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US 2020/0284153 A1Published application
Coolant channel
AssigneeROLLS-ROYCE plc
InventorAdrian L. HARDING
Life of this patent
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Abstract
A component for a gas turbine engine, comprising: first and second walls; a coolant channel defined by the space between the first and second walls; and a first rib extending between the first and second walls to the end of the coolant channel in a coolant flow direction, such that the coolant channel is bifurcated in the coolant flow direction.
Claims20
A component for a gas turbine engine, comprising:
- first and second walls;
- a coolant channel defined by the space between the first and second walls;
- and
- a first rib extending between the first and second walls to the end of the coolant channel in a coolant flow direction, such that the coolant channel is bifurcated in the coolant flow direction.
1 more element
Dependencies are inferred from the claim text.