Patent ID: 6684626
Filing Date: 2004-02-03
Classification: F01D,F02C,F02K

Abstract:
A gas turbine engine turbine assembly comprising:a low pressure turbine having a low pressure turbine flowpath, counter rotatable low pressure inner and outer shaft rotors having low pressure inner and outer shafts respectively, said low pressure inner shaft rotors including first low pressure turbine blade rows disposed across said low pressure turbine flowpath, said low pressure outer shaft rotor including second low pressure turbine blade rows disposed across said low pressure turbine flowpath, said first low pressure turbine blade rows including at least one first interdigitated turbine blade row disposed between at least one second adjacent pair of said second low pressure turbine blade rows, said second low pressure turbine blade rows including at least one second interdigitated turbine blade row disposed between at least one first adjacent pair of said first low pressure turbine blade rows, and at least one row of non-rotatable low pressure vanes disposed across said low pressure turbine flowpath between a non-interdigitated adjacent pair of said first and second low pressure turbine blade rows not having an interdigitated turbine blade row therebetween.