Was compressor rotor, axial, turbine engine; dual rotors, 9 stages; high bypass fan
A single or multistage assembly designed to receive thermal energy from the combustion section and convert it to mechanical energy to drive the rotor, compressor, aircraft gas turbine engine and/or the rotor, fan, aircraft gas turbine engine through a shaft, turbine, aircraft gas turbine engine. It consists of disks, blades, hubs, and the like. It is the moving part of a turbine assembly, aircraft gas turbine engine. It has facilities for attaching to a shaft, turbine, aircraft gas turbine engine.
Classification: Parts of gas turbine aircraft engines, other than for use in civil aircraft
NSN 5835-01-205-6614
NSN 5835-01-076-8445
NSN 6620-01-182-0282
NSN 7035-00-252-7467
NSN 6150-00-496-9064
NSN 5990-01-346-5422
NSN 6150-00-931-1051
NSN 2925-01-609-8464
NSN 5998-00-171-8941
NSN 6110-01-340-6692
NSN 6240-01-484-9576
NSN 5998-01-425-8863