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UnitedStatesPatent [,9] Chute [54] RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER [75] Inventor: RichardChute,HuntingtonWoods, Mich. [731 Assignee: EatonCorporation,Cleveland,Ohio [22] Filed: June24,1974 [21] Appl. No.: 482,808 Related US. Application Data [62] DivisionofSer.No.214,703,Jan.3,1972. [521 US. Cl. ..60/39.36; 60/39.65; 60/39.74S;415/186;415/202;60/39.75 151] Int. Cl.2 .. F02C 3/08; F02C 7/06; - F02C 7/22 [58] Field of Search .. 60/39.36, 39.75, 39.65; [ll] 4,000,609 [45] Jan. 4, 1977 radial out?ow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial in?ow turbine rotor secured to the other end of the central shaft member with itsdischarge end disposed outboard of the shaft assembly. The shaft assembly is supported atitsends,outboardoftherotors,byapairofbearings which are axially secured but allow limited radial movementoftheshaftassembly.An annularcombus tor is disposed between the turbine and compressor rotors in encircling relation to the central shaft mem ber. Fuel is supplied to the combustor chamber from the exhaustkend of the turbine through an axial passage in the shaft assembly opening at one end outboard of theexhaustendbearingandcommunicatingatitsother end with radial ports in the central shaft member ar ranged to sling fuel into the combustor chamber. The shaft assembly housing comprises two cast sections which are coupled together to enclose the combustor withtheendportionofeachhousingsectionshapedto de?ne a shroud for the radial blades of the turbine and compressor rotors, respectively. A cast nozzle plate and a diffuser plate are secured to the respective hous ing sections. The nozzle and diffuser plates each in clude an annular outer portion de?ning the vanes for the turbine and compressor rotors, respectively, and a centralhollowhubportionembracingthecentralshaft member of the shaft assembly; the inboard ends of the twohubportionsareaxiallyspacedtoexposetheradial ports in the central shaft member and allow slinging deliveryoffuelintothecombustor.An annularairinlet tothecompressorrotorspacestheshaftassemblyhous ing from a transmission housing, and the compressor end of the shaft assembly is coupled, outboard of the compressor end bearing, to speed reduction gearing journalledwithinthetransmissionhousing, 2Claims,7DrawingFigures 415/186, 202, 211" ReferencesCited UNITED STATES PATENTS 6/1956 Budworth ........................ 60/39.36 2,922,278 1/1960 Szydlowski ......... 156] 3,077,076 2/1963 3,115,011 12/1963 3,118,278 1/1964 3,199,294 8/1965 2,748,568 Williams et al. ................. 60/39.36 Hagen .. 60/39i3l FOREIGN PATENTS OR APPLICATIONS 675,752 12/1963 Canada ............................. 415/211 611,142 12/1960 Canada ............................ 60/39.36 PrimaryExaminer-CarltonR.Croyle Assistant Examiner-Robert E. Garrett Attorney, Agent, or Firm—Teagno & Toddy [57] ABSTRACT A smallgasturbineenginehavingasmall,highspeed shaft assembly including a central shaft member, a 254PDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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