Patent ID: 9074485
Filing Date: 2015-07-07
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbine engine comprising: a fan rotor, a first compressor rotor and a second compressor rotor, said second compressor rotor for compressing air to a higher pressure than said first compressor rotor; a first turbine rotor, said first turbine rotor configured to drive said second compressor rotor, and a second turbine rotor, said second turbine configured to drive said first compressor rotor; a fan drive turbine positioned downstream of said second turbine rotor, said fan drive turbine for driving said fan rotor through a gear reduction; and said first compressor rotor and said second turbine rotor configured to rotate as an intermediate speed spool, and said second compressor rotor and said first turbine rotor configured to rotate together as a high speed spool, with said high speed spool and said fan drive turbine configured to rotate in the same first direction, and said intermediate speed spool configured to rotate in an opposed, second direction; a mid-turbine frame is positioned between said first and second turbine rotors; and a turning vane is positioned between said mid-turbine frame and said second turbine rotor.