Stage of a turbine or compressor, particularly for a turbomachine
View Patent ↗A stage of a turbine or compressor for a turbomachine including at least a vane disk surrounded with a sectorized ring supported by a casing and including a circumferential flange radially clamped on a rail of the casing by substantially C-shaped cross-section locks which are axially engaged on the casing rail and the flange of the ring is disclosed. The inner and outer walls of each lock includes radial bearing surfaces on the flange of the ring and the casing rail, respectively. The bearing surfaces only extend on a part of the width of the lock.
1. A stage of a turbine or compressor, comprising:
at least a vane disk surrounded with a sectorised ring supported by a casing and comprising a circumferential flange radially clamped on an annular rail of the casing by substantially C-shaped cross-section locks which are axially engaged on the annular rail and the circumferential flange of the ring, each lock having two circumferentially directed parallel walls, respectively inner and outer, connected together by a radial wall, the inner and outer walls of the lock comprising radial supporting or bearing means on the circumferential flange and the annular rail, respectively,
wherein those bearing means only extend on a part of the circumferential extent of the lock.
2. A stage according to claim 1 , wherein each one of the inner and outer walls of the lock comprises at least one portion of greater dimension in an axial direction and at least one portion of smaller dimension in an axial direction, the, or each, portion of greater dimension having said radial bearing means.
3. A stage according to claim 2 , wherein the inner wall of the lock comprises a median portion of smaller axial dimension and end portions of greater axial dimension, or a median portion of greater axial dimension and end portions of smaller axial dimension.
4. A stage according to claim 2 , wherein the outer wall of the lock comprises a median portion of greater dimension and end portions of smaller axial dimension, or a median portion of smaller axial dimension and end portions of greater axial dimension.
5. A stage according to claim 2 , wherein the, or each, portion of greater axial dimension of each lock wall has a circumferential extent which makes up about the half of that of the lock.
6. A stage according to claim 2 , wherein the, or each, portion of greater axial dimension of each lock wall has a circumferential extent which makes up about the third of that of the lock.
7. A stage according to claim 2 , wherein the, or each, portion of greater axial dimension of each lock wall has a circumferential extent which makes up about the quarter of that of the lock.
8. A stage according to claim 2 , wherein the portions of smaller axial dimension of the lock walls are formed by serrations of those walls.
9. A compressor or turbine for a turbomachine comprising at least one stage of turbine or compressor according to claim 1 .
10. A turbomachine comprising at least one stage of turbine or compressor according to claim 1 .
11. A lock for a stage of a turbine or a compressor according to claim 1 , comprising:
two circumferentially directed parallel walls, respectively inner and outer, connected together at one circumferential edge thereof by a third substantially radial wall so that the lock has a substantially C-shaped cross-section,
wherein each one of the inner and outer walls comprises at the other of their circumferential edges thereof at least one portion of greater dimension in an axial direction and at least one portion of smaller dimension in the axial direction, said at least one portion of smaller dimension extending along at least a quarter of the circumferential extent of the lock in a circumferential direction, and said at least one portion of greater dimension having radial bearing means.
12. A stage according to claim 1 , wherein the part of the circumferential extent of the lock of the which the bearings means extend is less than the entire circumferential extent of the lock.
13. A stage according to claim 2 , wherein the, or each, portion of greater dimension on the inner wall of the lock includes an outer bearing wall which abuts the circumferential flange of the ring, and the, or each, portion of greater dimension on the outer wall of the lock includes an inner bearing wall which abuts the annular rail.
14. A stage according to claim 12 , wherein the outer bearing wall circumferentially extends along an entire circumferential dimension of the, or each, portion of greater dimension on the inner wall.
15. A stage according to claim 12 , wherein the inner bearing wall circumferentially extends along an entire circumferential dimension of the, or each, portion of greater dimension on the outer wall.