Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines

An aircraft gas turbine engine assembly comprising:

• a high pressure rotor 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 section located aft of said high pressure rotor and having a low pressure turbine flowpath, and tandem non-interdigitated counter rotating forward and aft low pressure turbines,
• said aft low pressure turbine including first low pressure turbine blade rows disposed across said low pressure turbine flowpath,
• said forward low pressure turbine including second low pressure turbine blade rows disposed across said low pressure turbine flowpath,
• said first low pressure turbine blade rows disposed downstream of said second low pressure turbine blade rows along said low pressure turbine flowpath, and
• rows of non-rotatable low pressure vanes disposed across said low pressure turbine flow path between first adjacent pairs of said first low pressure turbine blade rows and between second adjacent pairs of said second low pressure turbine blade rows.