In-line removable heat shield for a turbomachine suspension yoke

1. A heat shield device for a yoke suspending an engine from an aircraft, the device comprising:

a panel fixed to and surrounding the yoke, the panel extending radially inward towards an axis of the engine, the panel having first and second lateral faces; and

a component which is fixed to the engine and extending at least in part radially inward towards the axis of the engine, the component comprising a groove shaped in such a way that a lower end of the panel can be inserted into the groove,

wherein the component includes an inner branch, an outer branch, and an axial branch therebetween, the groove being delimited by the inner branch, the outer branch, and the axial branch, and

wherein the lower end of the panel and the groove are configured in such a manner to form a barrier against fire spread with at least a double chicane configuration for the heat shield.

2. The device according to claim 1 , wherein the inner and outer branches extend parallel to each other.

3. The device according to claim 1 , wherein the groove has a width greater than that of a part of the panel so as to allow the panel to move laterally within the groove.

4. The device according to claim 1 , wherein a space in between two ribs of the panel has a width greater than that of the branches of the component, so as to allow the panel to move laterally with respect to the component.

5. The device according to claim 1 , shaped to surround the yoke by four parallel walls extending radially so as to adapt to a shape of a turbomachine casing, in which device the component is formed of two partially cylindrical elements equipped with an attachment device which attaches the partially cylindrical elements to a turbomachine casing flange and of two rectilinear elements equipped with fixing devices which fix the rectilinear elements to the partially cylindrical elements.

6. The device according to claim 5 , wherein the fixing devices are of a tenon type fitting into mortices made in the partially cylindrical elements.

7. The device according to claim 5 , wherein the partially cylindrical elements have a shape of a numeral 4.

8. The device according to claim 5 , wherein the rectilinear elements have a shape of a U, lower ends of the panel of the device being inserted between branches of the U.

9. A turbomachine comprising:

a yoke attaching the turbomachine to an aircraft, which is positioned on at least one of an intermediate casing or an exhaust casing of the turbomachine; and

a heat shield device according to claim 1 , for the yoke.

10. The device according to claim 1 , wherein the lower end of the panel includes first and second radial ribs which radially extend the first and second lateral faces of the panel, respectively, and presents a space between the first and second radial ribs.

11. The device according to claim 10 , wherein the first radial rib is inserted into the groove, and the inner branch occupies the space, and the outer branch is outside the space.

12. The device according to claim 1 , wherein the inner branch bears and espouses the shape of a flange of a casing of the engine and the outer branch extends radially so as to form a lateral heat shield and barrier against fire.

13. The device according to claim 2 , wherein the inner branch bears and espouses the shape of a flange of a casing of the engine and the outer branch extends radially so as to form a lateral heat shield and barrier against fire.

14. A module comprising:

an engine casing,

a yoke for suspending and fixing the engine casing from an aircraft,

a heat shield device comprising:

a panel fixed to and surrounding the yoke and extending radially inward towards an axis of the engine, the panel having first and second lateral faces; and

a component which is fixed to the engine casing and comprising a groove shaped in such a way that a lower end of the panel can be inserted into the groove,

wherein the component includes an inner branch, an outer branch, and an axial branch therebetween, the groove being delimited by the inner branch, the outer branch, and the axial branch,

wherein the lower end of the panel includes first and second radial ribs which radially extend the first and second lateral faces of the panel, respectively, and presents a space between the first and second radial ribs,

wherein one of the first and second radial rib is inserted into the groove and the other first and second radial rib is outside the groove.