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4,000,609 12 RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER This is a division of Application Ser. No. 214,703 ?led Jan. 3, 1972. BACKGROUND OF THE DISCLOSURE Anti-pollution laws create grave problems with re spect to the continued use of internal combustion en gines. The new laws establish regulatory authority with respect to al engines rather than to only automobile size engines. Exhaust emission standards for small power ranges, e.g. 15 to 50 horsepower, are foreseen as a natural consequence of these laws. lnherently, a gas turbine engine is a low air polluting device.A majordrawback,however,tothelargeusage of small gas turbines istheir high cost relative to com parable size reciprocating engines. If such costs could be signi?cantly reduced without a sacri?ce in ef? 20 ciency,itisconsideredthatgasturbinesinthe 15to50 horsepower range could displace the reciprocating engine in many product areas. It is accordingly a primary object of the present in ventiontoprovideasmallgasturbineenginewhich,25 whileatleastasef?cientasknown designs,isconsider ablylessexpensivetomanufacture. BRIEF SUMMARY OF THE INVENTION Theinventionengineisofthesingleshafttypeand30 includesasmallhighspeedshaftassemblycomprisinga central shaft member, a radial turbine rotor at one end of the shaft member, and a radial compressor rotor at theotherendoftheshaftmember.An annularcombus tor encircles the central shaft member between the 35 turbine and compressor rotors. fuel ispassed axialy through this bearing for cooling purposes. According to yet another feature of the invention, the shaft assembly housing comprises two cast sections which are coupled together to enclose the combustor withtheendportionofeachhousingsectionshapedto de?ne a conforming shroud for the radial blades of the turbine and compressor rotors, respectively. The end portion of the housing section associated with the tur bine rotor is further shaped to provide a horn or funnel portion which centrally supports the turbine end bear ing and de?nes an annular exhaust passage around this bearing. According to a further feature of the invention, a nozzle plate cast diffuser plates ae secured, respec tively, to the two cast housing sections; the nozzle and diffuse plates each includes an annularouter portion de?ning the vanes for the turbine and compressor to tors, respectively, and a central hollow hub portion embracingthecentralshaftmemberoftheshaftassem bly. The inboard ends ‘ofthe two hub portions are axi ally spaced to expose the radial ports in the central shaft member and allow slinging delivery of fuel to the combustor. Accordingtoanotherfeatureoftheinvention,the combustor comprises two annular stampings with the radially inner periphery of each stamping seated around a respective hub portion of the nozzle and dif fuserplate. Accordingtostilanotherfeatureoftheinvention, theradiallyouterperipheriesofthecombustorstamp ingsarearrangedinconcentric,radiallyspacedrelation to de?ne an annular, axially extending exit passage for the combustor gases, the turbine end nozzle plate and associated housing section de?ne an annular, radially extending passage leading to the nozzle vanes sur roundingtheturbinerotor,andtheradiallyouterpe ripheries of the combustor stampings seat on concen tric,radiallyspacedsurfacesde?nedbytheturbineend nozzleplateandtheassociatedhousingsectionatthe entrance to the radially extending passage leading to the turbine rotor nozzle vanes. According toa stilfurtherfeature ofthe invention, a pluralityofcircumferentiallyspaced pairsofradialy alignedopeningsareprovidedintheportionsofthe combustor stampings de?ning the annular, axially ex tending exit passage from the combustion chamber, and a short sheet metal tube is slip ?tted in each pair of radiallyalignedopenings.Inthedisclosedembodiment, eachtubeincludesatabatitsradiallyouterendabut tingly engaging the adjacent inner housing surface to maintain the tubes in position and facilitate assembly. These and other objects, features and advantages of the present invention will become apparent from the drawingsandfromthedetaileddescriptionofapre ferred embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a fragmentary, side elevational view, in section,ofagasturbineengineaccordingtotheinven tion, taken on an axial plane passing through the center oftheengine. Manyenginedesignfeaturescontributetothesim~ ple, inexpensive and efficient nature of the invention engine. 40 According to one design feature of the invention engine, fuel is delivered to the combustor through an axialpassagewhichextendsthroughtheturbineendof the shaft assembly and terminates in radial ports in the centralshaftmemberarrangedtoslingfuelintothe45 combustor. According to a further feature of the invention en~ gine, the end of the shaft assembly opposite the end through which fuel is delivered is coupled to a speed reducingtransmissionsothatfuelisdeliveredthrough 50 one end of the shaft assembly while power is taken off of the other end of the shaft assembly. In the disclosed embodiment, fuel enters through the turbine end and power is taken off at the compressor end. Accordingtoanotherfeatureoftheinventionengine,55 the compressor end of the shaft assembly is coupled to aspeedreducingtransmissionandtheshaftassemblyis supported in a suitable housing by a pair of outboard bearings with one bearing disposed outboard of the turbinerotorandtheotherbearingdisposedbetween 60 thecompressorrotorinletandthecouplingoftheshaft assembly to the speed reducing transmission. According to stilanother feature of the invention, theturbinerotorisaradialin?owunitarrangedwithits dischargeoutboardofitsinlet,thebearingsupporting65 FIG.3isasectionalviewtakenonline3—3ofFIG. the turbine end of the shaft assembly is disposed out boardoftheturbinerotordischargeinthepathofthe hot exhaust gases from the turbine, and the incoming FIG. 2 isan end view of one part of the combustor embodied intheturbineofFIG. 1. 2. FIG.4isasectionalviewtakenonline4-4 ofFIG. 3.PDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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