Stationary flowpath components for gas turbine engines
AssigneeGeneral Electric Company
InventorVictor H.S Correia
Life of this patent
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Abstract
Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.
Claims23
In a gas turbine engine having a plurality of circumferentially spaced airfoils through which a gas flow passes, said gas flow defining a flow line, a stationary flowpath component having at least one circumferential edge defining a non-linear curvature.
In a gas turbine engine having a plurality of circumferentially spaced airfoils through which a gas flow passes, said gas flow defining a flow line, a plurality circumferentially arranged nozzle segments, wherein each one of said nozzle segments includes at least one circumferential edge defining a curvature that matches the curvature of said flow line.
In a gas turbine engine having a plurality of circumferentially spaced airfoils through which a gas flow passes, said gas flow defining a flow line, a plurality circumferentially arranged shrouds, wherein each one of said shrouds includes at least one circumferential edge defining a curvature that matches the curvature of said flow line.
In a gas turbine engine having a plurality circumferentially arranged stationary flowpath components, a flexible seal member disposed between two adjacent stationary flowpath components, said flexible seal member comprising:
- a plurality of segments;
- and
- means for rotatively joining said segments together.
Dependencies are inferred from the claim text.