| 摘要 |
A turbine engine component (52) includes an internal baffle (86) spaced between first and second walls (60,62). Each wall (60,62) may have a plurality of cooling holes (78) in fluid communication with respective upstream and downstream cooling paths (104,106) defined between the baffle (86) and the respective walls (60,62). Cooling air first flows through an upstream end portion (115) of the upstream cooling path (104), then through a downstream end portion (113) where the air enters a bleed aperture (112) in the baffle (86). From the bleed aperture (112), a portion of or all of the cooling air may enter an internal cavity (68) defined by the baffle (86) and, from there, flows through at least one hole (114) that may be a plurality of impingement holes (114) in the baffle (86), and into the downstream cooling passage (106) where the portion or all of the remaining cooling air may exit the component through the cooling holes (78) in the second wall (62). |
