Patent ID: 8333553

Claim:
A compressor of a gas turbine, the compressor comprising: at least one rotor-side blade ring; and at least one stator-side guide vane ring, the guide vane ring being formed by several guide vane segments, each guide vane segment being formed by several individual blades; each individual blade including an exterior shrouding band portion located radially on the exterior end of the individual blade, an interior shrouding band portion located radially on the interior end of the individual blade and a turbine blade arranged between the interior shrouding band portion and the exterior shrouding band portion; wherein within each guide vane segment of the at least one guide vane ring, adjacent individual blades are permanently connected with each other at opposite surfaces of their respective exterior band portions located radially on the exterior while being unconnected with each other at opposite surfaces of their respective interior band portions located radially on the interior.