Patent ID: 8376692

Claim:
A turbo compressor in an axial type of construction for a gas turbine, comprising a bladed stator and a bladed rotor, wherein the bladed stator includes a compressor casing that is longitudinally split on diametrically opposed sides and at least one guide blade ring with adjustable guide blades, wherein the adjustable guide blades are pivotably mounted about a respective radial axis on an inner ring of the bladed stator, and wherein the inner ring includes at least two segments around its circumference and includes for each adjustable guide blade a bearing bush which is insertable radially into an opening defined by the inner ring from a radial inside direction with respect to the inner ring and further comprising a sealing support with a rub coating or run-in coating detachably fastened on the inner ring, wherein the sealing support secures the bearing bush from falling out of the opening.