| 摘要 |
A turbine airfoil (44) having a baffleless cooling passage (66) for directing cooling fluid toward a trailing edge (72) is disclosed. Various construction details are developed which provide axially oriented, interrupted channels (104) for turning a flow of cooling fluid from a radial direction to an axial direction. In a particular embodiment, a turbine airfoil (44) has a cooling passage (66) including a plurality of radially spaced walls (76), a plurality of radially spaced dividers (82) downstream of the walls (76), and a plurality of radially spaced pedestals (78) positioned axially between the walls (76) and dividers (82). The walls (76) and dividers (82) define channels (104) having an axial interruption permitting cross flow between adjacent channels (104). The cross flow minimizes the adverse affects of a blockage within a subchannel (92) between adjacent walls (76). The pedestals (78) are aligned with the subchannels (92) such that cooling fluid exiting a subchannel (92) impinges upon the pedestal (78). |
