Sealing ring

A sealing ring adapted for insertion into a circumferential groove of a gas turbine engine, the circumferential groove being defined between two static elements of a compressor stage or a turbine stage of the gas turbine engine, the sealing ring having a substantially annular shape, and comprising:

• two radial surfaces, namely an inner radial surface and an outer radial surface;
• and
• two side surfaces extending between the inner radial surface and the outer radial surface;
• wherein one of the radial surfaces is configured for abutting against a corresponding first groove surface or second groove surface of the circumferential groove arranged in the gas turbine engine;
• wherein one of the side surfaces is configured for abutting against a corresponding third groove surface of the circumferential groove arranged in the gas turbine engine;
• wherein:
• at least a portion of the radial surface configured for abutting against the corresponding first or second groove surface, and
• at least a portion of the side surface configured for abutting against the corresponding third groove surface,
• are coated with a physical vapour deposited (PVD) coating;
• wherein the PVD coating comprises a passivation layer, and
• wherein the passivation layer comprises at least one component configured for passivating the corresponding surface of the sealing ring;
• and
• wherein the sealing ring is configured to be arranged into the circumferential groove sealing a joint between the static elements;
• wherein the component of the passivation layer configured for passivating the corresponding surface of the sealing ring is an alloyed aluminium oxide Al(M)O, wherein (M) is a metal;
• and
• wherein:
• i) the first groove surface and the third groove surfaces are part of the first element and the second groove surface is part of the second element;
• or
• ii) the second groove surface and the third groove surfaces are part of the first element and the first groove surface is part of the second element.