| 摘要 |
PURPOSE:To enable every part of a gas turbine blade to be cooled evenly and sufficiently using less amount of cooling air, by forming a front and a rear cooling passages separately from each other and also forming turbulence chambers between laminar cooling air port/normal air port and a cooling air duct. CONSTITUTION:The outer shell 1 of a blade is partitioned by a rib 2 to form inner spaces, in which a front and a rear inserts 3, 4 are inserted respectively. Air in the one-side insert 3 goes through air holes 12 and, after cooing the inner wall of the leading edge of the shell 1 via a turbulence chamber 13, flows through respective cooling air duct 6, 7 to laminar cooling air ports 10, 11 via respective turnulence chambers 8, 9. While the cooling air in the other side insert 4 goes through respective cooling air holes 19, 20 and, after flowing through respective cooling air ducts 15, 16 via respective turbulence chambers 17, 18, blows out through respective laminar cooling air ports 23, 24 via respective turbulence chambers 21, 22. The other part of the air flows through the cooling air ducts 15, 16 then join again to flow out from the air blowing hole 26 at the trailing edge of the blade.
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