Hybrid high temperature articles and method of making
First Claim
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.
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Accused Products
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.
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Citations
107 Claims
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1. An article for use in a hot gas path of a gas turbine assembly, said article comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40, 41, 42, 43, 44, 45, 46, 47, 48, 49, 50, 51, 52, 53, 54, 55, 56, 57)
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58. A turbine blade for use in a hot gas path of a gas turbine assembly, said turbine blade comprising:
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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.
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59. A metallic skin for an article located in the hot gas path of a gas turbine assembly, said skin comprising:
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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. - View Dependent Claims (60, 61, 62, 63, 64, 65, 66, 67)
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68. A metallic skin for an airfoil in the hot gas path of a gas turbine assembly, said skin comprising:
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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.
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69. A method for making an article for use in a hot gas path of a gas turbine assembly, said method comprising:
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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. - View Dependent Claims (70, 71, 72, 73, 74, 75, 76, 77, 78, 79, 80, 81, 82, 83, 84, 85, 86, 87, 88, 89, 90, 91, 92, 93, 94, 95, 96, 97, 98, 99, 100, 101, 102, 103, 104, 105, 106)
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107. A method for making a turbine blade for use in a hot gas path of a gas turbine assembly, said method comprising:
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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.
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Specification