Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans

A gas turbine engine turbine assembly comprising:

• a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft and rotatable about an engine centerline,
• a low pressure turbine having a low pressure turbine flowpath and located aft of said high pressure spool,
• said low pressure turbine having counter rotatable low pressure inner and outer shaft turbines,
• said low pressure turbine having low pressure inner and outer shafts respectively which are at least in part rotatably disposed coaxial with and radially inwardly of said high pressure spool,
• said low pressure inner shaft turbine including first low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a forward fan blade row by said low pressure inner shaft,
• said low pressure outer shaft turbine including second low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a aft fan blade row by said low pressure outer shaft,
• a single direction of rotation booster having at least a rotatable first row of booster blades drivenly connected to said low pressure outer shaft and axially located aft and downstream of said aft fan blade row, and
• at least one row of low pressure variable vanes disposed across said low pressure turbine flowpath between said low pressure inner and outer shaft turbines.