Ducted prop engine

A gas turbine engine for an aircraft, said engine having an axis, a front end, and a rear end, said engine comprising, in series flow relationship, axial flow compressor means, combustor means, and turbine means, including inner and outer concentric core stream wall means spaced apart defining a core stream annular gas flow path therebetween having an inlet and including the flow path of said axial flow compressor means;

• bypass duct means surrounding said compressor means, including inner and outer concentric bypass duct wall means defining an annular bypass stream flow path therebetween surrounding said core stream flow path;
• a disk disposed entirely between said core stream gas flow path and said bypass stream flow path downstream of said core stream flow path inlet and rotatable about said engine axis;
• a plurality of circumferentially disposed airfoils secured to said disk and extending across said bypass stream flow path;
• stationary engine support structure disposed radially outwardly of said core stream gas flow path and extending from said outer core stream wall means to said outer bypass duct wall means;
• first bearing support means disposed radially inwardly of said core stream gas flow path;
• first bearing means disposed radially inwardly of said core stream gas flow path and mounted on said first bearing support means, said first bearing means including a first rotatable race;
• second bearing means axially spaced from said irst bearing means and mounted on said engine support tructure radially outwardly of the core stream flow ath and including a second rotatable race;
• disk support means extending etween and attached to said disk and second rotatable ace and being reIatively stiff in the radial irection for transmitting aircraft maneuver loads and entrifugal loads from said disk into said engine upport structure;
• and
• drive means connecting said turbine means to said disk for rotating said disk including torque transmitting means secured to said first rotatable race, said torque transmitting means including airfoil shaped strut means rotatable about the engine axis and extending across the flow path of said axial flow compressor means and connected to said disk for rotating said disk and airfoils about the engine axis and for transmitting maneuver loads from said disk into said first bearing support means, wherein the axial location of said disk is such that a major portion of the maneuver loads therefrom are transmitted into said engine support structure, and a minor portion of the maneuver loads therefrom are transmitted into said first bearing support means.