Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
AssigneesRolls-Royce Deutschland Ltd & Co KG, Formtech GmbH
InventorsKarl Schreiber, Werner Beck
Life of this patent
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Abstract
A compressor blade 1 of a gas-turbine engine has a flow-exposed leading edge 2. A component 3, made of wear-resistant material and featuring a higher erosive wear resistance than the base material, is attached to at least part of a length of the leading edge 2 The component 3 forming the flow-exposed leading edge 2 is strip-shaped, has an essentially rectangular cross-section and, with reference to a sectional plane perpendicular to the radial direction, is arranged only on an inflow side of the compressor blade profile in a partial area of a sectional surface of the inflow area.
Claims20
A blade of a gas-turbine engine, comprising:
- a leading edge;
- a component attached along at least part of a length of the leading edge to form a flow-exposed portion of the leading edge, the component made of wear-resistant material having a higher erosive wear resistance than a base material of the leading edge, the component being strip shaped, having essentially rectangular cross-section and, with reference to a sectional plane perpendicular to a radial direction, is arranged only on an inflow side of a profile of the blade in a partial area of a sectional surface of an inflow area;
- wherein the component is embedded in a central portion of the leading edge and at least partially surrounded on both a pressure side and a suction side at the leading edge by the blade.
Dependencies are inferred from the claim text.