Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor

A Compressor (10), especially for a gas turbine, comprises a rotor (15) rotating about an axis (17) and a housing (11) coaxially surrounding said rotor (15), thereby defining a flow channel (14) between rotor (15) and housing (11) for a fluid to be compressed, whereby alternating rows of vanes (13) and blades (16) are arranged within the flow channel (14), the vanes (13) being mounted in the inner wall of the housing (11), and the blades (16) being mounted in the outer wall of the rotor (15). A fast exchangeability and/or repair in combination with an ease of reconditioning the machine, are achieved by providing intermediate rings (18) in the inner wall of the housing (11) between neighbouring rows of vanes (13) such that the outer wall of the flow channel (14) is essentially formed by said vanes (13) and intermediate rings (18).