REDUCTION GEAR FOR AIR PROPELLER OF TURBOPROPELLER AIRCRAFT ENGINE Russian patent published in 2006 - IPC F16H1/46 F16H55/08 

FIELD: aircraft engine engineering.

SUBSTANCE: reduction gear comprises kinematically closed gear transmission made of two coaxial stages. The first stage is connected with the shaft of the turbine and made of a planet mechanism. The second stage is made of a gear mechanism connected with the air fan. Each of the mechanisms comprises two central wheels (solar wheel and epicyclic wheel) and wheels-satellites which are in external and internal engagement with each other. All gear wheels are evolvent, strait-tooth cylindrical wheels with asymmetrically shaped teeth having the same asymmetry coefficient that is determined from the equation K = d_unw/d_w, where d_unw is the diameter of the main circumference of the not working tooth section and d_w is the diameter of the main circumference of the working tooth section, and ranges from 1.05 to 1.15. The angle of engagement of the teeth of the gear wheels-satellites with central wheels in transmitting torque for outer engagement of teeth ranges from 30° to 35°, and for the inner engagement from 30° to 40°.

EFFECT: improved structure and prolonged service life.

2 dwg