초록 ▼

A cooling system for a turbine airfoil of a turbine engine having a perimeter cooling channel formed from a portion of a serpentine cooling channel, an airfoil tip cooling channel, and a leading edge cooling channel. The cooling system also includes cooling channels enabling cooling fluids to be di

A cooling system for a turbine airfoil of a turbine engine having a perimeter cooling channel formed from a portion of a serpentine cooling channel, an airfoil tip cooling channel, and a leading edge cooling channel. The cooling system also includes cooling channels enabling cooling fluids to be discharged into the root of the airfoil to cool rim cavities and purge air therein. The cooling system may be configured such that the cooling fluids may pass into a mid-chord serpentine cooling channel, flow through the serpentine cooling channel generally in a chordwise direction from the leading edge toward the trailing edge, flow toward the tip section and along the trailing edge, flow from the trailing edge toward the leading edge in the airfoil tip cooling channel, flow along the leading edge in the leading edge cooling channel, through the root of the blade, and be exhausted into a rim cavity.

대표청구항 ▼

I claim: 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 to the first end for supporting the airfoil and for coupling the airfoil to a disc, and a

I claim: 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 to 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; the cooling system comprising a serpentine cooling channel positioned in a mid-chord region of the generally elongated airfoil and being formed from a first leg, a second leg, and a third leg wherein the legs are generally aligned with each other and the first leg is positioned between the leading edge of the generally elongated airfoil and the second leg; a cooling supply channel in fluid communication with the first leg for supplying cooling fluids to the first leg from the root; an airfoil tip cooling channel in fluid communication with the third leg of the serpentine cooling channel and extending proximate to an outer wall forming the tip section of the airfoil; a leading edge cooling channel in fluid communication with the airfoil tip cooling channel and extending along the leading edge of the generally elongated airfoil and into the root of the airfoil to exhaust cooling fluids into the root of the generally elongated airfoil. 2. The turbine airfoil of claim 1, further comprising at least one aft rim cooling channel in fluid communication with the serpentine cooling channel. 3. The turbine airfoil of claim 2, wherein the at least one aft rim cooling channel is in fluid communication with a serpentine cooling channel turn coupling the second leg of the serpentine cooling channel to the third leg of the serpentine cooling channel. 4. The turbine airfoil of claim 3, wherein the at least one aft rim cooling channel forms an opening in an outer surface of the root of the generally elongated airfoil. 5. The turbine airfoil of claim 1, further comprising at least one trailing edge exhaust orifice in fluid communication with the third leg of the serpentine cooling channel and forming at least one cooling fluid exhaust orifice in the trailing edge of the generally elongated airfoil. 6. The turbine airfoil of claim 5, wherein the at least one trailing edge exhaust orifice comprises a plurality of trailing edge exhaust orifices positioned generally at acute angles relative to the third leg of the serpentine cooling channel and pointed toward the tip section of the generally elongated airfoil. 7. The turbine airfoil of claim 1, further comprising at least one tip exhaust orifice in fluid communication with the airfoil tip cooling channel and forming at least one cooling fluid exhaust orifice in the tip section of the generally elongated airfoil. 8. The turbine airfoil of claim 7, wherein the at least one tip exhaust orifice comprises a plurality of tip exhaust orifices positioned generally at acute angle relative to the airfoil tip cooling channel and pointed in a downstream direction. 9. The turbine airfoil of claim 8, further comprising at least one trip strip in at least one of the group consisting of the serpentine cooling channel, the airfoil tip cooling channel, and the leading edge cooling channel. 10. The turbine airfoil of claim 9, wherein the at least one trip strip protrudes from an outer wall forming a pressure side of the generally elongated airfoil. 11. The turbine airfoil of claim 10, wherein the at least one trip strip comprises a plurality of trip strips protruding from the outer walls forming the pressure side and a suction side of the generally elongated airfoil. 12. The turbine airfoil of claim 1, wherein a single rib extends from a pressure side to a suction side of the generally elongated airfoil and separates the leading edge cooling channel from the first leg of the serpentine cooling channel. 13. The turbine airfoil of claim 1, wherein an outer wall of the generally elongated airfoil forms a downstream side of the third leg of the serpentine cooling channel and forms the trailing edge of the generally elongated airfoil. 14. 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 to 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; the cooling system comprising a serpentine cooling channel positioned in a mid-chord region of the generally elongated airfoil and being formed from a first leg, a second leg, and a third leg wherein the legs are generally aligned with each other and the first leg is positioned between the trailing edge of the generally elongated airfoil and the second leg; a cooling supply channel in fluid communication with the first leg for supplying cooling fluids to the first leg from the root; an airfoil tip cooling channel in fluid communication with the third leg of the serpentine cooling channel and extending proximate to an outer wall forming the tip section of the airfoil; a trailing edge cooling channel in fluid communication with the airfoil tip cooling channel and extending along the trailing edge of the generally elongated airfoil and into the root of the airfoil to exhaust cooling fluids into the root of the generally elongated airfoil and into an aft rim cavity; wherein an outer wall of the generally elongated airfoil forms a downstream side of the third leg of the serpentine cooling channel and forms the trailing edge of the generally elongated airfoil; and wherein the outer wall of the generally elongated airfoil forms the tip section and an outer side of the airfoil tip cooling channel. 15. The turbine airfoil of claim 14, further comprising at least one forward rim cooling channel in fluid communication with the serpentine cooling channel. 16. The turbine airfoil of claim 15, wherein the at least one forward rim cooling channel is in fluid communication with a serpentine cooling channel turn coupling the second leg of the serpentine cooling channel to the third leg of the serpentine cooling channel. 17. The turbine airfoil of claim 14, further comprising a plurality of trailing edge exhaust orifices positioned generally at acute angles relative to the trailing edge cooling channel of the serpentine cooling channel and pointed toward the tip section of the generally elongated airfoil. 18. The turbine airfoil of claim 14, further comprising a plurality of tip exhaust orifices positioned generally at acute angles relative to the airfoil tip cooling channel and pointed in a downstream direction. 19. The turbine airfoil of claim 18, further comprising at least one trip strip extending from an inner surface of a pressure side and an inner surface in a suction side in at least one of the group consisting of the serpentine cooling channel, the airfoil tip cooling channel, and the trailing edge cooling channel. 20. The turbine airfoil of claim 14, wherein a single rib extending from a pressure side to a suction side of the generally elongated airfoil separates the trailing edge cooling channel from the first leg of the serpentine cooling channel.