초록 ▼

The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and

The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell fastened to the annular structure. A first seal is fitted in a first groove provided around the upstream part of the external casing of the diffuser grating, the strips of this first seal bearing on the downstream end of a first projection integral with the annular structure. A second seal is fitted in a second groove provided under said annular structure, the strips of this second seal bearing on the downstream end of a second projection integral with said annular structure and on the end of a third projection formed on the upstream part of the external casing of the diffuser.

대표청구항 ▼

The invention claimed is: 1. A jet engine comprising, from upstream to downstream (the upstream and downstream directions being defined by the direction of circulation of the primary flow), a high-pressure compressor, a diffuser grating and a combustion chamber, said high-pressure compressor compri

The invention claimed is: 1. A jet engine comprising, from upstream to downstream (the upstream and downstream directions being defined by the direction of circulation of the primary flow), a high-pressure compressor, a diffuser grating and a combustion chamber, said high-pressure compressor comprising an external shell which radially delimits a duct for said primary flow and is connected to an annular structure extending radially outward, said diffuser grating comprising in the axial continuation of said external compressor shell an external casing connected to a rearwardly oriented conical strut delimiting, upstream, an end of said combustion chamber, said strut itself being connected to an external casing shell which extends in the upstream direction and is fastened to said annular structure by fastening means, said strut, said external casing shell and said annular structure defining a cavity around said diffuser grating, air bleed orifices being made in said strut in order to bring the end of the combustion chamber into communication with said cavity, said external casing shell being equipped with air bleed vents, and sealing means being provided between said annular structure and said external diffuser grating casing in order to isolate said cavity from the duct for the primary flow, wherein the sealing means comprise a first seal and a second seal of the sectorized type made up of counterseal-lined strips which are acted on by springs, said first seal being fitted in a first groove provided around an upstream part of the external casing of the diffuser grating, the strips of this first seal bearing, under the action of first springs, on a downstream end of a first projection integral with the annular structure, and said second seal being fitted in a second groove provided under said annular structure, the strips of this second seal bearing, under the action of second springs on an upstream end of a second projection integral with said annular structure and on an upstream end of a third projection integral with said upstream part of the external casing. 2. The jet engine as claimed in claim 1, wherein the first groove is delimited by an upstream flange and a downstream flange, the first seal and the first springs being retained by means of rivets fastened on said flanges, and the third projection is formed on an upstream face of said upstream flange. 3. The jet engine as claimed in claim 2, wherein the annular structure comprises a rearwardly oriented, radially inner part, and the second groove is delimited by said part and a third flange situated above the upstream flange, the first projection extending in the downstream direction from a radially inner end of said third flange, said radially inner end additionally having the second projection which extends in the upstream direction and on which the second seal bears. 4. The jet engine as claimed in claim 3, wherein the second springs are fastened to lugs formed on said annular structure independently of the fastening by means of pins of the strips and counterseals of the second seal in the second groove.