Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design
View Patent ↗The invention relates to a low pressure turbine ( 1 ) of a turbomachine comprising a nozzle ( 62 ) belonging to an upstream stage ( 20 B) and a nozzle ( 162 ) belonging to a downstream stage ( 20 C), the nozzle ( 62 ) forming segments ( 62 a ) having an external structure ( 66 ) comprising: a tab ( 76 ) bearing radially on a hook ( 79 ) fixed to the case, a tab ( 85 ) bearing radially on a reaming ( 87 ) in the case, the tabs ( 76, 85 ) delimiting an annular upstream cooling air circulation cavity ( 91 ), a contact surface ( 84 ) extending in the downstream direction from the tab ( 85 ) and lined with an abradable element ( 86 ) on the inside, the contact surface comprising a downstream end ( 92 ) bearing axially on the nozzle ( 162 ) and bearing radially on a stop ( 93 ) of the case, the contact surfaces ( 84 ) delimiting an annular downstream cooling air circulation cavity ( 94 ) communicating with cavity ( 91 ).
1. A low pressure turbine of a turbomachine comprising a stator provided with a case, a nozzle belonging to an upstream stage and a nozzle belonging to a downstream stage, each of the two stages housed in the case also comprising a bladed mobile wheel arranged downstream from the nozzle of its stage, the nozzle of the upstream stage being segmented so as to form angular nozzle segments each with an external structure from which nozzle blades project radially inwards, wherein each external structure comprises:
a first tab bearing radially on a hook on the stator fixed to the case,
a second tab bearing radially on a reaming in the case, said first and second tabs of the external structures of the segments delimiting an annular upstream cooling air circulation cavity, jointly with said case,
a contact surface extending in the downstream direction from the second tab and lined with an abradable element on the inside in contact with the mobile wheel of the upstream stage, said contact surface comprising a downstream end bearing axially on the nozzle of said downstream stage and bearing radially on a stop of the case or said nozzle in the downstream stage, the contact surfaces of the external structures of the segments cooperating with said case, to delimit an annular downstream cooling air circulation cavity communicating via a passage with said upstream cavity.
2. A turbine according to claim 1 , wherein the nozzle in the downstream stage is segmented so as to form angular nozzle segments, or is in the shape of an annular part.
3. The turbine according to claim 1 or claim 2 , wherein the nozzle of said downstream stage has an external structure from which the nozzle blades project radially inwards, said external structure comprising:
a first annular tab on which said downstream end of the contact surfaces of the segments bears axially, and
a second annular tab delimiting an upstream annular cooling air circulation cavity jointly with said first annular tab and said case, the cavity communicating with said downstream cooling air circulation cavity of the nozzle in the upstream stage.
4. The turbine according to claim 3 , wherein the downstream ends of the contact surfaces of the segments in the nozzle in the upstream stage, bearing axially on said first annular tab of the nozzle in the downstream stage, cooperate with this first annular tab to define an annular pressurisation cavity containing cooling air from said downstream cavity, so as to limit the air leakage flow from the upstream cavity of the nozzle in the downstream stage to the primary flow, between the nozzles in the upstream stage and the downstream stage.
5. The turbine according to claim 4 , wherein the downstream end of the contact surfaces of the segments in the nozzle in the upstream stage is generally U or C shaped with the open part facing downstream, the two ends of the U or C bearing axially on said first annular tab of the nozzle in the downstream stage.
6. The turbine according to claim 1 , for wherein each external structure, said first tab, said second tab and said contact surface are made of a single part with an external ring segment from which nozzle blades project radially inwards.
7. The turbine according to claim 1 , wherein said stop, on which said downstream end of the contact surface bears radially, is a reaming made on the case or on the nozzle in the downstream stage.
8. The turbine according to claim 1 , wherein the stator hook on which the first tab bears radially, is made of a single part with the case or is added onto this case.
9. The turbine according to claim 1 , wherein the case also comprises an axial stop facing said downstream end of the contact surface and at a distance from it, in the direction opposite the nozzle in the downstream stage.
10. A turbomachine comprising a low pressure turbine according to claim 1 .
11. The turbine according to claim 1 , wherein said downstream end forms a leak tight axial contact with the nozzle of said downstream stage, said leak tight axial contact being configured to limit leaks from a primary flow between the nozzles of said upstream and downstream stages.