Combustion turbine single airfoil stator vane structure
First Claim
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1. A one-piece cast stator structure for a fluid turbine, comprising:
- an inner shroud segment;
an outer shroud segment;
a single, generally hollow, airfoil-shaped stator vane having one wall with a concave outer face, and an opposite wall with a convex outer face, said vane having opposite radial ends integrally joining said shroud segments through an investment casting process;
said vane walls being of a given thickness throughout its hollow portion;
the wall thickness of at least one of said shroud segments, in the general vicinity of the intersection between said at least one shroud segment and the hollow wall portion of the vane, is of substantially reduced thickness relative to the wall thickness of said at least one shroud segment along its side margins, so as to provide a closer match in thickness between said vane wall given thickness and said reduced thickness than between said given thickness and said shroud side margin thickness;
upstream and downstream support rail means on the outer face of said outer shroud segment for connecting said stator sturcture to blade ring means;
means for securing said upstream rail means to said blade ring means to restrain relative movement in the circumferential and axial directions while permitting limited relative movement in the radial direction;
said blade ring means includes groove means receiving said downstream rail means, and said groove means and rail means are dimensioned to provide one clearance permitting limited relative movement therebetween in a radial direction; and
the downstream end of said outer shroud carrying said downstream rail has an arc on its portion facing said blade ring means of a shorter radius than the radius of said facing blade ring means to provide another clearance at the circumferential ends of said outer shroud in the order of two to three times larger than said one clearance.
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Abstract
A one-piece, investment cast stator structure is provided including inner and outer shrouds 14 and 12 with a hollow airfoil-shaped vane therebetween and with areas 34, 36, 42 and 44 in the vicinity of the intersections of the shrouds with the airfoil vane walls being of reduced thickness relative to the remainder of the shrouds to provide improved properties of the material in these areas to better respond to thermal stresses imposed on the structure.
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Citations
1 Claim
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1. A one-piece cast stator structure for a fluid turbine, comprising:
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an inner shroud segment; an outer shroud segment; a single, generally hollow, airfoil-shaped stator vane having one wall with a concave outer face, and an opposite wall with a convex outer face, said vane having opposite radial ends integrally joining said shroud segments through an investment casting process; said vane walls being of a given thickness throughout its hollow portion; the wall thickness of at least one of said shroud segments, in the general vicinity of the intersection between said at least one shroud segment and the hollow wall portion of the vane, is of substantially reduced thickness relative to the wall thickness of said at least one shroud segment along its side margins, so as to provide a closer match in thickness between said vane wall given thickness and said reduced thickness than between said given thickness and said shroud side margin thickness; upstream and downstream support rail means on the outer face of said outer shroud segment for connecting said stator sturcture to blade ring means; means for securing said upstream rail means to said blade ring means to restrain relative movement in the circumferential and axial directions while permitting limited relative movement in the radial direction; said blade ring means includes groove means receiving said downstream rail means, and said groove means and rail means are dimensioned to provide one clearance permitting limited relative movement therebetween in a radial direction; and the downstream end of said outer shroud carrying said downstream rail has an arc on its portion facing said blade ring means of a shorter radius than the radius of said facing blade ring means to provide another clearance at the circumferential ends of said outer shroud in the order of two to three times larger than said one clearance.
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Specification
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Current AssigneeSiemens Westinghouse Power Corporation
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Original AssigneeWestinghouse Electric Corporation (Paramount Global (f/k/a ViacomCBS Inc.))
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InventorsHultgren, Kent G.
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Primary Examiner(s)Jillions, John M.
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Assistant Examiner(s)NOT, DEFINED
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Application NumberUS06/345,125Time in Patent Office1,169 DaysField of Search415/189, 415/191, 415/200, 415/138, 415/139, 415/134, 415/135, 415/136, 415/190, 415/137, 415/187, 415/188, 415/193, 415/208, 416/241 RUS Class Current415/136CPC Class CodesF01D 9/02 Nozzles; Nozzle boxes; Stat...F01D 9/042 fixing blades to stators fi...
