Interior configuration for turbine rotor blade
AssigneeGeneral Electric Company
InventorsHarrish Bommanakatte, Jalindar Appa Walunj, Anthony Louis Giglio, Jason Douglas Herzlinger
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Abstract
An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.
Claims22
An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine, the interior cooling configuration comprising:
- a first flow passage and a second flow passage that comprise a side-by-side configuration for a segment;
- and
- multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage, wherein the crossover passages are staggered.
An interior cooling configuration formed within an airfoil of a rotor blade of a combustion turbine engine, the interior cooling configuration comprising:
- a first flow passage and a second flow passage extending radially and in parallel within a segment between an inboard position and an outboard position;
- and
- multiple lateral crossover passages extending linearly between and fluidly connecting the first flow passage to the second flow passage, the crossover passages being spaced at regular radial intervals within the segment;
- wherein a reference plane bisects the first flow passage and the second flow passage;
- wherein the crossover passages are staggered relative to the reference plane.
Dependencies are inferred from the claim text.