The invention relates to the field of aircraft engine, in particular to devices nodal compounds housings turbine engine (hereinafter - CCD) aircraft. A device for connecting casings 1 and 2, the outer and inner contours turbofan engine comprises a sandwiched between the housings 1 and 2 the external and internal motor circuits and mounted on one of these housings an annular element formed as a thin-walled ring 6 fixed to the housing 2 by means of suspension elements in the form of inclined wall 3 with shelves 4 and 5 are rigidly fixed respectively to the thin-walled ring 6 and the housing 2. a thin-walled ring 6 is mounted relative to the housing 1 of another motor circuit with a radial annular gap 7. The thermo-compensation Technologically compound preferably all suspension elements thin-walled ring 6 with each other at their flanges 4 and 5 to form a corrugated belt. The utility model improves the reliability of the device for connecting a gas turbine engine housings, while simultaneously providing a support function of the gas generator at full kinematic junction housings and maintaining the air flow parameters in the external circuit of the engine.
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