Turbine airfoil cooling system with axial flowing serpentine cooling chambers
View Patent ↗A cooling system for a turbine airfoil of a turbine engine having suction and pressure side serpentine cooling channels formed between an internal support core and an outer wall of the turbine airfoil. The suction and pressure side serpentine cooling channels may be formed from legs extending in a general chordwise direction between leading and trailing edges of the airfoil. The suction and pressure side serpentine cooling channels may receive cooling fluids from a cooling fluid supply source through a cooling fluid inlet, pass the cooling fluids through the cooling system and exhaust the cooling fluids through a cooling fluid exhaust orifice proximate to the tip section. The cooling system is particularly suitable for use with low cooling fluid flow.
1. A turbine airfoil, comprising:
a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil;
an outer wall forming an outer surface of the generally elongated airfoil;
a suction side serpentine cooling channel positioned proximate to a suction side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the suction side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil; and
a pressure side serpentine cooling channel positioned proximate to a pressure side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the pressure side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil;
wherein a leg forming a portion of the suction side serpentine cooling channel has a width proximate to the leading edge that differs from a width of the same leg proximate to the trailing edge.
2. The turbine airfoil of claim 1 , further comprising a leading edge impingement channel extending along the leading edge of the generally elongated hollow airfoil.
3. The turbine airfoil of claim 1 , further comprising a trailing edge impingement channel extending along the trailing edge of the generally elongated hollow airfoil.
4. The turbine airfoil of claim 1 , further comprising a cooling fluid inlet positioned proximate to the root of the airfoil that places the suction side and pressure side serpentine cooling channels in fluid communication with a cooling fluid supply source.
5. The turbine airfoil of claim 1 , further comprising a cooling fluid exhaust orifice positioned proximate to the tip section of the generally elongated hollow airfoil and in fluid communication with the suction side and pressure side serpentine cooling channels.
6. The turbine airfoil of claim 1 , further comprising a plurality of trip strips extending into the suction side serpentine cooling channel from an inner surface of the outer wall.
7. The turbine airfoil of claim 6 , wherein the plurality of trip strips are positioned at an acute angle between a chordwise direction and a spanwise direction.
8. The turbine airfoil of claim 1 , further comprising a plurality of trip strips extending into the pressure side serpentine cooling channel from an inner surface of the outer wall.
9. The turbine airfoil of claim 8 , wherein the plurality of trip strips are positioned at an acute angle between a chordwise direction and a spanwise direction.
10. The turbine airfoil of claim 1 , wherein the suction side serpentine cooling channel comprises at least three legs in fluid communication with each other through turns positioned at the leading and trailing edges.
11. The turbine airfoil of claim 1 , wherein the pressure side serpentine cooling channel comprises at least three legs in fluid communication with each other through turns positioned at the leading and trailing edges.
12. The turbine airfoil of claim 1 , wherein a leg forming a portion of the pressure side serpentine cooling channel has a width proximate to the leading edge that differs from a width of the same leg proximate to the trailing edge.
13. A turbine airfoil, comprising:
a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil;
an outer wall forming an outer surface of the generally elongated airfoil;
a suction side serpentine cooling channel positioned proximate to a suction side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the suction side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil; and
a pressure side serpentine cooling channel positioned proximate to a pressure side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the pressure side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil;
wherein a width of the suction side serpentine channel between the internal support core and the outer wall differs from a width of the pressure side serpentine channel between the internal support core and the outer wall.
14. The turbine airfoil of claim 13 , wherein a width of the suction side serpentine channel between the internal support core and the outer wall differs from the root to the tip section of the generally elongated hollow airfoil.
15. The turbine airfoil of claim 14 , wherein a width of the pressure side serpentine channel between the internal support core and the outer wall differs from the root to the tip section of the generally elongated hollow airfoil.
16. A turbine airfoil, comprising:
a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil;
an outer wall forming an outer surface of the generally elongated airfoil;
an internal support core positioned in the at least one cavity;
a suction side serpentine cooling channel positioned proximate to a suction side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the suction side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil;
a pressure side serpentine cooling channel positioned proximate to a pressure side of the generally elongated airfoil and defined by the internal support core and the outer wall;
wherein the pressure side serpentine cooling channel is formed from a plurality of legs that are positioned in a generally chordwise direction from the leading edge to the trailing edge of the generally elongated, hollow airfoil;
a leading edge impingement channel extending alone the leading edge of the generally elongated hollow airfoil;
a trailing edge impingement channel extending along the trailing edge of the generally elongated hollow airfoil;
a cooling fluid inlet positioned proximate to the root of the airfoil blade that places the suction side and pressure side serpentine cooling channels in fluid communication with a cooling fluid supply source;
a cooling fluid exhaust orifice positioned in the trailing edge proximate to the tip section of the generally elongated hollow airfoil and in fluid communication with the suction side and pressure side serpentine cooling channels;
wherein a leg forming a portion of the suction side serpentine cooling channel has a width proximate to the leading edge that differs from a width of the same channel proximate to the trailing edge; a leg forming a portion of the pressure side serpentine cooling channel has a width proximate to the leading edge that differs from a width of the same channel proximate to the trailing edge; a width of the suction side serpentine channel between the internal support core and the outer wall differs from the root to the tip section of the generally elongated hollow airfoil; and a width of the pressure side serpentine channel between the internal support core and the outer wall differs from the root to the tip section of the generally elongated hollow airfoil.
17. The turbine airfoil of claim 16 , further comprising a plurality of trip strips extending into the suction side serpentine cooling channel from an inner surface of the outer wall and a plurality of trip strips extending into the pressure side serpentine cooling channel from an inner surface of the outer wall; wherein the plurality of trips strips in the pressure and suction side serpentine cooling channels are positioned at acute angles between a chordwise direction and a spanwise direction.
18. The turbine airfoil of claim 16 , wherein a width of the suction side serpentine channel between the internal support core and the outer wall differs from a width of the pressure side serpentine channel between the internal support core and the outer wall.