Sealing assembly, turbine and associated assembly method

FR3158534A1Pending Publication Date: 2025-07-25SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2024000576
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-01-19
Publication Date
2025-07-25

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Abstract

A sealing assembly for a turbomachine, comprising: - A sealing ring centered on an axis (X) comprising a first ring sector (70) and a second ring sector (70) arranged circumferentially opposite each other, the first ring sector comprising a first connecting face (70a) comprising a first groove (75b) and the second ring sector comprising a second connecting face (70a) comprising a second groove (75b), the first groove and the second grooves being arranged opposite each other to form a first housing (76b) comprising a first axial opening (77a), - a first sealing tongue (8a) mounted in the first housing to provide a seal between the ring sectors, the first connecting face comprising a third groove (75c) passing through the first groove and partly forming a second housing (76c),wherein a second sealing tab (8b) is inserted to extend between the first sealing tab and the first axial opening. Figure for abstract: Fig. 4,
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Claims

8. A turbine (160) according to claim 7, wherein the radial distance between the spoiler and the first housing (76b) is less than the radial dimension of the second sealing tab (8b) inserted into the second housing (76c).

9. A turbomachine (100) comprising a turbine (160) having a first turbine stage comprising a first distributor (2) and a first bladed wheel (3), and a second turbine stage comprising a second distributor (2), the turbine (160) comprising a sealing assembly according to one of claims 1 to 6 located axially between the first distributor (2) and the second distributor (2), the sealing assembly surrounding the first bladed wheel (3).

10. A method of mounting a turbine according to claim 7 or 8, comprising the following steps: - assembling (El) at least a first and a second ring sector to form a sealing ring (7), then mounting the sealing ring (7) on the outer casing (4) around the upstream impeller; - inserting (E2) the first sealing tab (8a) into the first housing (76b); - inserting (E3) the second sealing tab (8b) into the second housing (76c); - mounting (E4) the downstream distributor on the outer casing (4), so that the spoiler (221) is arranged opposite the second radial opening (78a) of the second housing (76c). [Fig. 1] Fig. 1 [Fig. 2] 100 * Fig.2 [Fig. 3] Fig. 3

Citation Information

Patent Citations

  • Mateface cooling feather seal assembly

    US20120189424A1

  • Flexible three-piece seal assembly

    US5154577A

  • Low-pressure turbine shroud

    US5188507A