VARIATOR GEAR RATIO BETWEEN TURBINE SHAFT AND AIRCRAFT ENGINE STARTER-GENERATOR Russian patent published in 2015 - IPC F02C7/275 F02C7/32 

FIELD: engines and pumps.

SUBSTANCE: proposed device comprises first and second gears rigidly fitted in starter-generator shaft, first and second mid gears, clutch and clutch drive. Said first and second mid gears are fitted on turbine shaft to engage with first and second fixed gears, respectively, to allow different gear ratio. Said clutch is fitted in between mid gears and engaged mechanically with turbine shaft. Said clutch can displace on turbine shaft between the position whereat it engages with first mid gear and that whereat it engages with second mid gear. Clutch drive displaces the clutch from one position to another when the sum of torques between turbine shaft and starter-generator shaft changes its sign. Another invention of the set relates to aircraft turbine incorporating aforesaid gear ratio variator.

EFFECT: higher reliability, decreased weight.

9 cl, 7 dwg