Patent ID: 8075253

Claim:
A gas turbine compressor comprises a first fixed stage ( 5 ) comprising a plurality of first adjustable vanes ( 11 ) and further fixed stage ( 7 ), which comprises an inner ring ( 12 ) extending about a first axis (A 1 ); an outer ring ( 13 ) arranged about the inner ring ( 12 ) and coaxial with the inner ring ( 12 ); and a plurality of second adjustable vanes ( 14 ), each of which extends along a second axis (A 2 ) in an essentially radial direction with respect to the first axis (A 1 ) and between the inner ring ( 12 ) and the outer ring ( 13 ); wherein each of the second vanes ( 14 ) is adjustable about the corresponding second axis (A 2 ) independently from the first adjustable vanes ( 11 ).