Abstract: The invention relates to a protection dish (32) for a counterbore formed in an aircraft mechanical part, said protection dish (32) having an axial cross-section about an axis (A) having substantially the shape of a U, and comprising a substantially annular wall (34) of axis (A) and a substantially cylindrical rim (36) of axis (A) connected to an outer periphery of said substantially annular wall (34). The invention is characterised in that said dish (32) is configured to be deformed in response to an axial stress (F) of a determined intensity applied on the substantially annular wall (34) thereof from a first state, wherein the substantially cylindrical rim (36) has a first transverse dimension (E) relative to axis (A), to a second state, wherein the substantially annular wall (34) being deformed, the cylindrical rim (36) has a second transverse dimension (E?) relative to the axis (A) that is greater than the first transverse dimension (E) along a transverse direction (T) determined relative to axis (A).

Abstract: A seal (13) closing off a clearance (9) between one end in the form of a bowl (7) of an arm (4) and a circular shell (1) of a turbomachine is compressed between the rim (8) of the bowl by a support (14) distinct from the platform (10) delimiting the gas flow stream (5) and retained by screws (11) already present to fix the platform to the shell (1). The layout is lighter in weight and the resistance of seal does not depend on the platform (10) exposed to damage.

Abstract: A flange of a blade root platform is separated from an adjacent edge of the blade by a groove that prevents direct transmission of forces created by the bolted attachment of the platform flange to the adjacent part of the blade and reduces stress concentrations.

Abstract: The invention relates to a protection dish (32) for a counterbore formed in an aircraft mechanical part, said protection dish (32) having an axial cross-section about an axis (A) having substantially the shape of a U, and comprising a substantially annular wall (34) of axis (A) and a substantially cylindrical rim (36) of axis (A) connected to an outer periphery of said substantially annular wall (34). characterised in that said dish (32) is configured to be deformed in response to an axial stress (F) of a determined intensity applied on the substantially annular wall (34) thereof from a first state, wherein the substantially cylindrical rim (36) has a first transverse dimension (E) relative to axis (A), to a second state, wherein the substantially annular wall (34) being deformed, the cylindrical rim (36) has a second transverse dimension (E?) relative to the axis (A) that is greater than the first transverse dimension (E) along a transverse direction (T) determined relative to axis (A).

Abstract: A seal (13) closing off a clearance (9) between one end in the form of a bowl (7) of an arm (4) and a circular shell (1) of a turbomachine is compressed between the rim (8) of the bowl by a support (14) distinct from the platform (10) delimiting the gas flow stream (5) and retained by screws (11) already present to fix the platform to the shell (1). The layout is lighter in weight and the resistance of seal does not depend on the platform (10) exposed to damage.

Abstract: The flange (11) of a blade root platform (10) is separated from an adjacent edge (31) of the blade (4) by a groove (18), that prevents direct transmission of forces created by the bolted attachment of the platform flange (11) to the adjacent part of the blade (4) and reduces stress concentrations.