Turbojet with contrarotating wheels

Claim 1

A turbojet comprising: turbine means including first and second turbine wheels which rotate in opposite directions during operation of the turbojet, multistage compressor means including an inner and an outer rotor driven by said first and second turbine wheels, respectively, said inner rotor including a first bladed wheel and a second bladed wheel, both connected to a common inner shaft, said outer rotor including a first bladed wheel and a second bladed wheel arranged alternately with said first and second bladed wheels of the inner rotor and arranged in axial succession upstream from said turbine means for defining an axial gas flow channel extending towards said turbine means, said outer rotor comprising: an outer shaft rotatably arranged around said inner shaft, and coupled to said first turbine wheel, ring means arranged around the second blade wheel of said inner rotor and defining an outer boundary of said gas flow channel at said second bladed wheel of the inner rotor, first connection means extending radially inwardly from said ring means towards said outer shaft, on the downstream side of said second bladed wheel of the inner rotor, said first connecting means comprising spokes crossing said gas flow channel, said second bladed wheel of the outer rotor being connected to said first connecting means between said spokes and said outer shaft, second connecting means between said ring means and said first bladed wheel of the outer rotor, said second connecting means extending radially inwardly on the upstream side of said second blade wheel of the inner rotor, and comprising spokes crossing said gas flow channel, and a conical flange extension supported rotatably on said inner shaft, said first stage wheel of the outer rotor being supported on said conical flange.