Patent ID: 8092148

Claim:
A gas turbine comprising: at least one compressor; at least one combustion chamber; and at least one turbine, at least one of the at least one compressor and the least one turbine comprising a rotor and a stationary housing, the rotor including rotor blades, the stationary housing including a run-in coating and at least one channel, the stationary housing surrounding the rotor blades such that there is a gap between radially outer ends of the rotor blades and the stationary housing, the stationary housing further including a peripheral ring segment forming a substrate for the run-in coating; wherein the at least one channel is configured to apply a pressure prevailing on a high-pressure side of the rotor blades to a low-pressure side of the rotor blades in an area of the gap to prevent a flow through the gap, at least a portion of the at least one channel extending within the peripheral ring, the at least one channel opening on the low-pressure side into the gap in a first area of the run-in coating at a low-pressure side opening, and opening on the high-pressure side in a second area of the peripheral ring segment outside of the gap at a high-pressure side opening.