| 摘要 |
<p>PURPOSE: To increase reliability on operation by providing a motor which receives the electric power from a power generator connected to the rotary shaft of a rotating member and operates a device controlling the pitch of the propeller blades of a gas turbine engine, and outputting the power via a gear device. CONSTITUTION: An engine 12 fitted near the tail end of an aircraft 10 has a gas turbine 18 at its front stage, and a front propeller 14F and a rear propeller 14R constituting a propeller stage are rotatively driven in opposite directions by the high-energy gas flow generated here. The propellers 14F, 14R have variable-pitch moving blades 24, 26. A synchronous generator 40 is arranged near the compressor stage in the gas turbine 18, and its electric power is fed to motors 42, 44 arranged in an oil sump 39 behind the moving blades 24, 26 via a rectifier/inverter stage 50. The motors 42, 44 are mechanically connected to gear boxes 46, 48, and the output shaft sides of the gear boxes 46, 48 are connected to a mechanism controlling the pitches of the propellers 14F, 14R.</p> |
