Hybrid high temperature articles and method of making

• US 6,726,444 B2
• Filed: 03/18/2002
• Issued: 04/27/2004
• Est. Priority Date: 03/18/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Jiang, Liang, Zhao, Ji-Cheng, Schafrik, Robert Edward, Darolia, Ramgopal, Jackson, Melvin Robert
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Kershteyn, Igor
• Application Number:
  US10/063,091
• Publication Number:
  US 20030175122A1
• Time in Patent Office: 771 Days
• Field of Search: 415/115, 415/200, 416/97.R, 416/96.A, 416/241.R, 416/241.B
• US Class Current: 415/115
• CPC Class Codes: F01D 5/14 Form or construction selecting particular materials, measures against erosion or corrosion F01D5/28
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F05D 2300/143 Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising a spar, the spar providing mechanical support for the article and comprising a cooling fluid delivery system, a top end, and a bottom end; a standoff structure attached to the spar, the standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, the spacing elements having first ends adjacent to the spar and second ends opposite to the first ends; a skin conformally surrounding the spar and the standoff structure, the skin comprising a top end and a bottom end, wherein the standoff structure separates the spar and the skin, wherein the plurality of spacing elements is disposed with an inner surface of the skin adjacent to the second ends of the spacing elements to form a plurality of plena between the spar and the skin, the plena in fluid communication with the cooling fluid delivery system, the skin comprising at least one metal selected from the group consisting of Rh, Pd, and Pt; and a base connecting the bottom end of the spar and the bottom end of the skin.

Claims

1. An article for use in a hot gas path of a gas turbine assembly, said article comprising:

a spar, said spar providing mechanical support for said article and comprising a cooling fluid delivery system, a top end, and a bottom end;

a standoff structure attached to said spar, said standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, said spacing elements having first ends adjacent to said spar and second ends opposite to said first ends;

a skin conformally surrounding said spar and said standoff structure, said skin comprising a top end and a bottom end, wherein said standoff structure separates said spar and said skin, wherein said plurality of spacing elements is disposed with an inner surface of said skin adjacent to said second ends of said spacing elements to form a plurality of plena between said spar and said skin, said plena in fluid communication with said cooling fluid delivery system, said skin comprising at least one metal selected from the group consisting of Rh, Pd, and Pt; and

a base connecting said bottom end of said spar and said bottom end of said skin.

2. The article of claim 1, further comprising a thermal harrier coating disposed on said skin.

3. The article of claim 2, wherein said thermal barrier coating comprises yttria-stabilized zirconia.

4. The article of claim 2, wherein said thermal barrier coating comprises a columnar microstructure.

5. The article of claim 2, wherein said thermal barrier coating has a thickness in the range from about 0.1 mm to about 0.5 mm.

6. The article of claim 5, wherein said thickness of said thermal barrier coating is in the range from about 0.1 mm to about 0.3 mm.

7. The article of claim 1, wherein said spar comprises at least one of a ceramic, a superalloy, a silicide-based composite, and a titanium aluminide.

8. The article of claim 7, wherein said composite comprises at least one of a molybdenum-base silicide, a niobium-base silicide, and combinations thereof.

9. The article of claim 7, wherein said ceramic comprises a ceramic matrix composite.

10. The article of claim 9, wherein said composite comprises silicon carbide.

11. The article of claim 7, wherein said superalloy comprises a nickel-based superalloy.

12. The article of claim 11, wherein said nickel-based superalloy comprises a directionally solidified alloy.

13. The article of claim 12, wherein said superalloy comprises a directionally solidified eutectic alloy.

14. The article of claim 11, wherein said nickel-based superalloy comprises a single crystal.

15. The article of claim 1, wherein said spar has a thickness in the range from about 0.5 mm to about 5 mm.

16. The article of claim 15, wherein said thickness of said spar is in the range from about 0.5 mm to about 3 mm.

17. The article of claim 1, wherein said cooling fluid delivery system comprises a plurality of cooling holes.

18. The article of claim 1, wherein said cooling fluid delivery system comprises a plurality of grooves running from said top end to said bottom end of said spar.

