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in,Fl'GURE6(scealsoFIGURE l)thematingconical surfaces ofvparts 68 and 69 and also the mating conical surfaces 112e and 126g adjustably engage each other in íiuidsealingrelation. Theangleoftheconicalsurface 112a is determined so as to coincide approximately with the angle of the resultant force S of the axial forces A> and the radial forces R. The axial forces A are deter mined primarily by the pressure of the motive gases ap plied against the effective area of the upstream or high pressuresideofinnerhousing23,aslforexampleagainstlO nularpassage,andmeanscarriedbysaidouterhousing engaging axially opposite ends of said inner housing to Supportv the same including a resilient battle extending around said axis and in the direction of flow of said motive gases from adjacent one axial end of said outer thebulkhead32,bañie40,andnozzles38and45a. The radialforceR isdeterminedprimarilybythermallyin duced expansion of the inner housing 23 relative to the outerhousing10duringoperationoftheengine. Thus theplaneofengagementbetweensurfaces112mand126er15 housingtosaidinnerhousingandterminatinginacon is substantially parallel to the direction of movement of innerhousing23-urgedbytheforcesA andR. Iclaim: 1. In a gas turbine engine having a pair of coaxial ical end yieldingly engaging a mating conicalportion of said inner housing to urge the same in said direction, said bafllebeing `spaced radially from the outer wall of said outer housing to comprise therewith anannular inlet air rotors, an outer housing, an inner housing within said 20 ductdischargingintosaidchambers.V outer housing and containing said rotors, journal means Ycarried by said outer housing and rotatably supporting said rotors, annular gas passage means supported by said 6. The combination according to claim 5 comprising in addition an axial Íiow air compressor coaxial with said annular passage and discharging radially into an annu larly arranged diffuser deiined by interconnected inner inner housing coaxially with said rotors for conducting motive gases thereto, bame means subject to the axial 25 and outer walls, said outer wall being a continuation of pressure of said motive gases and carried by said annular gas passage means to close the area radially inwardly thereof at a location between said rotors, said inner hous ing being thereby urged axially in the downstream direc tion>by said pressure, a plurality of domes in said outer 30 housing at locations spaced around the axis of said gas passage means and rotors, a corresponding plurality of platforms carried by said inner housing, each platform extending transversely to a radius from said axis and havinggaspassagesectorsopeningradiallytherethrough, 35 nular passage, said inner housing having a separate re eachplatformalsobeingspacedradiallyinwardlyfromf ,generatorsupportingplatformatthebaseofeachcham ber, a pair of conical supports coaxial with said annular passage and carried by said outer housing at the axially opposite ends nespectively` of saidinner housing, said the outer surface of one of each of said domes to provide a regenerator chamber, said»inner and outer housing slid ably engaging each other ataxially opposite ends of said innerhousingtosupportthelatter,theslidingengagement40 conicalsupportsslidablyengagingmatingconicalpor between said housings at the downstream end 'ofVthe inner housing being at mating conical surfaces of said housings coaxial with said rotors and enlarging in said downstream direction. 2. In a gas turbine engine having a pair of coaxial ro tors, an outer housing, an inner housing within said outer housing and containing said rotors, a plurality of domes in said outer housing at locations spaced around the axis of said rotors, a corresponding plurality of platforms can ried by said inner housing, each platform extending trans versely to a radius from said axis and having gas passage sectors opening radially therethrough, each platform also being spaced radially inwardly from the outer surface of tions of said inner housing in supporting relation, and at least one of said conical supports being resiliently urged yieldingly against its mating conical portion to accommo date thermally induced dimensional changes between said inner and outer housings. 8. In a gas turbine engine, an outer housing, an inner housing supported within said outer housing and defining in part an annular passage for motive gases, said outer housing including an end Wall spaced axially from said inner housing, bearing supporting means extending around the axis of said annular passage and axially into the space bounded by said annular passage, a rotor shaft journalled in said supporting means and extending at one end into said space along said axis, said supporting means enlarg~ one of each of said domes tovprovide a regenerator cham ber, and means carried by said outer housing engaging 55 ing radially in the axial direction toward Vsaid end Wall axially opposite ends of said inner housing to supportthe same, the last named means including a resilient bañle extending around said axis and in the axial direction from adjacent one axial end of said outer housing to the juxta posedaxialendofsaidinnerhousingandyieldinglyen 60 gaging the latter to urge the same in said direction. and terminating in sliding engagement with said wall at locations remote from said axis, said supporting means also having a portion rigidly secured to said wall at loca tions adjacent the periphery of said shaft. 9.Inagasturbineengine,anouterhousing,aninner housing Supported within said outer housing and deñning in part an annular passage for motive gases, said outer housing including an end wall spaced, axially from said inner housing, annular bearing supporting means coaxial 3. The combination according to claim 2 wherein said barile and inner housing engage each other in sliding rela tion at a conical surface to accommodate thermally in duceddimensionalchangesbetweensaidinnerandouter l withsaidannularpassageandextendingaxiallyintothe housings. 4. In a gas turbine engine, an outer housing, an inner housing within said outer housing and defining in part an annular passage for motive gases, a plurality of regenerator chambers in the outer portions of said outer housing and spaced circumferentially around the axis of said annular passage, said inner housing having a separate regenerator supporting platform at the base of each chamber, _and means carried by said outer housing engaging axially op posite ends of said inner housing to support the same in space bounded by said annular passage, a rotor shaft jour nalledV in saidsupporting means and extending at one end into said space along said axis, the journal support for said shaft including bearing means within said space _and second bearing means adjacent saidYend wall, said supporting means enlarging radially in the axial direction toward said end Wall and terminating in sliding engage ment with said wall at locations remote from said axis, said supporting meansv also having a portion rigidly se ,cured to said wall at iocationsadjacent the periphery of ät. cluding a resilient conical support coaxial with said axis and yieldingly engaging a mating conical portion oí` said inner housing to urge said inner housing axially in one axial direction. ' 5.’In a gas turbine engine, an outer housing, an inner housing within said outer housing and deñning in part an annular passage for motive gases, a plurality‘of regener ator chambers in the outer portions of said outer housing and spaced circumferentially aroundthe axis of said an the outer wall of said outer housing, said inner wall being spaced axially inwardly of said outer Wall and being con nected to the axial outer ‘end of said baffle, and said diffuser discharging into said inlet air duct. 7. In a gas turbine engine, an outer housing, an inner housing within said outer housing and deñning in part an annular passage for motive gases, a plurality of regenera tor chambers in the outer portions of said outer housing and spaced circumferentialiy around the axis of said an- ,PDF Image | GAS TURBINE ENGINE HOUSING
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