초록 ▼

The present invention relates to a pressure seal (7) of a turbomachine stator, said seal (7) comprising a first abradable surface opposite a rotor portion of the turbomachine and a second surface in contact with an inner shroud (3) of the stator, said seal (7) comprising a plurality of component uni

The present invention relates to a pressure seal (7) of a turbomachine stator, said seal (7) comprising a first abradable surface opposite a rotor portion of the turbomachine and a second surface in contact with an inner shroud (3) of the stator, said seal (7) comprising a plurality of component units (10), each component unit (10) having, on its first abradable surface, a circumferential step (9) creating an obstacle in the circumferential direction of the inner shroud (3).

대표청구항 ▼

1. A pressure seal (7) of a turbomachine stator, said seal (7) comprising a first abradable surface opposite a rotor portion of the turbomachine and a second surface in contact with an inner shroud (3) of the stator, the first abradable surface of the seal (7) having a stepped profile and comprising

1. A pressure seal (7) of a turbomachine stator, said seal (7) comprising a first abradable surface opposite a rotor portion of the turbomachine and a second surface in contact with an inner shroud (3) of the stator, the first abradable surface of the seal (7) having a stepped profile and comprising a plurality of component units (10), each component unit (10) comprising: a circumferential step (9) creating an obstacle in the circumferential direction of the inner shroud (3), and an axial step (8) creating an obstacle in the axial direction of the turbomachine. 2. The pressure seal (7) as in claim 1, wherein the circumferential step (9) and the axial step (8) of the component unit (10) define the contours of a profile that may assume a plurality of distinct shapes. 3. The pressure seal (7) as in claim 2, wherein the component units (10) have profiles and/or dimensions that vary in the circumferential direction of the inner shroud (3). 4. The pressure seal (7) as in claim 2, wherein the profiles of the different component units (10) are offset in the axial direction of the turbomachine. 5. The pressure seal (7) as in claim 2, wherein the component units (10) have a same profile that repeats periodically along the circumference of the inner shroud (3), thus forming repetitive units. 6. The pressure seal (7) as in claim 5, wherein each repetitive unit covers, in the circumferential direction of the inner shroud (3), an angular sector corresponding to four to ten pitches of the rotor vanes (1) driven by said rotor portion. 7. The pressure seal (7) as in claim 1, wherein the rotor portion opposite the first abradable surface comprises sealing elements (6) secured to a drum (5). 8. The pressure seal (7) as in claim 1, wherein said seal (7) is made of silicone or epoxy. 9. A turbomachine stator comprising at least one pressure seal (7) as in claim 1. 10. The pressure seal (7) of claim 1, wherein the first abradable surface is free of cavities. 11. The pressure seal (7) of claim 1, wherein the stepped profile consists of only one of the axial step. 12. The pressure seal (7) of claim 1, wherein the first abradable surface includes a raised section along a raised annular side, and a recessed section along a recessed annular side, said circumferential step being closer to the raised annular side than the recessed annular side. 13. The pressure seal (7) of claim 1, wherein each of the component units share the a first common maximum depth for the circumferential step (9) and share a second common maximum depth for the axial step (8).