19. The article of claim 1, further comprising an oxidation-resistant coating disposed on said spar.

20. The article of claim 19, wherein said oxidation-resistant coating comprises at least one of a platinum-nickel aluminide, a nickel aluminide, and a MCrAlY material, wherein M is at least one of Ni, Fe, and Co.

21. The article of claim 19, wherein said oxidation-resistant coating has a thickness in the range from about 5 to about 50 μ

m.

22. The article of claim 1, wherein said spar further comprises an outer surface facing said skin, and wherein a thermal barrier coating is disposed on said outer surface of said spar.

23. The article of claim 22, wherein said thermal barrier coating comprises yttria-stabilized zirconia.

24. The article of claim 22, wherein said thermal barrier coating has a thickness in the range from about 0.05 mm to about 0.2 mm.

25. The article of claim 1, wherein said standoff structure is integral with said spar.

26. The article of claim 1, wherein said spacing elements have a height in the range from about 0.2 to about 3 mm.

27. The article of claim 26, wherein said spacing elements have substantially equal heights.

28. The article of claim 26, wherein said plurality of spacing elements comprises at least one of right rectangular prisms and right circular cylinders.

29. The article of claim 26, wherein said spacing elements are tapered.

30. The article of claim 1, wherein said standoff structure comprises at least one of a ceramic, a superalloy, a silicide-based composite, and a titanium aluminide.

31. The article of claim 30, wherein said ceramic comprises a ceramic matrix composite.

32. The article of claim 31, wherein said composite comprises silicon carbide.

33. The article of claim 30, wherein said superalloy is a nickel-based superalloy.

34. The article of claim 33, wherein said nickel-based superalloy comprises a directionally solidified alloy.

35. The article of claim 34, wherein said superalloy comprises a directionally solidified eutectic alloy.

36. The article of claim 33, wherein said nickel-based superalloy comprises a single crystal.

37. The article of claim 1, wherein said spacing elements comprise a gradient in material composition, said gradient extending from said first ends adjacent to said spar to said second ends adjacent to said skin.

38. The article of claim 1, wherein said standoff structure further comprises a diffusion barrier layer disposed at said second ends of said spacing elements.

39. The article of claim 38, wherein said diffusion barrier layer comprises ruthenium.

40. The article of claim 38, wherein said diffusion barrier layer has a thickness in the range from about 5 to about 50 μ

m.

41. The article of claim 1, wherein said skin comprises a single piece of said metal.

42. The article of claim 1, wherein said skin comprises at least about 80 atomic percent of said metal.

43. The article of claim 1, wherein said skin has a thickness in the range from about 0.1 mm to about 0.5 mm.

44. The article of claim 43, wherein said thickness of said skin is in the range from about 0.1 to about 0.3 mm.

45. The article of claim 1, wherein said skin further comprises a plurality of cooling holes in fluid communication with said plena.

46. The article of claim 45, wherein said cooling holes of said skin have diameters in the range from about 0.1 mm to about 0.75 mm.

47. The article of claim 45, wherein said plurality of cooling holes comprises a first group of cooling holes with diameters having a first value, and a second group of cooling holes with diameters having a second value.

48. The article of claim 1, wherein said skin further comprises a weld joint joining a first end of said skin to said inner surface of said skin to form an enclosure around said spar.

49. The article of claim 1, wherein said skin further comprises at least one metallurgical joint connecting said skin to said standoff structure.

50. The article of claim 49, wherein said metallurgical joint comprises at least one of a weld joint, a braze joint, and a diffusion bond joint.

51. The article of claim 1, wherein said article comprises a turbine airfoil.

52. The article of claim 51, wherein said base comprises a platform of said airfoil.

53. The article of claim 1, wherein said base comprises a superalloy.

54. The article of claim 53, wherein said superalloy comprises a nickel-based superalloy.

55. The article of claim 1, further comprising a mechanical joint attaching said spar to said base.

56. The article of claim 1, further comprising at least one of a weld joint, a braze joint, and a diffusion bond joint attaching said spar to said base.

57. The article of claim 1, further comprising a retainer interposed between said skin and said spar, wherein said retainer is connected to said skin by at least one of a weld joint, a braze joint, and a diffusion bond joint.

