| 摘要 |
An airfoil for a gas turbine engine, comprising:
an outer wall having a plurality cooling air exit openings (60);
an inner wall spaced apart from the outer wall, wherein the inner wall has a plurality of cooling air inlet openings (58);
a plurality of flow migration dams (74), wherein the flow migration dams extend between the inner wall and the outer wall, the plurality of flow migration dams forming therebetween a plurality of cooling passages, wherein the cooling passages are in fluid communication with the cooling air inlet openings and with the cooling air exit openings; and
a cooling air supply passage in fluid communication with the cooling air inlet openings, wherein the cooling air supply passage is operative to supply cooling air to the cooling air inlet openings (58). |
