| 摘要 |
A turbine vane for a gas turbine engine having an internal cooling system formed from at least one serpentine cooling channel with enhanced cooling elements. The serpentine cooling channel may include a first turn manifold with purge air discharge orifices inline with a first pass of the serpentine cooling channel. Cooling fluids may be used to cooling the leading edge of the vane and passed through the purge air discharge orifices to purge the rim cavity proximate to the endwall. The first turn manifold may also include a plurality of trip strips. The trips strips may be positioned on the suction and pressure sidewalls and may be offset from trip strips on the opposing sidewall. The cooling system may also include an aft purge rim orifice.
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