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4,000,609 34 FIG. 5 is an end view of another part of the combus torillustratedinFIG. 1. . FIG.6isasectionalviewtakenonline6_6 ofFIG. 5. ‘ FIG. 7 is a sectional view taken on line‘7—7 of FIG. 6. , DETAILED DESCRIPTION OF THE'DRAWINGS . tively passing through surfaces 48, 50 and 52. Louvers 54and58asviewedvinFIG.2'openinacounterclock wisedirectionintocombustionchamber36whilelou vers 56 open in a clockwise direction intocombustion chamber 36. The louvers permit the passage of air in a circular swirling motion along the annular concave surfacesintothecombustionchamber36withadjacent louver sets providing opposed air currents. The air passing through the louvers is primarily intended to coolforwardsection38,althoughitalsoaidscombus tion. Concentrically located spaced'passages 60, 62, 64 and 66'are positioned in side portion 44 to further facilitate the passage of air into combustion chamber 36.Passages60arelocatedtodirectanairflowacross the exterior surface 68 of portion 42 while passages 66 are located to direct an air flow across the interior surface70ofouterportion46.Passages62and64are located to direct air currents into combustion chamber FIG. 1 illustrates a gas turbine engine 10 according to theinvention.Theengine,broadlyconsidered,com l0 prises a generally circular power section 12 and a gen erally circular speed reducing transmission 16. Trans mission 16 isseparated from power section 12 by an annular, radially extending air inlet 18 which is en closedbyanannularautomobiletypeair?lter20. 15 Power section 12 includes'an intake housing 94, and exhaust housing 138 and a shaft assembly 14 journalled withinthehousings.Shaftassembly14comprisesfour axially_aligned section's. These sections include a for wardorpowertakeoffshaftsection22,aradialout 2036andradiallytowardinnerportion42andouterpor ?ow compressorrotor24,aslingerring'orcentralshaft member 26, and a radial in?ow turbine rotor 28. Slinger ring 26 and turbine rotor 28 have adjacent ends ofcomplimentarilysteppedcon?gurationrigidlyjoined‘ togetherbywelding.Atiebolt30,axiallylocatedrela 25 tivetothefoursections,hasacenterportion30a'freely passing through a suitable central bore in compressor rotor 24, an end 30b threadably received in a blind, tapped central bore in forward shaft section 22, and an end 300 threadably received in a tapped central 30 throughboreinapartitionportion26aofslingerring 26. Adjacent ends of slinger ring 26 and compressor rotor 24, and forward shaft section 22 and compressor rotor 24, respectively, are complimentary stepped and interlockupontighteningoftiebolt30toformarigid35 shaftassembly. equal‘innumberandalignedinlocationtothimble passages 72 in forward section 38, are provided in outer portion 84. Thimble passages 72 and 86 are aligned in assembly to permit thelocation of a cylindri cal or tubular thimble burner 74 in the opposing pas Acentral,axiallyextendingfuelsupplypassage32is provided in turbine rotor 28 and slinger ring 26. Pas~ sage 32 is conical in con?guration through turbine rotor28,divergingoutwardlyasitapproachesslinger40 ring 26. Passage 32 is cylindrical in con?guration in slinger ring 26 and communicates with the exterior of shaft assembly 14 through a plurality of circumferen tialyspaced,radiallyextendingslingerports34located tion38.Apluralityofthimblepassages86(FIG.7), inslingerring26.Anopening35isprovidedinthe45 turbine end of the shaft assembly for the introduction offuelintopassage32;opening35alsopermitsintro duction of an appropriate tool to tighten or loosen tie bolt 30 which, for this purpose, is provided with a socketheadpresentedintheportionofpassage3250 sages.Eachthimbleburner74isslip?ttedwithinthe located within slinger ring 26. I An annular combustion chamber or combustor 36 is disposed between the turbine and compressor rotors in encirclingrelationtoslingerring26.Combustor36as respective passages 72 and 86 and has an annular lip 88 at one end to engage outer portion 46 of forward sec_ tion 38 and prevent the movement of the thimble burner completely through the passages. A radially _ de?nedbyaliner31whichincludesaforwardsection55 extendingtab90oneachthimbleburner74isadapted 38 and a rearward section 40. to abuttingly engage interior surface 92 of intake hous As illustrated in FIGS. 2 to 4, forward section 38 ing 94 when- annular lip 88 is engaged with forward includesanannular,axiallyextendingradiallyinner section'38toassistintheassemblyofthecombustorin portion 42 that is generally cylindrical in shape. A the housing and prevent radial movement of the thim disk-likesideportion44connectedtotheendofinner 60 bleburnersduringuseoftheengine. portion 42 extends radially outwardly and terminates at Side portion 82 of‘rearward section 40 further in anaxiallyextendingradiallyouterportion46thatis cludesapairofspacedannularconcavesurface96and generally cylindrical in shape and encircles inner por 98 intermediate inner and outer portions 78 and 84 tion 42. Side portion 44-includes three spaced annular opening toward combustion chamber 36. Struck sets of concavesurfaces48,50and52openingtowardcom 65louvers100and102areequally,spacedincircles bustion chamber 36. Sets of louvers 54, 56 and 58 are struckfromsideportion44inequallyspacedcircles tatedpassagesrespectivelycommunicatingwithsur and provide directionally orientated passages respec tion 46 respectively. For convenience, arrows have been located in FIG. 3 to show the direction of the respectiveaircurrentsthroughpassages60,62,64and 66.Theairpassingthroughthesepassagesisprimarily intendedforcombustion,althoughitalsoservesacool ingfunction with respect to forward section 38. A pluralityofcircumferentiallyspacedthimblepas sages 72 are provided in outer portion 46 to receive burner thimbles 74 (FIG. 1). Small dilution passages 76 areprovidedeachsideofthimblepassages72todirect aircurrentsperpendiculartosurface70ofouterpor tion 46, as indicated by the arrows in FIG. 4. Rearward section 40, as illustrated in FIGS. 5 to 7, includes an annular, axially extending radially inner portion78thatisgenerallycylindricalinshape.A disk-like side portion 82 connected to inner portion 78 extendsradiallyoutwardlyandterminatesatanannu lar, axially extending radially outer portion 84 that is generally cylindrical in shape and encircles a part of innerportion78. As seen in FIG. 1, in assembly, outer portion 84 of rearward section 40 is concentric with and radially inwardly spaced from outer portion 46 of forward sec aroundside'portion82andprovidedirectionallyorien faces 96 and 98. As viewed in FIG. 5, louvers 1.00 openPDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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