Industrial turbine stator vane
View Patent ↗An industrial turbine stator vane with a aft flowing serpentine flow cooling circuit with an inner endwall turn channel having a rib extending into the first leg of the serpentine circuit, where the rib separates the turn channel from a purge air channel located along the lower end of the leading edge wall that opens into a front rim cavity to discharge purge air. The separate purge air channel minimizes pressure loss in the serpentine flow and maintains high flow velocity to cool the lower end of the leading edge wall.
1. An industrial engine turbine stator vane comprising:
an airfoil extending between an outer diameter endwall and an inner diameter endwall;
a three-pass aft flowing serpentine cooling circuit formed within the airfoil with a first leg located along a leading edge of the airfoil and a third leg located adjacent to a trailing edge region of the airfoil;
a row of exit holes located along the trailing edge of the airfoil and connected to the third leg;
an outer diameter endwall turn channel connected between the second leg and the third leg;
an inner diameter endwall turn channel connected between the first leg and the second leg;
a rib extends into the first leg and separates a purge air channel from the inner diameter endwall turn channel;
the purge air channel opens into a front rim cavity; and,
a purge air hole is connected to an end of the third leg and opens into an aft rim cavity.
2. The industrial engine turbine stator vane of claim 1 , and further comprising:
the rib is parallel to the leading edge wall of the airfoil.
3. The industrial engine turbine stator vane of claim 1 , and further comprising:
the two turn channels extend outward from the respective endwalls and form a smooth curved surface for the cooling air flow.
4. The industrial engine turbine stator vane of claim 1 , and further comprising:
the three legs of the serpentine flow circuit have skewed trip strips along the side walls of the legs; and,
the two turn channels are without trip strips and form a smooth surface for the cooling air flow to minimize pressure loss.
5. An air cooled stator vane for a gas turbine engine comprising:
an airfoil extending between an inner endwall and an outer endwall;
a multiple pass serpentine flow cooling circuit with a first leg located adjacent to a leading edge of the airfoil and a last leg located adjacent to a trailing edge region of the airfoil;
an inner diameter endwall turn channel connected between the first leg and a second leg of the multiple pass serpentine flow cooling circuit; and,
the inner diameter endwall turn channel includes a rib that extends radially into the first leg and separates a purge air channel connected to a rim cavity from the inner diameter endwall turn channel connected to the second leg.
6. The air cooled turbine stator vane of claim 5 , and further comprising:
the inner diameter endwall turn channel extends inward from the inner endwall and forms a smooth curved surface for the cooling air flow from the first leg to the second leg.
7. The air cooled turbine stator vane of claim 6 , and further comprising:
the inner diameter endwall turn channel is without trip strips and forms a smooth surface for the cooling air flow to minimize pressure loss.
8. The air cooled turbine stator vane of claim 6 , and further comprising:
the radial extending rib is parallel to a leading edge wall of the airfoil.
9. The air cooled turbine stator vane of claim 6 , and further comprising:
a row of trailing edge exit holes connected to the last leg of the multiple pass serpentine flow cooling circuit; and,
a second purge air hole connected to an end of the last leg and opening into an aft rim cavity.