초록 ▼

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel with bifurcated exhaust channels formed by suction and pressure side trailing edge cooling channels in fluid communication with a central trailing edge cooling channel. The suction and pressure side tra

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel with bifurcated exhaust channels formed by suction and pressure side trailing edge cooling channels in fluid communication with a central trailing edge cooling channel. The suction and pressure side trailing edge cooling channels may be separated with a trailing edge rib. The suction and pressure side trailing edge cooling channels may be recessed from the airfoil external surface to control the flow of cooling fluids from the cooling system such that the exhaust flow minimizes shear mixing and thus lowers the aerodynamic loss yet maintains high film cooling effectiveness for the airfoil trailing edge.

대표청구항 ▼

I claim: 1. A turbine airfoil, comprising: a generally elongated, hollow airfoil formed by an outer wall and 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

I claim: 1. A turbine airfoil, comprising: a generally elongated, hollow airfoil formed by an outer wall and 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 positioned in internal aspects of the generally elongated, hollow airfoil; at least one trailing edge cooling channel positioned within the generally elongated, hollow airfoil and proximate to the trailing edge, wherein the at least one trailing edge cooling channel comprises a central trailing edge cooling channel, at least one suction side trailing edge cooling channel extending from the central trailing edge cooling channel through the trailing edge, and at least one pressure side trailing edge cooling channel extending from the central trailing edge cooling channel through the trailing edge; wherein the at least one suction side trailing edge cooling channel and the at least one pressure side trailing edge cooling channel are separated by a trailing edge rib forming the trailing edge and positioned in a general spanwise direction and the at least one suction side trailing edge cooling channel and the at least one pressure side trailing edge cooling channel are recessed from an outer surface forming the trailing edge; and a plurality of chordwise support ribs extending chordwise from the outer wall into contact with the trailing edge rib. 2. The turbine airfoil of claim 1, wherein the plurality of chordwise support ribs form a plurality of suction side chordwise support ribs positioned in the at least one suction side trailing edge cooling channel. 3. The turbine airfoil of claim 2, wherein the plurality of chordwise support ribs form a plurality of pressure side chordwise support ribs positioned in the at least one pressure side trailing edge cooling channel. 4. The turbine airfoil of claim 3, wherein the plurality of chordwise support ribs in the at least one pressure side trauma edge cooling channel are aligned in a spanwise direction with the plurality of chordwise support ribs in the at least one suction side trailing edge cooling channel. 5. The turbine airfoil of claim 3, wherein the plurality of chordwise support ribs in the at least one pressure side trailing edge cooling channel are offset in a spanwise direction from the plurality of chordwise support ribs in the at least one suction side trailing edge cooling channel. 6. The turbine airfoil of claim 1, further comprising a plurality of pin fins in the central trailing edge cooling channel and extending from an inner surface of the outer wall forming the suction side to an inner surface of the outer wall forming the pressure side. 7. The turbine airfoil of claim 1, wherein the at least one cavity in the elongated, hollow airfoil of the cooling system comprises a serpentine cooling channel having an opening for receiving cooling fluids from a fluid supply source and includes at least one exhaust orifice in an internal rib for exhausting cooling fluids into the at least one trailing edge cooling channel. 8. The turbine airfoil of claim 7, further comprising a plurality of trip strips extending inwardly from inner surfaces of the outer wall forming the serpentine cooling channel. 9. The turbine airfoil of claim 6, wherein the plurality of pin fins in the central trailing edge cooling channel are aligned into rows extending in a spanwise direction. 10. The turbine airfoil of claim 1, further comprising at least one leading edge cooling channel positioned proximate to the leading edge, extending generally spanwise to the leading edge, and in fluid communication with the at least one cavity forming the cooling system. 11. A. turbine airfoil, comprising: a generally elongated, hollows airfoil formed by an outer wall and 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 positioned in internal aspects of the generally elongated, hollow airfoil; at least one trailing edge cooling channel positioned within the generally elongated, hollow airfoil and proximate to the trailing edge, wherein the at least one trailing edge cooling channel comprises a central trailing, edge cooling channel, at least one suction side trailing edge cooling channel extending from the central trailing edge cooling channel through the trailing edge, and at least one pressure side trailing edge cooling channel extending from the central trailing edge cooling channel through the trailing edge; wherein the at least one suction side trailing edge cooling channel and the at least one pressure side trailing edge cooling channel are separated by a trailing edge rib forming the trailing edge and positioned in a general spanwise direction; wherein the at least one suction side trailing edge cooling channel and the at least one pressure side trailing edge cooling channel are recessed from an outer surface forming the trailing edge; a plurality of suction side chordwise support ribs positioned in the at least one suction side trailing edge cooling channel; and a plurality of pressure side chordwise support ribs positioned in the at least one pressure side trailing edge cooling channel. 12. The turbine airfoil of claim 11, wherein the plurality of pressure side chordwise support ribs in the at least one pressure side trailing edge cooling channel are aligned in a spanwise direction with the plurality of suction side chordwise support ribs in the at least one suction side trailing edge cooling channel. 13. The turbine airfoil of claim 11, wherein the plurality of pressure side chordwise support ribs in the at least one pressure side trailing edge cooling channel are offset in a spanwise direction from the plurality of suction side chordwise support ribs in the at least one suction side trailing edge cooling channel. 14. The turbine airfoil of claim 11, further comprising a plurality of pin fins in the central trailing edge cooling channel and extending from an inner surface of the outer wall forming the suction side to an inner surface of the outer wall forming the pressure side. 15. The turbine airfoil of claim 11, wherein the plurality of pin fins in the central trailing edge cooling channel are aligned into rows extending in a spanwise direction. 16. The turbine airfoil of claim 11, wherein the at least one cavity in the elongated, hollow airfoil of the cooling system comprises a serpentine cooling channel having an opening for receiving cooling fluids from a fluid supply source and includes at least one exhaust orifice in an internal rib for exhausting cooling fluids into the at least one trailing edge cool big channel. 17. The turbine airfoil of claim 16, further comprising a plurality of trip strips extending inwardly from inner surfaces of the outer wall forming the serpentine cooling channel. 18. The turbine airfoil of claim 11, further comprising at least one leading edge cooling channel positioned proximate to the leading edge, extending generally spanwise to the leading edge and in fluid communication with the at least one cavity forming the cooling system.