| 摘要 |
Thrust nozzle cooling system for a hypersonic ducted rocket engine with a central body (12) of mushroom-shaped design, which for adjusting the cross-section of the hot gas flow duct (16) is arranged on a carrier pipe (8), fixed to the engine and enclosed at the end by the central body, so that it is axially adjustable by means of a hydraulic servomotor (18) accommodated in the said pipe. In order to guarantee an effective explosion protection and hot gas-resistant inner chamber sealing of the central body and carrier pipe for the cooling system with fuel-carrying cooling ducts (58, 66) for the outer wall sections of the central body and carrier pipe exposed to the hot gas flow, the cooling system according to the invention contains a coolant collecting chamber (62) arranged for variation of its volume adjacent to the servomotor between the rear end of the central body and end of the carrier pipe and closed off on the carrier pipe side by the hydraulic seal (32) of the servomotor. The collecting chamber arranged in the course of the coolant flow between the cooling ducts (58) of the carrier pipe outer wall and the cooling ducts (66) of the central body outside wall is adjusted to a coolant pressure level below the hydraulic pressure in the servomotor and above the hot gas pressure at the hot gas duct end of the sliding seat (10) between central body (12) and carrier pipe (8) and has a coolant connection to the sliding seat, by way of which connection the said seat is depressed by coolant from the collecting chamber. <IMAGE> |
