| 摘要 |
<p>A single shaft gas turbine engine of the type having a shaft assembly including, in axial alignment, a radial turbine element, a central slinger ring element, a radial compressor element, and a geared power takeoff element. The elements of the shaft assembly are interconnected by a tie bolt. An annular combustor liner defines a combustion chamber that encircles the central slinger ring. The shaft assembly is journaled by two bearings which are respectively located outboard of the turbine and on the geared power takeoff element. Each bearing is carried by a tubular support. Each tubular support has a free end carrying the respective bearing and another end secured to the bearing. The ends are spaced and interconnected by circumferentially spaced ribs to provide a flexible support for the prospective bearing. The gear on the power takeoff element drives a larger gear to withdraw power from the engine. A coil spring has one end seated on the housing and another end in contact with the free end of the tubular support carrying the bearing on the geared power takeoff element. The coil spring urges the geared power takeoff element in a radial direction that is opposite to the direction of the operational force exerted by the larger gear on the power takeoff gear. The coil spring is preloaded to exert a force equal to one half of the maximum force exertable by the larger gear on the power takeoff gear and has a spring rate that is relatively small when compared to the spring rate of the tubular support.</p> |
