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UnitedStatesPatentOffice 3,412,978 Patented Nov. 26, 1968 12 3,412,978 RADIAL FLOW TURBINE OR COMPRESSOR ROTOR FIGURE 7isagraphillustratingthe?ow characteristics oftherotorshowninFIGURE 6. Referring to the drawings, there is shown a gas turbine engine 10 comprising a radial flow compressor 11, combus John Gregory Keenan and John Alexander Henderson Scott, Derby, England, assiguors to Rolls-Royce Lim UK tiOn equipment 12 and a radial ?ow turbine 13. Radial ited, Derby, England, a British company FiledJuly21,1966,Ser.No.566,910 ?ow turbine 13 includes a radial ?ow rotor 14, comprising ahub 15onwhichtherearemounted apluralityofradial ly extending blades or vanes 16. As more clearly seen in FIGURE 6,therotorisformedontwoportionsconnected the rotor blades thicken compared with those of a con ventional turbine rotor, whereby the cross-sectional area of the ?ow passage de?ned between them is decreased. IndicatedonFIGURE 6isanareaC,de?nedwithina brokenoutline,thisareaindicatingthatinwhichthevanes 16arethickenedtoprovidethedecreaseincross-sectional area which enables a constant decrease in area to be ob tained. Thus, the thickening of the vanes shown in FIG URES 2 to 5 is achieved by thickening the vanes in the areaC,theremainingpartsofthevanesbeingleftattheir original thickness, i.e. that shown, for example, in FIG Claimspriority,applicationGreatBritain,Aug.6,1965, 33,872/65 3 Claims. (Cl. 253-39) 10 togetherbyfourdowelpins17. r The cross-sectional form of the blades or vanes 16 is shown indetailinFIGURES 2to5.The fullline?gures illustrate the cross sectional shape of the modi?ed rotor in accordancewiththepresentinventionandthebrokenline inlet and an outlet with vanes extending from the inlet 15 indicates the form of the blades on a conventional radial ?low turbine rotor. It will be noted that the rotor blades arethesame attheradiallyouterportionoftherotor,but, as the radially inner portion of the rotor is approached, ABSTRACT OF THE DISCLOSURE A radial flow compressor or turbine rotor having an to the outlet and de?ning ?ow passages therebetween. The radially inner portion of the vanes are thicker than the radially outer portions and the opposite axial ends of the rotor are of different diameters. Each of the vanes also has a thickness measured at a constant radius with respect to the axis of rotation which increases with increasing dis tancefromtheendoftherotorofsmallerdiameter.These featuresoftherotorprovideeach?ow passagewithan effective?ow cross-sectionalareavaryingatasubstantial ly constant rate from the inlet to the outlet of the rotor. This invention concerns radial ?ow turbine or com pressor rotors and, although not so restricted, itwill here inafter be described with reference to itsuse on a radial 30 URE 2. ?ow turbine for a gas turbine engine. In conventional radial ?ow turbine rotors, the vanes are Referring now to FIGURE 7, the curved graph A in dicates the variation in ?ow area of the flow passages de ?ned between adjacent vanes on a typical conventional turbine, i.e. that having vanes in accordance with the substantially constant in cross-sectional area, and it has been found that the effective ?ow cross-sectional area of theflowpassagede?nedbetweenadjacentvanesvaries35 brokenoutlineshowninFIGURES2-5.Itwillbenoted substantially along the ?ow path through the rotor. Thus, in a conventional radial ?ow turbine, it has been found that, from the inlet, the ?ow cross-sectional area of the flowpassagesmayincreasebyasmuchas50% andthen decreasebysomewhatmorethantheinitialincreasetoa40 atedthatsuchavariationincross-sectionalareadiscour ?nal cross-sectional area somewhat less than the inlet cross-sectional area. It will be appreciated that such varia tion in cross-sectional area hinders smooth flow of the ?uid through the rotor, thus causing losses due to turblence. According, therefore, to the present invention there is providedaradialflowturbineorcompressorrotorhaving radially extending vanes de?ning ?ow passages therebe tween, the radially inner portions of each vane being thicker than the radially outer portions thereof so that theeffective?ow crosssectionalareaofeachflowpassage variesatasubstantiallyconstantratefromtheinlettothe outlet thereof. In a preferred embodiment, the rotor has opposite axial ends of different diameter and the thickness of each vane, measured at a constant radius with respect to the axis of rotation of the rotor, increases, at least in the radially in ner part of the rotor, with increasing distance from the smaller diameter end of the rotor. The rotor may form part of a radial flow turbine, the ?ow cross-sectional area of each ?ow passage decreasing at a substantially constant rate in the downstream direc tion. Said turbine may be that of a gas turbine engine. The invention isillustrated, merely by way of example, in the accompanying drawings, in which: FIGURE 1isabroken-awayelevationofagasturbine engine including a radial flow turbine in accordance with the present invention, FIGURES 2 to 5 are cross-sectional views on the lines 2-2, 3—3, 4—4 and 5-—-5 of FIGURE 1, FIGURE 6isacross-sectionalviewtoalargerscaleof partoftheradial?owturbineshowninFIGURE 1,and ages smooth ?ow of ?uid through the rotor and creates turbulence and thus loss in efficiency. The linear graph B indicates the ?ow passage charac teristic with a rotor in accordance with the present inven tion, i.e. having blades 16 in accordance with the full line arrangementshowninFIGURES 2-5.Itwillbeappreci atedthatthethickeningofthevanes16adjacenttheradial ly inner portion of the rotor ‘decreases the cross-sectional area of the ?ow passages adjacent the radially inner por tionoftherotor,andthusthesubstantialincreaseincross sectionalareaindicatedbygraphA isreducedandthe linear form of graph indicated at B is produced. With such a form it will be appreciated that the decrease in cross sectional area of each ?ow passage in a downstream di rection is constant, and thus smooth ?ow of the ?uid is obtained. It will be ‘appreciated that the ?ow characteristics of a radial ?ow rotor in accordance with the present invention are greatly enhanced compared with those of a conven tional radial ?ow rotor. It will be appreciated that the invention is not restricted to use in a radial ?ow turbine, but may, for example, be employed in a radial flow compressor. The ?uid in this case will ?ow radially outwardly and thus the ?ow pas sagesbetweenadjacentvanes“willeffectivelyincreaseata substantially constant rate in a downstream direction. We claim: 1. A radial ?ow rotor having an inlet and an outlet ad jacent opposite axial ends and vanes extending from the inlettotheoutletandde?ning?owpassagestherebetween, saidaxialendsofsaidradialflowrotorhavingdifferent that the flow passages commence with an area of approxi mately 2.5 square inches which increases to nearly 3.5 square ‘inches and then decreases to somewhat less than 2 inchesadjacenttheoutlettotherotor.ItwillbeappreciPDF Image | RADIAL FLOW TURBINE OR COMPRESSOR ROTOR
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