Bleed-off device in a bypass turbojet
View Patent ↗This object is achieved by the bleed-off means comprising means for tapping air from the primary duct which are arranged upstream of the intermediate casing and means for evacuating the air tapped into the secondary duct downstream of the support arms, these means comprising conduits arranged around the intermediate casing under the platforms.
1. A bypass turbojet comprising:
a primary duct;
a secondary duct;
a low-pressure compressor;
a high-pressure compressor;
a structural intermediate casing arranged axially between said low-pressure compressor and said high-pressure compressor, said structural intermediate casing comprising a radial flange defining an upstream face of said structural intermediate casing, said structural intermediate casing being equipped at its periphery with a plurality of support arms having platforms which internally delimit the secondary duct, and
bleed-off means allowing some of a gaseous stream delivered by said low-pressure compressor to be tapped off and led to said secondary duct, said bleed-off means comprising:
means for tapping air from said primary duct, said means for tapping being arranged upstream of said radial flange of said intermediate casing, and
means for evacuating said tapped air into said secondary duct downstream of said support arms, said means for evacuating comprising conduits arranged around said structural intermediate casing under said platforms.
2. The bypass turbojet according to claim 1 , wherein said bleed-off means is not mechanically fixed to said structural intermediate casing.
3. The bypass turbojet according to claim 1 , wherein said structural intermediate casing is free of any hole in its radial flanges.
4. The bypass turbojet according to claim 1 , wherein said primary duct further comprises an annular conduit with a swan neck cross-sectional shape.
5. The bypass turbojet according to claim 1 , further comprising an inter-duct casing separating said primary and said secondary ducts.
6. The bypass turbojet according to claim 5 , wherein said structural intermediate casing is located within said inter-duct casing.
7. The bypass turbojet according to claim 1 , wherein said bleed-off means further comprises a control ring controlling a rate at which said gaseous stream is tapped off.
8. The bypass turbojet according to claim 1 , wherein said structural intermediate casing bears a device for driving a turbojet equipment.
9. The bypass turbojet according to claim 1 , wherein said structural intermediate casing further comprises radial arms configured to transmit to the support arms forces exerted by a fan and said low-pressure compressor on their bearings.
10. A bypass turbojet comprising:
a primary duct;
a secondary duct;
a low-pressure compressor;
a high-pressure compressor;
a structural intermediate casing arranged axially between said low-pressure compressor and said high-pressure compressor, said structural intermediate casing comprising a radial flange defining an upstream face of said structural intermediate casing, and
a manifold in communication with said primary duct and said secondary duct, said manifold being in communication with said primary duct at a position axially upstream of said radial flange.
11. The bypass turbojet according to claim 10 , wherein aid structural intermediate casing comprises at its periphery a support arm having a platform which delimit the secondary duct.
12. The bypass turbojet according to claim 10 , wherein said manifold is in communication with said secondary duct axially downstream of said structural intermediate casing.
13. The bypass turbojet according to claim 10 , wherein said manifold comprises a conduit arranged around said intermediate casing.
14. The bypass turbojet according to claim 10 , wherein said manifold is not mechanically fixed to said structural intermediate casing.
15. The bypass turbojet according to claim 10 , wherein said structural intermediate casing is free of any hole in its radial flanges.
16. The bypass turbojet according to claim 10 , wherein said primary duct further comprises an annular conduit with a swan neck cross-sectional shape.
17. The bypass turbojet according to claim 10 , further comprising a inter-duct casing separating said primary and said secondary ducts.
18. The bypass turbojet according to claim 17 , wherein said structural intermediate casing is located within said inter-duct casing.
19. The bypass turbojet according to claim 10 , wherein said manifold further comprises a control mechanism which controls a rate at which gaseous stream is tapped off from said primary duct.
20. The bypass turbojet according to claim 10 , wherein said structural intermediate casing bears a device for driving a turbojet equipment.