FIELD: engines and pumps.
SUBSTANCE: combustion chamber for turbo machine such as aircraft turbojet or turboprop comprises inner and outer circular walls composed by solids of revolution coupled by the chamber bottom circular wall. Combustion chamber inner wall is made of one ply of material its depth (e1, e2) or properties varying in lengthwise axis and in circumferential direction of said prop while outer circular wall features, in fact, invariable magnitude.
EFFECT: higher resistance to limiting temperatures without application of heat barriers and without increase in weight.
7 cl, 3 dwg
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