초록 ▼

A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetw

A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetween. A plurality of film cooling shelf holes are disposed through the tip shelf to an internal cooling circuit of the blade and are spaced away from a junction between the recessed tip wall portion and the tip shelf. The exemplary embodiment of the airfoil includes shelf hole centerlines of the holes passing through pierce points in the shelf. At least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. A majority of centerlines are angled away from vertical lines passing through the pierce points at first component angles in a range between 2 degrees and 16 degrees.

대표청구항 ▼

What is claimed is: 1. A turbine blade comprising: an airfoil including an airfoil outer wall extending longitudinally outwardly from a root, pressure side and suction sides extending laterally from a leading edge to a trailing edge of the airfoil, a squealer tip at a radially outer end of the airf

What is claimed is: 1. A turbine blade comprising: an airfoil including an airfoil outer wall extending longitudinally outwardly from a root, pressure side and suction sides extending laterally from a leading edge to a trailing edge of the airfoil, a squealer tip at a radially outer end of the airfoil, the squealer tip including a radially outer tip cap attached to the airfoil outer wall, a continuous squealer tip wall extending radially outwardly from and continuously around the tip cap forming a radially outwardly open tip cavity, a recessed tip wall portion recessed inboard from the pressure side of the airfoil outer wall forming a tip shelf therebetween, an internal cooling circuit extending longitudinally outwardly from the root to the tip cap bounded in part by the recessed tip wall portion, and a plurality of film cooling shelf holes disposed through the tip shelf and extending through the recessed tip wall portion directly into the internal cooling circuit and spaced away from a junction between the recessed tip wall portion and the tip shelf. 2. A turbine blade as claimed in claim 1, further comprising: the film cooling shelf holes having shelf hole centerlines passing through pierce points in the shelf angled at compound angles with respect to vertical lines passing through the pierce points, the compound angles have orthogonal first and second component angles, the first component angles lie in first planes defined by the vertical lines and first coordinate lines that are normal to the vertical lines and extend between the vertical lines and the recessed tip wall portion, the second component angles lie in second planes defined by the vertical lines and second coordinate lines that are normal to the vertical lines and normal to the first coordinate lines, and at least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. 3. A turbine blade as claimed in claim 2, further comprising the shelf hole centerlines being angled at the second component angles in downstream lateral directions with respect to vertical lines wherein the downstream lateral directions are normal to corresponding ones of the outboard directions and the vertical lines. 4. A turbine blade as claimed in claim 2, wherein the first component angles lie in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 5. A turbine blade as claimed in claim 3, further comprising the shelf hole centerlines being spaced away from a fillet at the junction. 6. A turbine blade as claimed in claim 5, further comprising the film cooling shelf holes extending into the fillet no more than 50 percent of a fillet width of the fillet as measured along the tip shelf. 7. A turbine blade as claimed in claim 6, wherein the first component angle lies in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 8. A turbine blade as claimed in claim 2, wherein the majority of first component angles are in a range between 2 degrees and 16 degrees. 9. A turbine blade as claimed in claim 8, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0. 5 degrees and 5 degrees. 10. A turbine blade as claimed in claim 2, further comprising the pressure side of the airfoil outer wall including the recessed tip wall portion being angled away from the shelf hole centerlines in an inboard direction. 11. A turbine blade as claimed in claim 10, wherein the first component angles are in a range between 2 degrees and 16 degrees. 12. A turbine blade as claimed in claim 11, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 13. A turbine blade as claimed in claim 2, further comprising the turbine blade made with a nickel-base superalloy having a free sulfur content less than about 1 part per million by weight. 14. A turbine blade as claimed in claim 13, further comprising the shelf hole centerlines being angled at the second component angles in downstream lateral directions with respect to vertical lines wherein the downstream lateral directions are normal to corresponding ones of the outboard directions and the vertical lines. 15. A turbine blade as claimed in claim 13, wherein the first component angles lie in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 16. A turbine blade as claimed in claim 14, further comprising the shelf hole centerlines being spaced away from a fillet at the junction. 17. A turbine blade as claimed in claim 16, further comprising the film cooling shelf holes extending into the fillet no more than 50 percent of a fillet width of the fillet as measured along the tip shelf. 