Sealing assembly, turbine and associated process

FR3158533A1Pending Publication Date: 2025-07-25SAFRAN AIRCRAFT ENGINES SAS
View PDF 3 Cites 0 Cited by

Patent Information

Application Number
FR2024000575
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-01-19
Publication Date
2025-07-25

Smart Images

  • Figure 00000020_0000
    Figure 00000020_0000
  • Figure 00000021_0000
    Figure 00000021_0000
  • Figure 00000022_0000
    Figure 00000022_0000
Patent Text Reader

Abstract

A method for mounting a sealing assembly comprising a first ring sector (701) and a second ring sector (702), the first ring sector (701) comprising a first connecting face (70a) and the second ring sector (702) comprising a second connecting face (70b), the first connecting face (70a) comprising a first groove (75c) and the second connecting face (70b) comprising a second groove (75d) configured to be arranged circumferentially facing each other so as to define a housing (76b) comprising an axial opening (77a) opening at an axial end of the sealing assembly when said assembly is mounted, the method comprising the following steps: - introducing (E1) a sealing tab (64b) into the first groove (75c), the first groove (75c) and the second groove (75d) not being aligned circumferentially;- displacement (E2) of the second ring sector (702) relative to the first ring sector (701) to circumferentially align the first groove (75c) and the second groove (75d), the alignment having the effect of blocking the sealing tab (64b) so as to prevent the sealing tab (64b) from escaping from the housing (76b) through the axial opening (77a). Figure for abstract: No figure;
Need to check novelty before this filing date? Find Prior Art

Claims

ring (702) arranged circumferentially end-to-end around the axis (X), the first ring sector (701) comprising a first connecting face (70a) and the second ring sector (702) comprising a second connecting face (70b) arranged circumferentially opposite the first connecting face (70a), the first connecting face (70a) comprising a first groove (75c) and the second connecting face (70b) comprising a second groove (75d), the first groove (75c) and the second groove (75d) being arranged circumferentially opposite each other so as to form a housing (76b) comprising an unobstructed axial opening (77a) which opens at an axial end of the sealing assembly, - a sealing tab (64b) mounted in the housing (76b) so as to provide a seal between the first sector ring (701) and the second ring sector (702) circumferentially adjacent,the first groove (75c) comprising a first stop (78a) and the second groove (75d) comprising a second stop (78b), the first stop (78a) and the second stop (78b) reducing a section of the axial opening (77a) so that the sealing tab (64b) cannot escape through said axial opening (77a) by being axially blocked by both the first and second stops (78a, 78b).,

9. A sealing assembly according to claim 8, wherein the first stop (78a) and the second stop (78b) have identical dimensions and are arranged symmetrically with respect to a longitudinal plane comprising the axis (X).

10. A sealing assembly according to claim 8 or 9, wherein the first stop (78a) and the second stop (78b) are rectangular. FIG 1 FIG 2 in FIG 3 [Fig. 5] FIG 5 [Fig. 6] FIG 6 [Fig. 7A] FIG 7 A [Fig. 7B] [Fig. 8A] FIG SA. [Fig. 8B] FIG SB

Citation Information

Patent Citations

  • Methods and apparatus for assembling turbine engines

    US20070104571A1

  • Seal segment for shroud ring of a gas turbine engine

    US20200191005A1

  • Method for forming a cooling passage and for cooling a turbine section of a rotary machine

    US6254333B1