Turbine stator vane with purge air channel
A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and a separate purge air channel to supply purge air to the rim cavities. The purge channel is formed as a separate channel from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.
1. A stator vane for an industrial gas turbine engine comprising:
an airfoil with a leading edge region and a trailing edge region;
the airfoil extending between an outer endwall and an inner endwall;
a first leg of a serpentine flow cooling circuit located along the leading edge region;
a second leg connected to the first leg through a lower turn channel;
a purge air channel formed between the first leg and the second leg;
the purge air channel having an inlet opening above the outer endwall and bleed hole opening below the inner endwall; and,
the purge air channel connected to the lower turn channel through a core tie hole.
2. The stator vane of claim 1 , and further comprising:
the purge air channel opens into a front side rim cavity bleed hole and an aft side rim cavity bleed hole.
3. The stator vane of claim 2 , and further comprising:
the front side rim cavity bleed hole and the aft side rim cavity bleed hole both open onto sides of the purge air channel located below the inner endwall.
4. The stator vane of claim 1 , and further comprising:
the purge air channel opens into a plurality of bleed holes that open onto a bottom side of the inner endwall.
5. The stator vane of claim 1 , and further comprising:
the purge air channel is a smooth channel without trip strips such that a pressure loss and a heat transfer coefficient are minimal.
6. The stator vane of claim 1 , and further comprising:
the lower turn channel and the upper turn channel are both smooth channels without trip strips such that a pressure loss and a heat transfer coefficient are minimal.
7. The stator vane of claim 1 , and further comprising:
a print-out hole located at an end of the third leg to discharge purge air into an aft side rim cavity.
8. A process for cooling a stator vane and purging a rim cavity of a gas turbine engine, the stator vane having an airfoil extending between an inner endwall and an outer endwall, the process comprising the steps of:
passing cooling air through the airfoil in a serpentine flow path from a leading edge to a trailing edge to provide cooling for the airfoil;
passing purge air from the outer endwall to the inner endwall through a separate passage formed between adjacent channels within the airfoil from the serpentine flow path;
discharging some of the purge air into the serpentine flow path; and,
discharging the remaining purge air into the rim cavity of the turbine.
9. The process for cooling a stator vane and purging a rim cavity of claim 8 , and further comprising the steps of:
discharging most of the serpentine flow cooling air through exit holes in the trailing edge to provide cooling for the trailing edge region; and,
discharging a remaining serpentine flow cooling air from the serpentine flow into an aft side of the rim cavity.
10. The process for cooling a stator vane and purging a rim cavity of claim 8 , and further comprising the step of:
passing the purge air through the separate passage within the airfoil without imparting any turbulent flow to limit pressure loss and heat transfer to the purge air.