Patent ID: 7871246

Claim:
An airfoil for a gas turbine comprising: an outer structure comprising a first wall; an inner structure comprising a second wall spaced relative to said first wall such that a cooling gap is defined between at least portions of said first and second walls, an inner surface of said second wall defining an inner cavity, said inner structure further comprising a separating member for separating said inner cavity of said inner structure into a cooling fluid supply cavity and a cooling fluid collector cavity, said second wall comprising at least one first impingement passage, at least one second impingement passage, and at least one bleed passage; and seal structure provided within said cooling gap between said first and second walls for separating said cooling gap into first and second cooling fluid impingement gaps, said at least one first impingement passage extending from said cooling fluid supply cavity to said first cooling fluid impingement gap, said at least one bleed passage extending from said first cooling fluid impingement gap to said cooling fluid collector cavity, and said at least one second impingement passage extending from said cooling fluid collector cavity to said second cooling fluid impingement gap such that cooling fluid exits said collector cavity through said at least one second impingement passage and passes into said second cooling fluid impingement gap.