Patent ID: 8152463

Claim:
A method for impingement air cooling for gas turbines, comprising: providing a first partition wall having a plurality of impingement air openings; providing a separate second wall spaced apart from the first partition wall to form a cooling air duct between the first partition wall and the second wall, the first partition wall separating a cooling air supply from the cooling air duct, the second wall separating the cooling air duct from a hot gas flow; supplying separate jets of cooling air via the impingement air openings to hit an area of the second wall to impingement cool that area of the second wall; removing the cooling air from the cooling air duct between the two walls in the form of a cross-flow; creating intervallic annular swirl structures with high cooling effect in the cross-flow, with these annular swirl structures penetrating the cross-flow with high intensity and frequency and hitting the second wall area to be impingement cooled prior to any mixing of the cooling air and the hot gas flow; and supplying the cooling air to the impingement air openings in cooling air velocity packs (V cool (t)) having a certain amplitude (V cool ) and frequency (f).