| 摘要 |
<p>In the proposed method, each landing gear wheel is rotated with the aid of one of the radial- or axial-type air turbines which are mounted on said wheel, rotate in opposite directions and to which compressed air from the main engines or from an auxiliary power-generating plant of the aircraft is fed. The wheels are spun by one of the turbines before landing or during forwards movement on the ground, while the other turbine is used for braking after touchdown, and also for reversing and for turns when manoeuvring. Air is also used for bleeding and cooling a wheel brake. Non-communicating air collectors of the turbines are connected by a telescopic pipe, which is fastened on a landing gear leg, via control valves to on-board compressed-air sources. Brake stator discs have through-channel sectors and are nozzle diaphragms, while rotor discs have through-channels arranged uniformly around the circumference and are working wheels of the axial turbine. Nozzle apparatuses of the radial turbine are mounted on the stator, while the working wheel is mounted on the internal rim of the landing gear wheel. The nozzle apparatuses are connected by sector air ducts to the corresponding air collectors.</p> |
