FRONT SUPPORT OF LOW-PRESSURE TURBINE OF TWO-SHAFT GAS-TURBINE ENGINE Russian patent published in 2007 - IPC F02C7/06 

FIELD: aircraft industry.

SUBSTANCE: invention relates to gas-turbine engines of aircraft and ground application, namely, to supports for rotors of turbomachines rotating at high speed, and also for lubrication and cooling of bearings and supports proper, and it can be used in supports exposed to high stresses. Proposed support contains roller bearing, flanged inner race secured on shaft of low-pressure rotor, outer race being fitted in unit of central conical train on stator. Space formed on inner diameter of low-pressure turbine shaft is connected by two rows of oil feed holes with ring grooves on outer diameter of low-pressure turbine shaft which, in its turn, is connected with through oil-feed holes in inner race of bearing at angle of 40-50° to longitudinal axis.

EFFECT: provision of serviceability of front support of low-pressure turbine and optimum delivery of oil for lubricating and cooling of bearing.

1 dwg