58. A turbine blade for use in a hot gas path of a gas turbine assembly, said turbine blade comprising:

a spar, said spar providing mechanical support for said airfoil and comprising a plurality of cooling holes;

a standoff structure integral with said spar, said standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, said spacing elements having first ends adjacent to said spar and second ends opposite to said first ends;

a skin comprising inner and outer surfaces, said skin conformally surrounding said spar and said standoff structure, wherein said standoff structure separates said spar and said skin, wherein said plurality of spacing elements are disposed with said inner surface of said skin adjacent to said second ends of said spacing elements to form a plurality of plena between said spar and said skin, said plena in fluid communication with said cooling holes of said spar, said skin comprising at least 80 atomic percent of a metal selected from the group consisting of Rh, Pd, Pt, and mixtures thereof, said skin further comprising a plurality of cooling holes in fluid communication with said plena;

a base connecting said spar and said skin; and

a thermal barrier coating comprising yttria-stabilized zirconia disposed on said outer surface of said skin.

59. A metallic skin for an article located in the hot gas path of a gas turbine assembly, said skin comprising:

a free-standing sheet comprising, in an amount of at least about 80 atomic percent, at least one metal selected from the group consisting of Rh, Pd, and Pt;

wherein said sheet has a shape adapted to conformally surround a support structure of said article.

60. The metallic skin of claim 59, wherein said skin comprises a single piece of metal.

61. The metallic skin of claim 59, wherein said skin has a thickness in the range from about 0.1 mm to about 0.5 mm.

62. The metallic skin of claim 61, wherein said thickness of said skin is in the range from about 0.1 to about 0.3 mm.

63. The metallic skin of claim 59, wherein said skin further comprises a plurality of cooling holes.

64. The metallic skin of claim 63, wherein said cooling holes have diameters in the range from about 0.1 mm to about 0.75 mm.

65. The metallic skin of claim 63, wherein said plurality of cooling holes comprises a first group of cooling holes with diameters having a first value, and a second of cooling holes with diameters having a second value.

66. The skin of claim 59, wherein said skin further comprises a weld joint joining a first end of said skin to a surface of said skin to form an enclosure.

67. The skin of claim 59, wherein said shape comprises a turbine airfoil shape.

68. A metallic skin for an airfoil in the hot gas path of a gas turbine assembly, said skin comprising:

a free-standing sheet comprising, in an amount of at least about 80 atomic percent, at least one metal selected from the group consisting of Rh, Pd, and Pt

wherein said sheet has a shape adapted to conformally surround a support structure of said airfoil.

69. A method for making an article for use in a hot gas path of a gas turbine assembly, said method comprising:

providing a spar, said spar providing mechanical support for said article and comprising a cooling fluid delivery system, a top end, and a bottom end;

attaching a standoff structure to said spar, said standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, said spacing elements having first ends adjacent to said spar and second ends opposite to said first ends;

providing a skin conformally surrounding said spar and said standoff structure, said skin comprising a top end and a bottom end, wherein said standoff structure separates said spar and said skin, wherein said plurality of spacing elements is disposed with an inner surface of said skin adjacent to said second ends of said spacing elements to form a plurality of plena between said spar and said skin, said plena in fluid communication with said cooling fluid delivery system, said skin comprising at least one metal selected from the group consisting of Rh, Pd, and Pt;

providing a base for said article; and

joining said bottom end of said spar and said bottom end of said skin to said base.

70. The method of claim 69, further comprising disposing a thermal barrier coating on said skin.

71. The method of claim 70, wherein said thermal barrier coating comprises yttria-stabilized zirconia.

72. The method of claim 70, wherein said thermal barrier coating comprises a columnar microstructure.

73. The method of claim 70, wherein said thermal barrier coating has a thickness in the range from about 0.1 mm to about 0.5 mm.

74. The method of claim 73, wherein said thickness of said thermal barrier coating is in the range from about 0.1 mm to about 0.3 mm.

75. The method of claim 69, wherein providing said spar comprises providing at least one of a ceramic, a superalloy, a silicide-based composite, and a titanium aluminide.

76. The method of claim 75, wherein said ceramic comprises a ceramic matrix composite.

77. The method of claim 75, wherein said superalloy comprises a nickel-based superalloy.

78. The method of claim 77, wherein said nickel-based superalloy comprises one of a directionally solidified alloy and a single-crystal alloy.

