TURBINE FOR LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: rocket manufacturing. SUBSTANCE: proposed turbine has housing with working chamber, working medium supply channel communicating with chamber, cooling space and cooling medium supply channel communicating with cooling space. Special arrangement for feeding cooling medium to turbine wheel is located in end face part of working chamber at side of working medium supply channel. This arrangement is made in form of ring chamber communicating with ring slot in housing and with cooling medium supply channel. Turbine has also bushing made of material whose thermal conductivity exceeds that of housing material. Bushing is installed coaxially relative to turbine wheel and is secured on housing to form cooling space on its outer surface. Length of bushing exceeds that of turbine wheel. Bushing is installed to project beyond wheel to side of working medium supply channel. Outer surfaces of ring chamber and ring slot of arrangement for feeding cooling medium to turbine wheel are formed by inner surface of projecting part of bushing. Turbine wheel installed in housing is provided with shroud. EFFECT: prevention of ignition in turbine inner space at operation on oxidizing gas. 4 cl, 3 dwg