Device for suspending a turbine engine from an airplane

1. A device for suspending a turbojet casing, the device comprising:

a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing, each lug having an inside face and an outside face; and

a protection piece for providing protection against wear mounted on each lug and that has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes,

wherein the protection piece includes first and second parallel walls, each of the parallel walls covering one of said faces of the lug, and a connection portion connecting the first and second parallel walls together, the connection portion covering a top of the lug,

wherein said first and second parallel walls extend over different radial extents, an extent of one of said first and second parallel walls covering the outside face of the lug being greater than an extent of the other of said first and second parallel walls that terminates radially short of the shouldered pin, and,

wherein said other of the first and second parallel walls includes a concave curved inside peripheral edge surrounding a portion of an annular rim of the orifice of the lug through which the shouldered pin passes.

2. A device according to claim 1 , wherein, on each lug, the protection piece includes a wall covering the outside face of the lug and includes an orifice for passing the shouldered pin, the orifice in the wall of the protection piece having a diameter that is less than the diameter of the shoulder of the pin.

3. A device according to claim 1 , wherein the connection portion includes a bottom wall of an annular groove of shape complementary to a shape of the top of the lug.

4. A device according to claim 3 , wherein the top of the lug has a circular portion on which the bottom wall of likewise circular shape is engaged, angular extents of the bottom wall and of the circular portion of the lug being identical.

5. A piece for protecting an outside face of a lug of a clevis in a suspension device according to claim 1 , the piece comprising first and second parallel walls connected together by a bottom wall in a shape of a sector of an annular groove, the first parallel wall having a circular orifice and the second parallel wall having no such orifice and being of a radial extent that is less than that of the first wall.

6. A protection piece according to claim 5 , made by stamping a metal sheet with a thickness of about 1 mm.

7. A device for suspending a turbojet casing, the device comprising:

a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing, each lug having an inside face, an outside face, and an intermediate portion extending between said inside and outside faces, said intermediate portion having, at a top section, a curved outline centered on an axis of said aligned orifices which are adapted for passing therethrough the shouldered pin; and

a protection piece for providing protection against wear mounted on each lug and that has the shouldered pin passing therethrough,

wherein said protection piece comprises two parallel walls and a connection portion extending therebetween having a curved outline complementary to said curved outline top section of the lug, and

wherein ends of the connection portion come into abutment on parts of said intermediate portion located apart from said top section, so that the protection piece is prevented from moving in rotation relative to the corresponding lug.

8. A device according to claim 7 , wherein the two walls of the protection piece extend over different radial extents, an extent of one of the walls covering the outside face of the lug being greater than an extent of the other of the walls that terminates radially short of the shouldered pin.

9. A device according to claim 8 , wherein the other wall includes a concave curved inside peripheral edge surrounding a portion of an annular rim of the orifice of the lug through which the shouldered pin passes.

10. A device for suspending a turbojet casing, the device comprising:

a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing, each lug having an inside face, an outside face, and an intermediate portion extending between said inside and outside faces, said intermediate portion having, at a top section, a curved outline centered on an axis of said aligned orifices which are adapted for passing therethrough the shouldered pin; and

a protection piece for providing protection against wear mounted on each lug and that has the shouldered pin passing therethrough,

wherein said protection piece comprises two parallel walls and a connection portion extending therebetween having a curved outline complementary to said curved outline top section of the lug,

wherein ends of the connection portion come into abutment on parts of said intermediate portion located apart from said top section, so that the protection piece is prevented from moving in rotation relative to the corresponding lug,

wherein the two parallel walls of the protection piece extends over different radial extents, an extent of one of said two parallel walls covering the outside face of the lug being greater than an extent of the other of said two parallel walls that terminates radially short of the shouldered pin, and

wherein said other of said two parallel walls includes a concave curved inside peripheral edge surrounding a portion of an annular rim of the orifice of the lug through which the shouldered pin passes.