| 摘要 |
An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber (10) for liquid rocket propulsion systems is disclosed having internal trapezoidal-shaped cooling channels (12). The thrust chamber (10) consists of an inner wall (11), which is fully integrated to an outer wall (14) via radial coupling webs (13). Segmented annular voids (15) between the inner wall (11), outer wall (14) and adjoining radial webs (13) form the cooling channels (12). The manufacturing method enables any general tubular shell geometry ranging from simple cylindrical heat exchanger tubes to complex converging-diverging, Delaval-type nozzle structures with an annular array of internal cooling channels. The manufacturing method allows for transitioning the tubular shell structure from a two-dimensional circular geometry to a three-dimensional rectangular geometry. The method offers the flexibility of producing internal cooling channels (12) of either constant or continuously variable cross-sectional area, in addition to orienting the cooling channels (12) either axially, helically or sinusoidally (e.g., undulating) with respect to the longitudinal axis of the tubular shell structure. |
