A gas turbine engine having a component, the component comprising a ceramic matrix composite material, the ceramic matrix composite material comprising reinforcing fibers in a ceramic matrix material,
- an abradable seal being arranged on the component, the abradable seal being bonded to the component, the abradable seal comprising hollow aluminosilicate spheres having a diameter in the range 400 to 1800 microns and an aluminum phosphate matrix, the hollow aluminosilicate spheres being arranged in the aluminum phosphate matrix, the weight proportion of hollow aluminosilicate spheres being 30% to 50%.