| 摘要 |
<p>A counter-rotating rotary-piston engine (10) has an output shaft (12) with a cylindrical inner cavity rotatably mounted on a single support spindle (14) in the frame of an aircraft. The output shaft (12) extends substantially through the length of the engine block (24), which is suitably journaled on the shaft (12) or the spindle (14) to permit its counter-rotation. Internal combustion power is transmitted to the output shaft (12) by means of an inner rotary piston (38) fixed to the shaft which cooperates in conventional manner with an outer working chamber (36) in the engine block (24), thereby producing concurrent rotation of the shaft (12) and counter-rotation of the engine block (24). Dual propellers (20, 32) mounted on the shaft (12) and on the block (24) improve thrust performance, balance the torques and moments of inertia of the two counter-rotating masses, and virtually eliminate any resultant torque to the aircraft.</p> |
