AIRCRAFT COMBUSTION CHAMBER CASE Russian patent published in 2011 - IPC F23R3/00 F02K9/34 F02K9/62 

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 1600°C. 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 1000°C 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