Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it
View Patent ↗A unit locking a ring sector attachment device onto an aircraft turbomachine casing, the unit including two clamping arms connected to each other at their aft ends by a connecting arm extending approximately parallel to the general direction between the two clamping arms. The unit also includes a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms.
1. A locking unit for a device configured to attach ring sectors onto an aircraft turbomachine casing, the unit extending along a circumferential direction between a first circumferential end and a second circumferential end, the unit comprising:
in a cross section of the unit in a plane orthogonal to the circumferential direction, two clamping arms connected to each other at their aft ends by a connecting arm extending between the two clamping arms, forward ends of the two clamping arms configured to squeeze at least one ring sector into contact with at least one casing element, between them; and
a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms, and
wherein each passage is approximately cylindrical with its axis corresponding to the direction line.
2. A locking unit according to claim 1 , wherein each direction line is a straight line.
3. A locking unit according to claim 1 , wherein the two passages are arranged on or close to the first circumferential end and the second circumferential end.
4. A locking unit according to claim 1 , wherein each passage is a through passage or a blind passage.
5. A locking unit according to claim 1 , wherein each direction line extends approximately radially.
6. A locking unit according to claim 1 , wherein each passage is in a form of a groove extending along the direction line.
7. A locking unit according to claim 6 , wherein each groove is configured to open up in the circumferential direction.
8. A locking unit according to claim 7 , wherein each groove is approximately semi-circular in shape when viewed from outside the unit and along the direction line.
9. A locking unit according to claim 6 , wherein each groove forms at least one stop surface on the connecting arm, the stop surface being oriented approximately towards a space between the arms of the unit, defined between the clamping arms.
10. A locking unit according to claim 1 , wherein each passage has a closed delimitation line in a view taken from outside the unit along the direction line.
11. A locking unit according to claim 10 , wherein each delimitation line is generally an oblong or circular line.
12. A locking unit according to claim 1 , forming an angular sector of an annular locking device.
13. A device for fixing ring sectors on an aircraft turbomachine casing comprising:
casing elements formed with first aft circumferential rims on which second aft circumferential rims of the ring sectors are applied; and
a plurality of locking units according to claim 1 , engaged on the first and second circumferential rims to hold them in contact with each other.
14. A turbine in an aircraft turbomachine comprising a ring sectors attachment device according to claim 13 .
15. An aircraft turbomachine comprising a turbine according to claim 14 .
16. A turbomachine according to claim 15 , which is a turbojet or a turboprop.