Casing cover in a jet engine
View Patent ↗A casing cover for enclosing a casing in a jet engine is disclosed. The casing cover includes two coaxial shells arranged one inside the other and radial envelopes which connect the two coaxial shells. Radial arms of the casing extend inside the radial envelopes. The cover is fastened at its downstream end to a first element of the casing and axially abuts at its upstream end on a second element of the casing. In a free state, an axial dimension of the cover of less than the axial distance of the casing between the point where the first element of the casing is fastened to the downstream end of the cover and the point where the second element of the casing axially abuts the upstream end of the cover such that the cover is tensioned axially when it is mounted on and fastened to the casing.
1. A casing cover for enclosing a casing in a jet engine, comprising:
first and second coaxial shells, the first coaxial shell being arranged inside the second coaxial shell; and
radial envelopes connecting the first coaxial shell to the second coaxial shell,
wherein radial arms of the casing radially extend inside the radial envelopes,
wherein the cover is fastened at a downstream end of the first coaxial shell to a first element of the casing and an upstream end of the second coaxial shell axially abuts against a second element of the casing, the downstream end of the first coaxial shell includes an annular flange and the upstream end of the second coaxial shell includes a radial lip, and
wherein an axial dimension of the cover between the downstream end of the first coaxial shell and the upstream end of the second coaxial shell in a free state is less than an axial distance of the casing between the point where the first element of the casing is fastened to the downstream end of the first coaxial shell and the point where the second element of the casing abuts the upstream end of the second coaxial shell such that the cover is tensioned axially when mounted on and fastened to the casing.
2. The casing cover as claimed in claim 1 , wherein a difference between the axial dimension of the cover, in the free state, and the axial distance between the point where the first element of the casing is fastened to the downstream end of the first coaxial shell and the point where the second element of the casing axially abuts the upstream end of the second coaxial shell is substantially equal to a maximum deviation between an axial thermal expansion of the cover and an axial thermal expansion of the casing during the operation of the jet engine.
3. The casing cover as claimed in claim 2 , wherein the difference is approximately 1 to 1.2 millimeters.
4. The casing cover as claimed in claim 1 , wherein the annular flange at the downstream end of the first coaxial shell is fastened to a flange of a bearing support by bolts and the radial lip at the upstream end of the second coaxial shell is disposed inside and upstream of a radial lip formed at an upstream end of the second element of the casing, the radial lip of the upstream end the second coaxial shell of the cover axially abuts the radial lip of the second element of the casing when the cover is mounted on the casing.
5. The casing cover as claimed in claim 4 , wherein the radial lip of the upstream end of the second coaxial shell of the cover radially abuts the second element of the casing during the operation of the jet engine due to thermal expansion.
6. A jet engine which comprises at least one casing cover, as claimed in claim 1 .
7. The casing cover as claimed in claim 1 , wherein the radial envelopes have an axially profiled shape and include a plurality of holes oriented in a downstream direction and which open out into a flow path of a gas stream.
8. The casing cover as claimed in claim 7 , wherein the radial arms include an internal cavity which circulates cooling air and a plurality of holes at an upstream end of the radial arms which open out toward an upstream end portion of the radial envelopes.
9. The casing cover as claimed in claim 1 , wherein first radially inner ends of the radial arms of the casing are fastened to a cylindrical wall of a bearing support and second radially outer ends of the radial arms are fastened to a cylindrical casing element of the casing, and the bearing support includes a substantially frustoconical wall which extends downstream towards an axis of the jet engine and supports an outer race of a bearing.
10. The casing cover as claimed in claim 9 , wherein the first element of the casing includes an annular flange attached to the cylindrical wall of the bearing support.
11. The casing cover as claimed in claim 10 , wherein the second element of the casing includes a radial lip provided on the cylindrical casing element.
12. The casing cover as claimed in claim 9 , wherein the a downstream end of the cylindrical casing element includes an elastically deformable member which radially abuts a downstream end of the second coaxial shell.
13. The casing cover as claimed in claim 1 , wherein the cover is positioned such that a stream of hot gas originating from a combustion chamber and a turbine of the jet engine flows between an area defined between the first coaxial shell and the second coaxial shell.