AIRCRAFT COMBUSTION CHAMBER CASE

摘要

FIELD: engines and pumps. ^ SUBSTANCE: proposed combustion chamber multilayer case comprises internal pressure load bearing metal shell, layer of silicon dioxide fabric impregnated with high-temperature glue for it to be guide to metal shell inner surface whereon sequentially applied are ceramic composite material reinforced by carbon fibers, antirust binder layer and high-temperature ceramic composite material layer to stay in contact with gas produced in fuel combustion that feature temperature approximating to 1600C. Silicon dioxide fabric features heat conductivity of about 0.2 W/mC. Linear expansion factor and modulus allow thermal and mechanical compatibility of metal shell and said ceramic layers at operating temperatures of about 1000C and make about 20 106, 1/C and 20 GPa, respectively. Thickness of every layer is selected so that temperature load on metal shell is reduced to level not requiring additional external air cooling. ^ EFFECT: improved operating performances and higher efficiency. ^ 2 cl, 1 dwg