A fan assembly (13) of a gas turbine engine (10), the fan assembly (13) comprises an array of radially extending blades (32) defining gaps therebetween and an annulus filler (40) located within at least one gap. The annulus filler (40) comprises at least two individual bodies (41, 42) arranged circumferentially adjacent one another with at least one adjacent a blade (32), one of the bodies (42) comprises a flexible wall (50, 51) arranged to centrifuge outwardly against the other body (41) thereby urging both bodies against the blades (32) and securing them during engine operation.
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