| 摘要 |
An aircraft (10) having turboprop propulsion has a plurality of gas turbine engines (11), each with a two stage reduction gearbox (30, 41) with the engine output shaft (17, 17A) inline with the propeller drive output shaft (19, 51) to drive a propeller (12). The input gear reduction stage (20) and output gear reduction stage (21) share a plurality of layshafts (22, 38). The layshaft gears are arranged to avoid any net thrust loading of the layshaft. The engine output gear (25, 36) and gearbox output gear (28, 49) and propeller all have colinear rotational axes. |
