| 摘要 |
A turbine engine airfoil (100) includes a three-pass serpentine shaped cooling cavity (102) including a leading edge chamber (114), an oversized intermediate chamber (116), and a trailing edge chamber (118) in flow communication. The cavity further includes a combination of a plurality of ribs (124, 126, 148, and 150) and a plurality of pins (130), a purge air swirler (146), a turning vane (134), and a metering partition (142) which mixes the high pressure air and provides increased air cooling and uniform flow control in the airfoil. The metering partition provides a decrease of the air pressure in the trailing edge chamber allowing for an increase in the number of trailing edge slots. <IMAGE> |
