CPC F01D 5/06 (2013.01) [F05D 2220/32 (2013.01)] | 11 Claims |
1. A gas turbine engine defining an axial direction and comprising:
a turbine section comprising a turbine having a plurality of first speed turbine rotor blades;
a compressor section comprising a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades, the plurality of first speed compressor rotor blades alternatingly spaced with the plurality of second speed compressor rotor blades along the axial direction;
a fan section comprising a fan; and
a first spool rotatable by the plurality of first speed turbine rotor blades and coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades, coupled to the plurality of second speed compressor rotor blades for driving the plurality of second speed compressor rotor blades, and coupled to the fan for driving the fan,
wherein the turbine further comprises a plurality of second speed turbine rotor blades,
wherein the plurality of first speed turbine rotor blades are alternatingly spaced with the plurality of second speed turbine rotor blades along the axial direction,
wherein the gas turbine engine further comprises a second spool coupled to and rotatable with the plurality of second speed turbine rotor blades and the fan for driving the fan,
wherein the plurality of second speed compressor rotor blades are further coupled to the fan for driving the fan.
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