ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE

摘要

A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor.

主权项

1. A gas turbine engine comprising:
a first turbine positioned upstream of a second intermediate turbine and a third turbine being positioned downstream of the first and second turbines; and a fan and three compressors, with an upstream one of said compressors being connected to rotate with said fan rotor, and said third turbine for driving said upstream compressor and said fan both through a gear reduction, and a second intermediate compressor for being driven by said second intermediate turbine rotor, and a third compressor downstream of said first and second compressors and for being driven by said first turbine rotor.