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1 4,821,506 by the passage of the compressed gas through such 2 path. In addition to the advantages of improved cooling along with an increase in efficiency because of the abil ity to improve the matching of the components, the invention has the further advantage of allowing the use of a larger diameter at the turbine rotor tip which thus provides higher efficiency. It also minimizes or elimi nates the problem of nozzle erosion in radial nozzles 10 thatarecommonlyemployedinradialin?owturbines. Theinventionalsocontemplatesthatthepluralityof therotatableguidevanesbeindividuallymountedabout axes which intersect the axis of rotation of the turbine at rightangles. In a preferred embodiment, the compressed gas path is located radially outward of the combustion gas path. The invention also contemplates that the compressor and the turbine be mounted on a single shaft and posi tioned generally immediately adjacent to one another. The invention contemplates that the combustion gas passage means include an axial combustion gas path section in which the vanes are disposed and which ter minates in a radially inward directed combustion gas path section that focuses on the turbine. Variableturbinenozzleshavebeenusedtoavoidthe 25 compromisesbyallowingtheturbinetomatchoptimum compressoref?ciencies.Heretofore,inthecaseofradial in?ow turbines, radial turbine nozzles have been uti lized.An exampleofthistypeofmachineisillustrated inareportentitled,“InterimreportAFFDL-TR-77-68, withtheaccompanyingdrawings. VolumeI”forperiodMay 1976-July1976,obtainable fromtheAirForceFlightDynamicLaboratory(FED), _ RADIAL TURBINE WITH VARIABLE AXIAL NOZZLE FIELD OF THE INVENTION This invention relates to turbines having a radial in?ow to a turbine wheel, and more speci?cally, to the provisionofanaxiallydirected,variablenozzleforsuch a turbine. BACKGROUND OF THE INVENTION Auxiliary power units in the form of small gas tur binesmay beprovidedforvariouscombinationsofshaft power output and compressed air output. Typically, theyareofeithertheso-called“integralbleed”or“load compressor”type. Extractionofcompressordischargeairintheintegral bleed auxiliary power units without concurrent shaft power output (zero concurrent shaftpower output) plus 20 requirements to operate in a 100% shaftpower mode only(zerobleedairoutput),resultinperformancecom promisesnecessarytomaintainadequatemarginagainst compressor surge. Wright-Patterson Air Force Base, Oh., 45433, pages 86-95 thereof dealing with variable nozzle geometry. Whilesuchgeometryisofassistanceinovercoming 35 the performance compromises mentioned above, an other dif?culty exists. Speci?cally, the components of the variable nozzles when applied to a radial in?ow turbine are operating in a relatively hot environment. Both the nozzle vanes and the actuating mechanism thereforeissubjectedtotheheatwiththeconsequence that power plant life and reliability may be lessened. The present invention isdirected to overcoming the foregoingproblems. SUMMARY OF THE INVENTION Itistheprincipalobjectoftheinventiontoprovidea new and improved gas turbine power plant. More spe ci?cally,itisanobjectoftheinventiontoprovideanew and improved gas turbine power plant of the type hav ing a radial in?ow turbine with an axial ?ow, variable turbinenozzle. FIG. 1 is a fragmentary sectional view of a gas tur bine power plant made according to the invention; and FIG.2isafragmentary,enlarged,developedviewof a turbine nozzle. DESCRIPTION OF THE PREFERRED EMBODIMENT An examplary embodiment of a gas turbine power plant made according to the invention is illustrated in the drawings and with reference to FIG. 1, is seen to include a shaft 10 journalled by bearings 12 (only one set of which isshown) for rotation about an axis. The An exemplaryembodimentoftheinventionachieves theforegoingobjectsinaturbinepowerplantincluding a radial outflow compressor and a radial in?ow turbine coupled for simultaneous rotation about an axis of rota tion. Means are provided to deliver combustion gas from a combustor to the radial in?ow turbine along an axialcombustiongaspathconcentrictotheaxisofrota~60 asiswellknown. tion along with means to deliver compressed gas from the radial out?ow compressor to the combustor along a compressed gas path parallel to the axial combustion gaspath. Rotation of the compressor 16 will cause inlet air to be compressed and expelled from the compressor in a radial direction through the diffuser 26 which converts a velocity head to a pressure head. An annular elbow Guidevanesarerotatablymountedandpositionedin65 shapedpassage38concentricwiththeshaft10andon the axial combustion gas path and are provided with integral rotatable guide vane control elements that ex tendthroughthecompressedgaspathsoastobecooled the outlet side of the diffuser 36 redirects the radial compressedair?ow generallyaxiallythroughanaxial passage 40 (also concentric about the shaft 10) which An actuator is coupled to guide vane control ele ments and may be operated by suitable means to pro vide for position control of the guide vanes. Other objects and advantages will become apparent from the following specification taken in connection DESCRIPTION OF THE DRAWINGS 45 shaft 10 may include gear teeth 14 which serve as a power take-offmeans. The shaft 10 has fixedly secured thereto a radial out ?ow compressor, generally designated 16, and a radial in?ow turbine, generally designated 18. The compres sor 16 includes a plurality of blades 20 (only one of which is shown) mounted on a hub 22 which in turn is secured to the shaft 10. Each of the blades 20 has a discharge end 24 which is radially directed toward a diffuser 26 of conventional construction. Each blade 20 also includes an axially directed in?ow end 28 directed toward an air inlet such as shown at 30. Inlet guide vanes 32 may be located between the inlet 30 and the vane ends 28. The vanes 32 may be conventionally rotatable about axes 34 and be driven by an actuator 36PDF Image | Radial Turbine 1987
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