| 摘要 |
FIELD: weapons and ammunition.SUBSTANCE: cruise missile engine combustion chamber is composed of sandwiched article and comprises shell to sustain inner pressure load and thermal ceramic composite protection ply to contact the gases formed at fuel combustion. Said thermal ceramic composite protection ply features linear expansion factor and elasticity modulus that allow thermal and mechanical compatibility with said shell. Besides, said thickness is selected to rule out the shell additional external cooling. Said shell is made of ceramic composite reinforced with carbon fibres that feature linear expansion factor of not over 5.2x101/°C, modulus of elasticity making at least 13·10MPa, and breaking strength not lower than 90 MPa. Said thermal ceramic composite protection ply in contact with gases with working temperature not over 2000°C features linear expansion factor of not over 5.5·101/°C.EFFECT: decreased weight and overall dimensions, simplified design, higher reliability.2 cl, 2 dwg |