79. The method of claim 78, wherein said superalloy comprises a directionally solidified eutectic alloy.

80. The method of claim 69, wherein providing said spar comprises providing a spar having a thickness in the range from about 0.5 mm to about 5 mm.

81. The method of claim 80, wherein said thickness of said spar is in the range from about 0.5 mm to about 3 mm.

82. The method of claim 69, wherein said cooling fluid delivery system of said spar comprises at least one of a plurality of cooling holes and a plurality of grooves running from said top end to said bottom end of said spar.

83. The method of claim 69, further comprising disposing an oxidation-resistant coating on said spar.

84. The method of claim 83, wherein said oxidation-resistant coating comprises at least one of a platinum-nickel aluminide, a nickel aluminide, and a MCrAlY material, wherein M is at least one of Ni, Fe, and Co.

85. The method of claim 83, wherein said oxidation-resistant coating has a thickness in the range from about 5 to about 50 μ

m.

86. The method of claim 69, further comprising disposing a thermal barrier coating on an outer surface of said spar, wherein said outer surface faces said skin.

87. The method of claim 69, wherein attaching said standoff structure comprises forming said standoff structure integrally with said spar.

88. The method of claim 69, wherein said spacing elements have a height in the range from about 0.2 to about 3 mm.

89. The method of claim 69, wherein said standoff structure comprises at least one of a ceramic, a superalloy, a silicide-based composite, and a titanium aluminide.

90. The method of claim 89, wherein said ceramic comprises a ceramic matrix composite.

91. The method of claim 89, wherein said superalloy comprises a nickel-based superalloy.

92. The method of claim 91, wherein said nickel-based superalloy comprises one of a directionally solidified alloy and a single crystal alloy.

93. The method of claim 91, wherein said superalloy comprises a directionally solidified eutectic alloy.

94. The method of claim 69, further comprising disposing a diffusion barrier layer at said second ends of said spacing elements.

95. The method of claim 69, wherein providing said skin comprises providing a single piece of said metal.

96. The method of claim 69, wherein said skin comprises at least about 80 atomic percent of said metal.

97. The method of claim 69, wherein said skin has a thickness in the range from about 0.1 mm to about 0.5 mm.

98. The method of claim 97, wherein said thickness of said skin is in the range from about 0.1 to about 0.3 mm.

99. The method of claim 69, wherein said skin further comprises a plurality of cooling holes in fluid communication with said plena.

100. The method of claim 99, wherein said cooling holes of said skin have diameters in the range from about 0.1 mm to about 0.75 mm.

101. The method of claim 69, further comprising joining a first end of said skin to said inner surface of said skin to form an enclosure around said spar.

102. The method of claim 69, further comprising forming at least one metallurgical joint connecting said skin to said standoff structure.

103. The method of claim 102, wherein forming comprises at least one of welding, brazing, and diffusion bonding.

104. The method of claim 69, wherein said article made by said method comprises a turbine airfoil.

105. The method of claim 104, wherein providing said base comprises providing a platform of said airfoil.

106. The method of claim 69, wherein joining comprises at least one of welding, brazing, and diffusion bonding.

107. A method for making a turbine blade for use in a hot gas path of a gas turbine assembly, said method comprising:

providing a spar, said spar providing mechanical support for said turbine blade and comprising a plurality of cooling holes, a top end, and a bottom end;

attaching a standoff structure to said spar, said standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, said spacing elements having first ends adjacent to said spar and second ends opposite to said first ends;

providing a skin conformally surrounding said spar and said standoff structure, said skin comprising inner and outer surfaces, wherein said standoff structure separates said spar and said skin, wherein said plurality of spacing elements is disposed with said inner surface of said skin adjacent to said second ends of said spacing elements to form a plurality of plena between said spar and said skin, said plena in fluid communication with said cooling holes, said skin further comprising at least 80 atomic percent of a metal selected from the group consisting of Rh, Pd, Pt, and mixtures thereof, said skin further comprising a plurality of cooling holes in fluid communication with said plena;

providing a base for said turbine blade;

joining said bottom end of said spar and said bottom end of said skin to said base; and

disposing a thermal barrier coating on said outer surface of said skin.