A metallic heat-insulating tile for a combustion chamber of a gas turbine engine, the heat-insulating tile comprising: a shield plate, having a first face to be exposed in use to hot gas flowing through a combustion chamber of a gas turbine engine, a second face opposite to the first face; an aft surface and an aft edge between the first face of the shield plate and the aft surface; an outer rim, extending from the shield plate in a direction opposite to the first face thereof and having a first side portion, a second side portion, opposite to the first side portion, and an aft portion; a plurality of seal holes (30, 31) in the outer rim; wherein: the first face of the shield plate is configured as a portion of a surface of revolution about a central axis; and the seal holes (30, 31) include a plurality of side seal holes in the first side portion and in the second side portion of the outer rim and a plurality of aft seal holes in the aft portion of the outer rim, each side seal hole having a respective side hole axis and each aft seal hole having a respective aft hole axis; characterized in that: for each side seal hole, the respective side hole axis forms a first angle (α) of ± 15° with a first reference plane and a projection of the respective side hole axis on the first reference plane forms a second angle (β) of ± 30° with a second reference plane perpendicular to the central axis; the aft hole axes of the aft seal holes form respective third angles (y) between 5° and 45° with a direction parallel to the central axis; the first reference plane is parallel to the central axis and perpendicular to a median plane of the first face of the shield plate that includes the central axis; the aft edge is rounded with first curvature radius and the aft surface of the heat-insulating tile has a first concave region and a second concave region, separated by a ridge, all extending parallel to the aft edge between the first side portion and the second side portion of the outer rim. a shield plate, having a first face to be exposed in use to hot gas flowing through a combustion chamber of a gas turbine engine, a second face opposite to the first face; an aft surface and an aft edge between the first face of the shield plate and the aft surface; an outer rim, extending from the shield plate in a direction opposite to the first face thereof and having a first side portion, a second side portion, opposite to the first side portion, and an aft portion; a plurality of seal holes (30, 31) in the outer rim; wherein: the first face of the shield plate is configured as a portion of a surface of revolution about a central axis; and the seal holes (30, 31) include a plurality of side seal holes in the first side portion and in the second side portion of the outer rim and a plurality of aft seal holes in the aft portion of the outer rim, each side seal hole having a respective side hole axis and each aft seal hole having a respective aft hole axis; characterized in that: for each side seal hole, the respective side hole axis forms a first angle (α) of ± 15° with a first reference plane and a projection of the respective side hole axis on the first reference plane forms a second angle (β) of ± 30° with a second reference plane perpendicular to the central axis; the aft hole axes of the aft seal holes form respective third angles (y) between 5° and 45° with a direction parallel to the central axis; the first reference plane is parallel to the central axis and perpendicular to a median plane of the first face of the shield plate that includes the central axis; the aft edge is rounded with first curvature radius and the aft surface of the heat-insulating tile has a first concave region and a second concave region, separated by a ridge, all extending parallel to the aft edge between the first side portion and the second side portion of the outer rim. the first face of the shield plate is configured as a portion of a surface of revolution about a central axis; and the seal holes (30, 31) include a plurality of side seal holes in the first side portion and in the second side portion of the outer rim and a plurality of aft seal holes in the aft portion of the outer rim, each side seal hole having a respective side hole axis and each aft seal hole having a respective aft hole axis; characterized in that: for each side seal hole, the respective side hole axis forms a first angle (α) of ± 15° with a first reference plane and a projection of the respective side hole axis on the first reference plane forms a second angle (β) of ± 30° with a second reference plane perpendicular to the central axis; the aft hole axes of the aft seal holes form respective third angles (y) between 5° and 45° with a direction parallel to the central axis; for each side seal hole, the respective side hole axis forms a first angle (α) of ± 15° with a first reference plane and a projection of the respective side hole axis on the first reference plane forms a second angle (β) of ± 30° with a second reference plane perpendicular to the central axis; the first reference plane is parallel to the central axis and perpendicular to a median plane of the first face of the shield plate that includes the central axis; the aft edge is rounded with first curvature radius and the aft surface of the heat-insulating tile has a first concave region and a second concave region, separated by a ridge, all extending parallel to the aft edge between the first side portion and the second side portion of the outer rim.