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US 2011/0217159 A1Published application
Preferential cooling of gas turbine nozzles
AssigneeGeneral Electric Company
InventorsKevin Weston McMahan, Joseph V. Citeno
Life of this patent
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Abstract
Turbine nozzle assemblies include a plurality of circumferentially spaced first components and second components, which are designed to provide different amounts of cooling. The second components, which are generally aligned with an opening of transition pieces, are designed to provide more cooling than the first components, which are generally aligned with interfaces between the transition pieces.
Claims20
A turbine engine, comprising:
- a turbine nozzle assembly with a plurality of circumferentially spaced first components and second components;
- and
- a plurality of transition pieces each defining a hot gas path from a combustor to the turbine nozzle assembly;
- wherein the first components are generally aligned with interfaces between two transition pieces of the plurality of transition pieces, the second components are generally aligned with openings of individual transition pieces of the plurality of transition pieces, and the second components are configured to provide more cooling than the first components.
1 more element
A turbine engine, comprising:
- a turbine nozzle assembly with a plurality of circumferentially spaced vanes each extending between a plurality of band segments;
- a plurality of transition pieces each defining a hot gas path from a combustor to the turbine nozzle assembly;
- a first component comprising at least one vane of the plurality of circumferentially spaced vanes or at least one band segment of the plurality of band segments;
- and
- a second component comprising at least one vane of the plurality of the circumferentially spaced vanes or at least one band segment of the plurality of band segments, wherein the second component is disposed at or adjacent to an interface between two transition pieces of the plurality of transition pieces, and is configured to provide less cooling than the first component.
2 more elements
A turbine engine, comprising:
- a turbine nozzle assembly comprising:
- a first annular ring of inner band segments;
- a second annular ring of outer band segments disposed about the first annular ring;
- a plurality of first vanes extending between the first and second annular rings;
- and
- a plurality of second vanes extending between the first and second annular rings;
- a plurality of combustors;
- and
- a plurality of transition pieces each defining a hot gas path from a combustor of the plurality of combustors to the turbine nozzle assembly;
- wherein individual first vanes of the plurality of first vanes are generally aligned with interfaces between two transition pieces of the plurality the transition pieces, individual second vanes of the plurality of second vanes are generally aligned with the combustors, and the individual first vanes of the plurality of first vanes comprise fewer cooling holes than the individual second vanes of the plurality of second vanes.
7 more elements
Dependencies are inferred from the claim text.