| abstract |
The present invention provides a rotor-starter assembly for a gas turbine engine, the assembly comprising a rotor (2) having a layer of ceramic material (8) that forms an abrasive coating deposited on a chip, wherein the layer is mainly composed of zirconia A starter 4 provided with a porosity ratio of 15% or less, arranged around the rotor and forming a wear coating, facing the tip of the rotor, wherein the layer consists mainly of zirconia It is an assembly having a void ratio in the range of 20% to 50% and a pore size of 50 μm or less. |