Intermediate casing extension of improved design
View Patent ↗The invention relates to an extension ( 30 ) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part ( 64 ) preferably forming an annular groove ( 66 ) open radially outwards, into which the nacelle cowls will fit ( 38 ), the end ( 64 ) comprising at least one first angular sector ( 76 b ). According to the invention, the extension comprises a body ( 77 ) made from a single piece comprising a junction ring ( 74 ) and at least one second angular sector ( 76 a ) of said downstream annular connecting part ( 64 ), the first angular sector being added onto the extension body ( 77 ).
1. Extension ( 30 ) of an intermediate frame ( 21 ) for an aircraft turbine engine, that will project downstream from an outer ring ( 23 ) of said intermediate frame, said extension comprising a downstream annular connecting part ( 64 ) forming retention means ( 66 ) designed to hold nacelle cowls ( 38 ), said downstream annular connecting part ( 64 ) comprising at least a first angular sector ( 76 b ),
wherein said extension comprises a body ( 77 ) made from a single piece comprising a junction ring ( 74 ) and an integrally formed at least one second angular sector ( 76 a ) of said downstream annular connecting part ( 64 ), said first angular sector ( 76 b ) being added onto said extension body ( 77 ), and in that the extension comprises a plurality of first angular sectors ( 76 b ) and a plurality of second angular sectors ( 76 a ), a sum of all second angular sectors ( 76 a ) covering at least 80% of the circumference of the body.
2. Extension according to claim 1 , wherein the first angular sectors ( 76 b ) are mounted onto the body by bolts ( 77 ), in recesses ( 79 ) formed between two second directly consecutive sectors ( 76 a ) of said body.
3. Extension according to claim 1 , wherein said first angular sectors ( 76 b ) are made from a first material, and the second angular sectors ( 76 a ) are made from a second material different from the first material.
4. Extension according to claim 1 , wherein said retention means are formed from a groove ( 66 ) open radially outwards, into which the nacelle cowls ( 38 ) will fit.
5. Extension according to claim 1 , wherein said retention means are formed from a retention flange ( 66 ) projecting radially outwards.
6. Turbine engine ( 2 ) for an aircraft, comprising an intermediate frame ( 21 ) fitted at the downstream end of its outer ring ( 23 ) with an extension ( 30 ) according to claim 1 .
7. Turbine engine according to claim 6 , wherein the junction ring ( 74 ) of the body ( 77 ) is fitted with an annular collar ( 75 ) fastening the body to the downstream end of the outer ring ( 23 ) of the intermediate frame ( 21 ).
8. Propulsion assembly ( 1 ) for an aircraft comprising a turbine engine ( 2 ) according to claim 6 , and a nacelle ( 32 ) comprising the nacelle cowls ( 38 ) cooperating with said retention means ( 66 ).
9. Propulsion assembly ( 1 ) according to claim 8 , further comprising a turbine engine EMS ( 4 ) comprising a rigid structure ( 11 ) and means of fastening the turbine engine on said rigid structure, said nacelle cowls ( 38 ) thus being articulated on said rigid structure ( 11 ).
10. Extension according to claim 3 , wherein the first material is titanium or one of its alloys.
11. Extension according to claim 3 , wherein the second material is aluminium or one of its alloys.
12. Extension according to claim 5 , wherein said retention flange holds the nacelle cowls ( 38 ) by means of a retaining structure ( 93 ) clamping the retention flange ( 66 ) and a portion ( 68 ) of said nacelle cowls.