Blade or vane for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsRoger S. DUFFIN, Gabriel GONZALEZ-GUTIERREZ
Life of this patent
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Abstract
A blade or vane for a gas turbine engine comprising a pressure surface and a suction surface. The pressure surface or the suction surface comprises a roughness zone which is configured to provide greater flow resistance in a direction along the blade or vane than in a direction across the blade or vane.
Claims20
A blade or vane for a gas turbine engine comprising a pressure surface and a suction surface, wherein at least one of the pressure surface and the suction surface comprises a roughness zone which is configured to provide greater flow resistance in a direction (y) along the blade or vane than in a direction (x) across the blade or vane.
A method of modifying a blade or vane for a gas turbine engine comprising forming a roughness zone on a suction surface or pressure surface of the blade or vane, the roughness zone being configured to provide greater flow resistance in a direction (y) along the blade than in a direction (x) across the blade or vane.
Dependencies are inferred from the claim text.