18. A turbine blade as claimed in claim 17, wherein the first component angle lies in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 19. A turbine blade as claimed in claim 13, wherein the majority of first component angles are in a range between 2 degrees and 16 degrees. 20. A turbine blade as claimed in claim 19, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 21. A turbine blade as claimed in claim 13, further comprising the pressure side of the airfoil outer wall including the recessed tip wall portion being angled away from the shelf hole centerlines in an inboard direction. 22. A turbine blade as claimed in claim 21, wherein the first component angles are in a range between 2 degrees and 16 degrees. 23. A turbine blade as claimed in claim 22, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 24. A turbine blade as claimed in claim 2, further comprising a thermal barrier coating on inboard and outboard sides of the squealer tip wall, a radially outwardly facing surface of the tip cap within the squealer tip wall, and a flat top of the squealer tip wall. 25. A turbine blade as claimed in claim 24, further comprising the turbine blade made with a nickel-base superalloy having a free sulfur content less than about 1 part per million by weight. 26. A turbine blade as claimed in claim 25, further comprising the shelf hole centerlines being angled at the second component angles in downstream lateral directions with respect to vertical lines wherein the downstream lateral directions are normal to corresponding ones of the outboard directions and the vertical lines. 27. A turbine blade as claimed in claim 26, wherein the first component angles lie in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 28. A turbine blade as claimed in claim 27, further comprising the shelf hole centerlines being spaced away from a fillet at the junction. 29. A turbine blade as claimed in claim 28, further comprising the film cooling shelf holes extending into the fillet no more than 50 percent of a fillet width of the fillet as measured along the tip shelf. 30. A turbine blade as claimed in claim 29, wherein the majority of first component angles are in a range between 2 degrees and 16 degrees. 31. A turbine blade as claimed in claim 30, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 32. A turbine blade as claimed in claim 25, further comprising a plurality of chordally spaced apart tip cap supply holes extending radially through the tip cap from the cooling circuit into the tip cavity, the tip cap supply holes being located near the tip wall along the suction side of the continuous outer wall. 33. A turbine blade as claimed in claim 32, further comprising the shelf hole centerlines being angled at the second component angles in downstream lateral directions with respect to vertical lines wherein the downstream lateral directions are normal to corresponding ones of the outboard directions and the vertical lines. 34. A turbine blade as claimed in claim 33, wherein the first component angles lie in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 35. A turbine blade as claimed in claim 34, further comprising the shelf hole centerlines being spaced away from a fillet at the junction. 36. A turbine blade as claimed in claim 35, further comprising the film cooling shelf holes extending into the fillet no more than 50 percent of a fillet width of the fillet as measured along the tip shelf. 37. A turbine blade as claimed in claim 36, wherein the majority of first component angles are in a range between 2 degrees and 16 degrees. 38. A turbine blade as claimed in claim 37, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 39. A turbine blade as claimed in claim 24, further comprising the film cooling shelf holes having hole diameters in a range of about 14-18 mils. 40. A turbine blade as claimed in claim 39, further comprising the shelf hole centerlines being angled at the second component angles in downstream lateral directions with respect to vertical lines wherein the downstream lateral directions are normal to corresponding ones of the outboard directions and the vertical lines. 41. A turbine blade as claimed in claim 40, wherein the first component angles lie in first planes defined by the vertical lines and transverse lines which are shortest distances between the vertical lines and the recessed tip wall portion. 42. A turbine blade as claimed in claim 41, further comprising the shelf hole centerlines being spaced away from a fillet at the junction. 43. A turbine blade as claimed in claim 41, further comprising the film cooling shelf holes extending into the fillet no more than 50 percent of a fillet width of the fillet as measured along the tip shelf. 44. A turbine blade as claimed in claim 43, wherein the majority of first component angles are in a range between 2 degrees and 16 degrees. 45. A turbine blade as claimed in claim 44, further comprising a first plurality of the film cooling shelf holes having shelf hole centerlines with the positive first component angles in a range between 0.5 degrees and 5 degrees. 46. A turbine blade as claimed in claim 45, further comprising the turbine blade made with a nickel-base superalloy having a free sulfur content of less than about 1 part per million by weight. 47. A turbine blade as claimed in claim 46, further comprising a plurality of chordally spaced apart tip cap supply holes extending radially through the tip cap from the cooling circuit into the tip cavity, the tip cap supply holes being located near the tip wall along the suction side of the continuous outer wall.