US 7,604,456 B2 · Vane shroud through-flow platform cover

Abstract

A turbine vane array (10) for a combustion assembly (8) in a combustion turbine engine. The vane array (10) includes a plurality of stationary vane assemblies (12), each vane assembly (12) including at least one airfoil (24) and inner and outer shroud segments (26, 28) attached to opposing ends of the airfoil (24). The inner and outer shroud segments (26, 28) each include an inner face (34, 36) facing toward a gas path (13) extending through the vane array (10). A removable cover structure may be provided on the inner faces (34, 36) of the inner and outer shroud segments (26, 28). The cover structure may include removably attached insert elements (72, 72′) that are positioned on the inner faces (34, 36) extending between upstream edges (44) and downstream edges (46) of the shroud segments (26, 28) and extending between adjacent airfoils (24).

Claims20

Dependent claims

A combustion turbine vane array comprising:

a plurality of elongated airfoils including at least a first airfoil and a second airfoil located adjacent to each other;
a shroud portion defining an inner face extending laterally from said first airfoil to said second airfoil and extending longitudinally from a leading edge of said first airfoil to a trailing edge of said first airfoil, said inner face defining an annular boundary of a gas path directing a flow of a working gas through a turbine casing, and said inner face comprising a face surface facing radially inwardly toward the gas path, wherein said shroud portion forms an integral structure with said first airfoil;
and
an insert element extending from said first airfoil to said second airfoil and positioned in engagement on said face surface of said inner face of said shroud portion between said first and second airfoils, and defining a surface for contacting the working gas passing through said turbine vane array and an opposite surface engaging said inner face from said leading edge of said first airfoil to said trailing edge of said first airfoil.

1 more element

A combustion turbine vane array comprising:

structure arranged annularly around a turbine casing and defining a gas path, and including at least a first airfoil;
said structure comprising a shroud portion including an inner face comprising a face surface facing radially inwardly into said gas path, said shroud portion comprising a shroud segment coupled to said first airfoil adjacent a base portion of said first airfoil and extending laterally outwardly from junctions with said first airfoil at opposing sides of said first airfoil to respective lateral edges located in laterally spaced relation to said junctions and said shroud portion extending longitudinally from a leading edge of said first airfoil to a trailing edge of said first airfoil;
and
a cover structure removably engaged on said inner face of said shroud portion from said leading edge of said first airfoil to said trailing edge of said first airfoil and extending along said face surface of said inner face from at least one of said junctions at least to a respective lateral edge and along at least one side of said first airfoil adjacent said base portion.

1 more element

A method of maintaining a vane array located within a combustion turbine engine, comprising the steps of:

providing structure arranged annularly around a turbine casing and defining a gas path, said structure including a plurality of airfoils and a shroud portion spanning between said airfoils and having an inner face comprising a face surface facing radially into said gas path, said shroud portion being coupled to said airfoils adjacent a base portion of each of said airfoils and extending laterally outwardly from junctions between said shroud portion and each said airfoil at opposing sides of said airfoils and said shroud portion extending longitudinally from a leading edge of a first one of said airfoils to a trailing edge of said first one of said airfoils;
providing a cover structure positioned on and engaging said inner face of said shroud portion from said leading edge of said first one of said airfoils to said trailing edge of said first one of said airfoils and extending along said face surface of said inner face from at least one of said junctions located along at least one side of said airfoil adjacent said base portion to one of said junctions located along a side of an adjacent airfoil;
removing said cover structure from said inner face of said shroud portion;
and
positioning a replacement cover structure on said inner face of said shroud portion.

2 more elements

Dependencies are inferred from the claim text.

Vane shroud through-flow platform cover

Life of this patent

Vane shroud through-flow platform cover

Life of this patent

Abstract

Claims20