blade row 48 is housed within a nacelle 50 of the engine 10 supported about the stationary casing 14 by a plurality of radially extending and circumferentially spaced fan struts 52 an engine cowling 54 which encloses the core engine 20 and the low pressure turbine 22 is disposed within and extends coaxially with a rear portion of the nacelle 50 so as to define therewith a fan discharge nozzle 56 most of the thrust produced by the engine 10 is generated by air flow caused by rotation of the fan blade row 48 of the forward fan 16 which air flow passes over and through the nacelle 50 the low pressure turbine 22 includes an annular rear turbine frame 62 which supports a conventional bearing 64 which in turn rotatably supports an aft end of the low pressure shaft 32 the rear turbine frame 62 includes a radially outer first structural ring 66 disposed coaxially about the centerline a and a radially inner second structural ring 68 a plurality of circumferentially spaced apart struts 70 extend radially between the first and second structural rings 66 and 68 and are fixedly joined thereto each one of the struts 70 is conventionally surrounded by a conventional.