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US 11,359,496 B2Granted
Coolant channel
AssigneeROLLS-ROYCE plc
InventorAdrian L. Harding
Life of this patent
Estimating the term…
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.
Claims10
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,
- wherein the component is an aerofoil blade or vane comprising an aerofoil leading edge, an aerofoil trailing edge and an aerofoil suction side opposite an aerofoil pressure side, wherein the first wall is provided on the aerofoil suction side, the second wall is adjacent to the first wall, and the first wall and the second wall define the coolant channel to cool the aerofoil suction side of the component, and
- wherein the first rib is itself bifurcated into two radially separated sections that both extend to the end of the coolant channel in the coolant flow direction.
3 more elements
Dependencies are inferred from the claim text.