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4,000,609 56 into combustion chamber 96 in a clockwise direction while louvers 102 open into chamber 36 in a counter clockwise direction. The louvers direct air along the respective annular concave surfaces in a swirling mo tion into combustion chamber 36 with louvers 100 providing air in one rotational direction and louver 102 providing air in the opposite rotational direction. The airpassingthroughthelouversisprimarilyintendedto cool rearward section 40. Preferably, as viewed from one end ofcombustion chamber 36,1ouvers 100 and 54 should swirl air in opposite directions as should louvers 102 and 56 to create a turbulence within combustion chamber 36. Spaced passages 104, 106 and 108 are positioned in circles in side portion 82 of rearward section 40 to permit the passage of air into combustion chamber 36. Passages 104 are located to direct air currents across the exterior surface 80 of inner portion 78 while pas sages 106 are located to direct air currents radially into chamber 36 toward surface 80 of inner portion 78. Passages 108 are located to direct air currents across angular surface 109 of side portion 82 into chamber 36 and radially toward outer portion 84. vanes 121 projecting in cantilever fashion from the base sectin of portion 119, and a central hollow hub portion 132 encircling central shaft member 26 and extending axially inwardly from diffuser section 119. Bolts 120 are secured by nuts 124 located in air inlet 18 and further act to retain combustor forward section 38 at a given distance from diffuser plate 118 to form an air space therebetween. A plurality of screws 126 are located intermediate concave surface 48 and inner portion 42 in holes 128 in forward section 38 to further secure combustor section 38 to plate 118. Diffuserplate118,togetherwithhousingendsurface 112,providesapluralityofradiallyextendingpassages 130 de?ned between adjacent vanes 121; passages 130 directthe?ow ofoutletairfromcompressorrotor24. A labyrinthianseal134isformedonslingcrring26and terminates at a position adjacent a hub portion 132 to prevent the passage of air from compressor rotor 24 between diffuser plate 118 and shaft assembly 14. Dif fuser plate 118 ispreferably formed as an aluminum die casting. The radially inner periphery of combustor forward section38,asde?nedbytheinturnedaxiallyinneredge Thepurposeofthepassages60,62,64,66,104,106' ofportion42,seatsonhubportion132andde?nesan and108andthelouvers54,56,58,100and102is25 annularairspace‘betweenportion42andhubportion twofold. They are ?rst intended» to direct air coming into the combustion chamber 36 across forward and rearward sections 38 and 40 to cool these sections and, second, they are intended to create a turbulence within the combustion chamber 36 to provide proper fuel-air mixing and favorable combustion. The shape of sec tions 38 and 40 and the location of the louvers and passages are signi?cant to the operation of an ef?cient engineproducingthedesiredhorsepowerinthemini mum space. ' 35includesaradiallyextendingportion139havingan As seen in FIG. 7 a plurality of dilution passages 110 are located intermediate thimble passages 86 in outer portion 84 to direct air currents perpendicular to outer portion 84. In assembly, dilution passages 110 will be located intermediate to dilution passages 76 in outer 40 these blades. Housing 138 further de?nes a conical portion 46 of forward section 38. The dilution passages 76 and 110 are intended to direct air currents into and cool the exhaust gases exiting the combustion chamber between outer portions 46 and 84. exhaust passage 144 de?ned by inner and outer conical housing portions 146 and 148; portions 146 and 148 are interconnected by a plurality of circumferentially spaced Spreaders or spokes 150. Exhaust passage 144 Combustorsections38and40,andthimbles74,are45 communicateswiththeoutletofturbinerotor28and formed as sheet metal stampings. Intake housing 94 is cup-shaped and has an annular axially extending portion 93 de?ning a cylindrical sur face 92 that is concentric with the shaft assembly axis, and a radially extending portion 111 having an annular end surface 112, an axially extending cylindrical sur face 114 concentric with the axis of shaft assembly 14, and a curvilinear annular surface 115 interconnecting surfaces 112 and 114. Surface 115 closely conforms to the outer curvilinear con?guration of the blades of 55 for seating coaction with the outer periphery of com compressor rotor 24 to provide a shroud for these blades.An annularcompressorinletpassage 116,com municatingwithairinlet18,isde?nedbetweensurface 114 and the adjacent exterior cylindrical surface of shaftassembly14;passage116opensintotheblading60 housingportion152bybolts(notshown).Nozzleplate of compressor rotor 24. Housing 94 is preferably formed as an aluminum die casting. 156 includes an outer, annular nozzle portion 155 de ?ning a plurality of circumferentially spaced radially extending nozzle vanes 157 projecting in cantilever fashion from the base section of portion 155, and a An annular compressor diffuser plate 118 issecured to intake housing 94 by a number of bolts 120 which projectthroughopenings122incombustorforward65 centralhollowhubportion159encirclingcentralshaft section 38. Diffuser plate 1 18 includes an outer annular member 26 and extending axially inwardly from nozzle diffuser portion 119 de?ning a plurality of circumfer portion 155. The axially inner ends of hub portions 132 entialyspaced,generallyradialyextendingdiffuser and159areaxiallyspacedtoexposeradialports34 132. The air space between forward section 38 and diffuser plate 118 communicates with the passages and louvers in forward section 38 and a plurality of radially extending passages 136 which open into labyrinthian seal 134. Air ?ow through passages 136 increases the effectiveness of seal 134. Exhaust housing 138 is connected to the large open end of intake housing 94 by means of a known screw actuated U-shaped clamp 140. Exhaust housing 138 annular axially inwardly projecting portion 142 de?n ing an annular curvilinear inner surface 142a which closely conforms to the outer curvilinear con?guration of the blades of turbine rotor 28 to provide a shroud for the atmosphere to direct exhaust gases away from the engine. Inner portion 146 is annular in con?guration and terminates proximate shaft 14. Exhaust housing 138 ispreferably formed as a ductile iron casting. Radially extending portion 139 of exhaust housing 138 further includes an annular disk shaped portion 152extendingradiallyoutwardlyfromportion142and terminating at its radially outer edge in an inturned edge portion 154. Portion 154 de?nes an annular seat bustorforwardsection38,asde?nedbythefreeedge ofouterportion46. A nozzleplate156,somewhatsimilarindesignand relative location to diffuser plate 118, is secured toPDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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