| 摘要 |
A gas turbine vane airfoil (17) has an aft cavity (44) in which an insert (47) is placed so as to form a cooling air passage between the insert and the walls that form the cavity (54', 54"). The insert serves to distribute cooling air around the passage. Cooling air from the passage exits the vane airfoil via film cooling holes (56) in the pressure surface (40) of the airfoil and via a passage (55) formed in the trailing edge (29) of the airfoil. A W-shaped flexible regulator seal (52) is attached to the trailing edge (50) of the insert (47) and has legs (64, 65) that are pressed against ridges (80) in the airfoil walls. Holes (68, 69) in the regulating seal regulate the amount of cooling air (74) flowing from the passage surrounding the insert to the trailing edge passage, thereby preventing too low a pressure differential between the cooling air in the passage surrounding the insert and the hot compressed gas flowing over the airfoil, which would inhibit adequate film cooling.
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