises a radial outflow corn pressor connected in series flow relationship with a radial outflow turbine. Combustor means .are interposed between the compressor and turbine to providemeans for generat ing a hot gas stream. A power turbine, comprising a dlsc having a-circumferential cascade of turbine blades‘is disposed in the hot gas stream discharge from the radial outflow turbine. The disc is connected to .a shaft to pro vide a power takeoff. Regenerator means are shown in which the hot gas stream, after it passes through the 20 power turbine, preheats the discharge of the compressor beforeitentersthecombustormeans. The present invention is directed to a compact high efficiency engine that uses a radial outflow compressoras `ahigh pressure ratio machine and a radial outñow turbine as a high work capacity machine in back-to-back arrange ment with a free-wheeling power turbine between. The radial compressor and turbine outlets are close together 30 permitting the Ause of a regenerator in .a close coupled ar rangement to provide a compact regenerative engine. There is a general need for compact high eñiciency and low specific fuel consumption (SFC) engines in many capacities. For example, a small high powered engine lfor 35 use in tanks is desired where the engine is efficient during longrunningtimesatlowpower.A similarengineofconi pact arrangement may be used in an aircraft where 1t would run at high power mostl of the time. A common engine is desired that may use a regenerator means for reducing fuel consumption at low power in a military tank or may eliminate the regenerator and use the same compact engine in an aircraft. Furthermore, the engine should eliminate, as much as possible, any complex gear ingortransmissionstructureandyetbeabletoidleunder45 aloperatingconditionsandapplications. The main object of the present invention is to provide .a compact combination radial outflow compressor-radial outflow turbine engine with a free-wheeling power turbine. Another object is to provide a compact engine of the type described which uses known components and adds a free-wheeling turbine to provide a new combination. 40 50 A furtherobjectistoprovidesuchanenginethatlends itself to staging in either the compressor or turbine corn ponentstoprovideforadditionalpressureratiosorwork 55 extraction stages or both. Another object is to provide such a compact engine that utilizes `an efficient cycle, provides high pressure ratio, provides regeneration as needed, all at a low SFC. Brieiiy stated, the invention provides a radial outflow 60 a radial outflow compressor generally indicated at 18 turboshaft engine that has a shaft, a radial outflow com pressor that is rotatable on the shaft and has highly cam bered rotor blades on the compressor at a radial distance from the shaft so that the blades receive substantially radially flowing ñuid only. The compressor includes a rotating vaneless diffuser that extends beyond the rotor which has highly cambered rotor blades 20 at a radial distance from the shaft, the arrangement being such that thebladesreceivesubstantiallyradiallyflowingfluidonly as defined in the referenced co-pending application Ser. No, 243,561 and now abandoned. In order to raise the static pressure, the rotor or compressor blades are folPDF Image | RADIAL OUTFLOW TURBOSHAFT ENGINE
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