Device for passive control of the thermal expansion of the extension casing of a turbo-jet engine

1. A device for passive control of the thermal expansion of the extension casing of a turbo jet engine and for relieving the stresses thereof, said extension casing surrounding the inner casing of the high pressure compressor of the turbo jet engine, and including a flange for attachment to an upstream flange of the casing of the combustion chamber, wherein both flanges clamp a retaining flange of a diffusing cone, at least one circumferential cavity being arranged between one of the casing flanges and the flange of the diffusing cone wherein circulated gas is tapped at the inlet of the combustion chamber.

2. A device according to claim 1 , wherein the cavity is formed by a recess provided in one of said flanges.

3. A device according to claim 2 , wherein the circulation of the gas flux takes place using calibrated perforations provided in a flange.

4. A device according to claim 3 , wherein, the recess providing an inner transversal rim and an outer transversal rim resting on the face of the adjoining flange, the inner axial rim includes calibrated perforations forming gas inlet radial throats, and the flange comprises calibrated perforations forming outlet channels of the gas flux.

5. A device according to claim 4 , wherein the channels comprise an inlet orifice situated in the recess and an outlet orifice emerging into the annulus situated between the casing of the compressor and the extension casing.

6. A device according to claim 5 , the cavity of which is composed of several recesses laid out circumferentially in sectors, each recess communicating with a radial throat and a channel.

7. A device according to claim 6 , the flanges of which include flange holes laid out circumferentially, intended for letting through linking bolts for attachment of the flange with the upstream flange of the diffusing cone and the upstream flange of the casing of the combustion chamber.

8. A device according to claim 7 , wherein the radial throats are drilled at right angles with a flange hole.

9. A device according to claim 8 , wherein the channels are radially aligned with a flange hole.

10. A device for controlling thermal expansion of an extension casing of a turbo-jet engine with a combustion chamber, said extension casing being configured to surround an inner casing of a compressor of the turbo jet engine, said device comprising:

a downstream flange for the extension casing;

an upstream flange for the combustion chamber, said upstream flange being connected to said downstream flange;

a cavity between said downstream flange and said upstream flange;

perforations configured to let gas flow into said cavity from said combustion chamber; and

channels configured to let gas flow from said cavity and into a space between the casing of the compressor and the extension casing.

11. A device according to claim 10 , wherein said cavity is defined by a recess in at least one of said downstream flange or said upstream flange.

12. A device according to claim 11 , wherein said recess is defined by said downstream flange.

13. A device according to claim 10 , further comprising a retaining flange for a diffusing cone, said retaining flange being clamped between said downstream flange and said upstream flange.

14. A device according to claim 13 , wherein said cavity is between said retaining flange and said downstream flange.

15. A device according to claim 13 , wherein said cavity is between said retaining flange and said upstream flange.

16. A device according to claim 10 , wherein said channels are formed in said downstream flange for the extension casing.

17. A device according to claim 10 , wherein said perforations are formed in an inner rim of the downstream flange for the extension casing.

18. A device according to claim 16 , wherein said perforations are formed in an inner rim of the downstream flange for the extension casing.