Patent ID: 8550774

Claim:
A turbine arrangement, comprising: a rotor, comprising: a plurality of turbine blades extending in a radial direction through a flow path towards a stator and each blade includes a shroud located at a tip of the blade; and the stator surrounding the rotor forming the flow path for hot and pressurised combustion gases between the rotor and the stator, the stator comprising: a wall section, wherein the rotor defines the radial direction and a circumferential direction, wherein a plurality of shrouds move along the wall section when the rotor is turning, wherein a supersonic nozzle is located in the wall section and is connected to a cooling fluid provider and located such as to provide a supersonic cooling fluid flow towards the shroud, and wherein the supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow includes a flow component parallel to a moving direction of the shroud.