PRESSURISATION SYSTEM OF REAR LUBRICATION CHAMBER OF JET TURBINE ENGINE Russian patent published in 2011 - IPC F02C7/06 F01D25/16 F01D25/18 

FIELD: engines and pumps.

SUBSTANCE: jet turbine engine includes shaft brought into rotation with low pressure turbine (12). Rear part of shaft is supported on rolling bearing (20) located inside lubrication chamber (24) in which oil mist is constantly kept. Lubrication chamber (24) enveloping the rolling bearing includes inner rotating part connected to the shaft and outer fixed part, which are separated from each other by means of the first annular tight seal (40). Lubrication chamber (24) includes recuperative chamber (26) which is under positive pressure, located outside the above tight seal and which consists in its turn of two parts: fixed part and movable part, which are separated from each other by means of the first tight seal. Low pressure turbine (12) is located coaxially above shaft (14) and outside it. Rolling bearing is located between shaft and turbine. Recuperative chamber (26) is the only one and includes the second tight seal (48) located radially and outside the first tight seal. The second seal (48) is located at turbine rotor outlet.

EFFECT: simpler design owing only to one recuperative chamber, and higher efficiency owing to preventing any oil leaks in the direction of inner part of turbine rotor.

3 cl, 1 dwg