Cooled gas turbine vane
View Patent ↗A gas turbine airfoil (e.g. 12 ) includes a pressure sidewall ( 14 ) and a suction sidewall ( 16 ) joined along respective leading and trailing edges ( 18, 20 ) and extending radially outward from an inner diameter ( 26 ) to an outer diameter ( 22 ). The airfoil includes a plurality of suction side flow channels ( 52 ) extending chordwise within the suction sidewall and having respective heights selected to achieve a desired degree of cooling for the suction sidewall. The airfoil also includes a plurality of pressure side flow channels ( 30 ) extending chordwise within the pressure sidewall and having respective heights selected to achieve a desired degree of cooling for the pressure sidewall. A transition region ( 58 ) is provided in each flow channel wherein the height of the channel is reduced to an outlet height so that respective outlets of the flow channels can each be independently disposed in the trailing edge.
1. A gas turbine airfoil comprising:
a pressure sidewall and a suction sidewall joined along respective leading and trailing edges and extending radially outward from an inner diameter to a outer diameter;
a plurality of suction side flow channels extending chordwise within the suction sidewall and having respective heights selected to achieve a desired degree of cooling for the suction sidewall;
a plurality of pressure side flow channels extending chordwise within the pressure sidewall and having respective heights selected to achieve a desired degree of cooling for the pressure sidewall;
wherein a combined height of the suction side flow channels and the pressure side flow channels is greater than an available height along the trailing edge; and
a transition region in each flow channel wherein the height of the channel is reduced to an outlet height so that respective outlets of the flow channels can each be independently disposed in the trailing edge.
2. The airfoil of claim 1 , the transition region comprising a linear taper from the height of the channel to the outlet height.
3. The airfoil of claim 1 , the transition region comprising a curved taper from the height of the channel to the outlet height.
4. The airfoil of claim 1 , further comprising a convective cooling fin formed in a wall of at least one of the flow channels.
5. The airfoil of claim 1 , wherein the pressure side flow channels are aligned in parallel with corresponding suction flow side channels and the plurality of suction side flow channel outlets are interposed between respective pressure side flow channel outlets.
6. The airfoil of claim 1 , further comprising a leading edge plenum receiving a cooling fluid flow and discharging a suction side cooling fluid flow into respective suction side flow channels and discharging a pressure side cooling fluid flow into respective pressure side flow channels.
7. A gas turbine engine comprising the airfoil of claim 1 .
8. A gas turbine airfoil comprising:
a pressure sidewall and a suction sidewall joined along respective leading and trailing edges and extending radially outward from an inner diameter to a outer diameter;
a leading edge plenum receiving a cooling fluid flow and discharging a suction side cooling fluid flow and a pressure side cooling fluid flow;
a suction side flow channel integrally formed within the suction sidewall and extending chordwise within the suction sidewall from the leading edge plenum to the trailing edge and receiving the suction side cooling fluid flow from the leading edge plenum, conducting the suction side cooling fluid flow along an entire length of the suction side flow channel, and discharging the suction side cooling fluid flow from a first outlet disposed along the trailing edge, the suction side flow channel having a height along an upstream portion that is greater than a height of the first outlet;
a pressure side flow channel integrally formed within the pressure sidewall and extending chordwise within the pressure sidewall from the leading edge plenum to the trailing edge and receiving the pressure side cooling fluid flow from the leading edge plenum, conducting the pressure side cooling fluid flow along an entire length of the pressure side flow channel, and discharging the pressure side cooling fluid flow from a second outlet disposed along the trailing edge, the pressure side flow channel having a height along an upstream portion that is greater than a height of the second outlet; and
the first outlet and the second outlet disposed adjacent one another along the trailing edge so that the respective cooling flows do not mix before exiting the airfoil.
9. The airfoil of claim 8 , further comprising a transition region in each flow channel wherein the height of the channel is reduced to the height of the outlet so that the respective outlets of the flow channels can each be independently disposed in the trailing edge.
10. The airfoil of claim 9 , the transition region comprising a linear taper from the height of the channel to the height of the outlet.
11. The airfoil of claim 9 , the transition region comprising a curved taper from the height of the channel to the height of the outlet.
12. The airfoil of claim 8 , further comprising a convective cooling fin formed in a wall of at least one of the flow channels.
13. A gas turbine engine comprising the airfoil of claim 8 .
14. A gas turbine airfoil comprising:
a pressure sidewall and a suction sidewall joined along respective leading and trailing edges and extending radially outward from an inner diameter to an outer diameter, the pressure and suction sidewalls defining a cooling fluid flow channel conducting a cooling fluid flow from an inlet in the outer diameter to an exit in the inner diameter;
a leading edge plenum receiving a plenum portion of the cooling fluid flow and discharging a suction side cooling fluid flow and a pressure side cooling fluid flow;
a suction side flow channel integrally formed within the suction sidewall and extending chordwise within the suction sidewall from the leading edge plenum to the trailing edge and receiving the suction side cooling fluid flow from the leading edge plenum, conducting the suction side cooling fluid flow along an entire length of the suction side flow channel, and discharging the suction side cooling fluid flow from a first outlet disposed along the trailing edge, the suction side flow channel selected to achieve a desired degree of insulation between a hot combustion gas flowing around the exterior of the airfoil and the cooling fluid flow;
a pressure side flow channel integrally formed within the pressure sidewall and extending chordwise within the pressure sidewall from the leading edge plenum to the trailing edge and receiving a pressure side cooling fluid flow from the leading edge plenum, conducting the pressure side cooling fluid flow along an entire length of the pressure side flow channel, and discharging the pressure side cooling fluid flow from a second outlet disposed along the trailing edge, the pressure side flow channel selected to achieve a desired degree of insulation between the hot combustion gas and the cooling fluid flow; and
the first outlet and the second outlet disposed adjacent one another along the trailing edge so that the respective cooling flows do not mix before exiting the airfoil.
15. The gas turbine airfoil of claim 14 , the exit comprising a passageway configured to control the cooling fluid flow exiting the airfoil so that a sufficient cooling flow is retained within the airfoil to provide a desired degree of cooling for the airfoil.
16. A gas turbine engine comprising the airfoil of claim 14 .