Patent ID: 7993097

Claim:
A cooling device for a stationary ring surrounding a gas-turbine hot-gas flow path, said ring being made up of a plurality of ring segments that are fastened by upstream and downstream fastener systems onto a plurality of spacer segments forming a stationary annular support spacer surrounding said ring so as to co-operate therewith to define at least one annular impact cavity into which at least one cooling-air supply orifice opens out, each ring segment having walls that are pierced with a plurality of air exhaust holes opening out both into the impact cavity, and into the hot-gas flow path, the device further comprising a cooling circuit configured to channel the air coming from leakage through the seals of the fastener systems that fasten together the ring and spacer segments, and to direct, without reducing said leakage, said air towards at least one of the axial ends of the ring segments in contact with the hot gas so as to cool said at least one of the axial ends, wherein said cooling circuit defines axial air flow paths for each upstream fastener system and/or downstream fastener system, said axial air flow paths being defined by recesses formed: (a) for each upstream fastener system, in a radially inner surface of an outer upstream hook of each ring segment and/or in a radially outer surface of an inner upstream hook of each spacer segment, and (b) for each downstream fastener system, in a radially inner surface of an outer downstream hook of each ring segment and/or in a radially outer surface of an inner branch of a clip surrounding the outer downstream hook.