Abstract: A jet engine subassembly. The high pressure (HP) turbine includes a ball bearing assembly whose inner race is attached to the HP turbine shaft. The outer race takes radial loads through radially-extending tie rods which pass through the HP turbine nozzle vanes and are connected to the combustor's outer casing. The outer race takes axial loads through a support cone which is attached to the combustor diffurser's radially inner duct through an intermediate forward segment of the combustor inner casing. This eliminates the need for a heavy turbine frame. The ball bearing is the thrust bearing, and does not experience thermal axial growth. This allows the use of unshrouded sloped HP turbine blades.

Abstract: A bypass turbofan jet engine subassembly. A row of structural fan stators and a row of structural compressor guide vanes have their outer ends attached to the engine outer duct. The structural stator inner ends are attached by an inner support cone to the outer race of the fan rolling element bearing and the structural guide vane inner ends are attached by another inner support cone to the outer race of the compressor rolling element bearing. The fan and compressor outer races are interconnected by a tie bar. The subassembly eliminates the engine fan and compressor frames.