Patent ID: 7011492

Claim:
A turbomachine turbine vane comprising a multiply-perforated liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air admission opening for feeding the inside of the liner with cooling air and an air exhaust opening for exhausting a fraction of the cooling air from the vane, the liner being secured to the vane at a first end and being free at a second end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane, an annular gap between said free end of the liner and the inside edge of the vane defining a leakage zone for cooling air, wherein said inside edge comprises a groove for generating a head loss in said leakage zone so as to reduce a flow rate of cooling air passing through said leakage zone, and said groove comprises a rectangular section groove.