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4,821,506 3 typicallywillincludedeswirlblades42ofconventional construction. Compressed air exiting the passage 40 enters an annu lar combustor, generally designated 44. The combustor 44 includes an annular outer liner 46 and an annular inner liner composed of spaced walls 48 and 50 and an end wall 52. The compressed air conventionally enters the combustor 44 and is mixed with fuel therein and ignited. The hot combustion gases then exit the combus tor 44 through an annular outlet 54. It should be observed that the walls 46 and 48 are generally concentric about the rotational axis of the shaft 10 with the consequence that the two de?ne an axial continuation of the passage 40, the continuation beingdesignated56. The turbine 18 includes a hub 58 mounted to the shaft 10 by any suitable means along with a plurality of arcu ate blades 60. The blades 60 have a radially outward facing in?ow end 62 and a generally axially directed out?ow end 64. The latter is in ?uid communication with an exhaust duct 66 while the former is in ?uid communicationwitharadiallyinwarddirected,annular throat 68 de?ned by spaced radial walls 70 and 72 con centric with the shaft 10. Thewall70includesanaxialextension74inreason 25 ablycloseradialproximitytotheaxialpassage40while the wall 72 includes a radial inward, axial extension 76. The extension 74 and 76 thus de?ne an axial passage 78 concentricwiththeshaft10andwhichextendsfromthe combustor outlet 54 to the radial passage 68 to termi nate at the in?ow edges 62 of the turbine blades 60. Located within the axial passage 78 is a plurality of equally angularly spaced vanes 80. The vanes 80 extend generally axially as can be seen from FIG. 2 which is a partial developed view looking radially inward on the vanes 80. The vanes 80 together with the axial exten sions74and76de?neanaxialnozzleforthecombustion gases being directed against the blade 60 on the turbine wheel 18. Eachofthevanes80ismountedonanintegralassoci 40 ated shaft 82 which, as seen in FIG. 1 isjournalled by bearings 84 on opposite sides of the passage 40. Thus, eachshaft82isjournalledforrotationaboutanaxisthat is generally transverse (at right angles) to the axis of rotationoftheshaft10. Radially outward of the passages 40, each shaft 82 is secured to an associated hub 86 which mounts an axially directed actuator arm or link 88. Each actuator arm 88 isconnected as by any suitable means to an actuator 90. Theremay beoneactuatorforeachofthevanes80but in a preferred embodiment, a single actuator 90 operat‘ ingthroughalinkageorthelikewillbeutilizedforal of the vanes 80. In any event, the angular position of the vanes 80 within the axial passage 78 can be varied in the direction 55 of arrows 92 and 94 shown in FIG. 2 to optimally match capabilities of the compressor 16 for various operating conditions with the ?ow of gasses from the combustor 44 to the turbine wheel 58 to achieve optimum operat ing ef?ciencies. As noted previously, this minimizes or avoids the compromises present in ?xed geometry tur bines necessary to provide a desired margin against compressor surge. In addition, the invention provides advantages over radial turbine nozzles heretofore knownbyprovidingbettercoolingforactuatorcompo 65 compressedgaspassageportioncontainingsaidcom nents. Note in particular that the shafts 82 extend pressedgaspathparalleltosaidaxialcombustiongas throughthepassage40throughwhichcompressedair pathwithinsaidfirstcombustiongaspassageportionof from the compressor 16 is?owing upstream ofthe com said combustion gas passage means. 4. bustor 44. As a consequence, the shafts 82 as well as the linkages including the hub 86, the arms 88 and the actua tor 90 are all located in relatively cool regions to mini mize thermal degradation of the movable components. Furthermore, because the resulting turbine nozzle is axiallydirectedasopposedtoaradiallydirectednozzle which conventionally would be located within the ra dial passage 68, the tip diameter of the turbine wheel 18 may beincreasedtoprovideahigheref?ciencyofoper 10 ation for a gas power plant of a given overall outer diameter. Finally, erosion problems frequently suffered in ra dial nozzle construction are minimized and/or avoided through use of an axial nozzle structure. Iclaim: 1.A gasturbinepowerplanthavingincombination: a radial out?ow compressor means and a radial in ?ow turbinemeanscoupledforsimultaneousrota tion about an axis of rotation; I means to deliver combustion gas from a combustor to saidradialin?owturbinealonganaxialcombustion gaspathconcentrictosaidaxisofrotation; means to deliver compressed gas from said radial out?ow compressor means to said combustor along withacompressedgaspathparralleltosaidaxial combustiongaspath;and rotatably mounted guide vane means positioned in said axial combustion gas path and having inte grallysecuredtheretorotatableguidevanecontrol elementmeansextendingthroughsaidcompressed gas path, said guide vane control element means being cooled by passage of said compressed gas. 2. The gas turbine power plant of claim 1 wherein said rotatably mounted guide vane means includes a plurality of guide vanes and said integral guide vane control element means are mounted for rotation about an axis which intersects at right angles said axis of rota tion. ‘ 3. The gas turbine power plant of claim 2 wherein saidcompressedgaspathislocatedradiallyoutwardof said combustion gas path. 4. The gas turbine power plant of claim 3 wherein said radial out?ow compressor and radial in?ow turbine are mechanically secured to a rotatably mounted shaft 45 andarepositionedimmediatelyadjacentoneanother. 5. The gas turbine power plant of claim 4 wherein said means to deliver combustion gas from a combustor include a combustion gas passage means having a ?rst combustion gas passage portion positioned to transmit saidcombustiongasinsaidaxialcombustiongaspathto asecondcombustionpassageportionthattransmitssaid combustion gasesinaradialinward directiontoward said axis of rotation and into said radial in?ow turbine means. 6. The gas turbine power plant of claim 5 wherein said guide vane means islocated in said ?rst combustion gas passage portion. 7. The gas turbine power plant of claim 6 wherein said means to deliver said compressed gas from said radial out?ow compressor means includes a compressed gas passage means having a ?rst compressed gas passage that transmits said compressed gas in a radial outward direction away from said axis of rotation and into a second compressed gas passage portion, said secondPDF Image | Radial Turbine 1987
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