| 摘要 |
The louvered linear construction for a gas turbine engine combustor comprises a film cooling system with a double pass cool air film generator. The cooling inlet faces compressor discharge air to impinge on a depending lip extending from the hot wall of the louver disposed intermidiate to the cooling air inlet and the discharge slot. The cooling air is directed to impinge on the depending wall, change directions in a double loop configuration and heat the stiffening ring prior to discharging into the combustor in a film of uniform cooling air. |
