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EP-4286654-B1 - JOINT BETWEEN GAS TURBINE ENGINE COMPONENTS WITH BONDED FASTENER(S)

EP4286654B1EP 4286654 B1EP4286654 B1EP 4286654B1EP-4286654-B1

Inventors

  • SAVARD, PHILIPPE
  • LEFEBVRE, GUY

Dates

Publication Date
20260506
Application Date
20230531

Claims (14)

  1. An assembly (20) for a gas turbine engine, comprising: a seal carrier (33) with an annular groove (66), the seal carrier (33) extending between a first side and a second side; a seal land (93) opposite the annular groove (66); a seal ring (23) sealing a gap between the seal carrier (33) and the seal land (93), the seal ring (23) seated in the annular groove (66); and a plate (98) at the second side of the seal carrier (33); characterised in that : the assembly (20) further comprises a fastener (100) including a head (116) and an elongated member (118) connected to the head (116); the head (116) at the first side of the seal carrier (33); and the elongated member (118) projecting out from the head (116) through the seal carrier (33), the seal ring (23) and the plate (98), and the elongated member (118) bonded to the plate (98); the plate (98) is a retention plate (98) comprising one or more retainer apertures (112) extending axially through the retention plate (98); the seal carrier (33) is constructed from a seal carrier material, and the plate (98) and the fastener (100) are constructed from a common material that is different than the seal carrier material; and the plate (98) is welded or brazed to the elongated member (118) at a distal end (120) of the elongated member (118).
  2. The assembly (20) of claim 1, further comprising: a second fastener (100) including a second head (116) and a second elongated member (118) connected to the second head (116); the second head (116) at the first side of the seal carrier (33); the second elongated member (118) projecting out from the second head (116) through the seal carrier (33), the seal ring (23) and the plate (98); and the second elongated member (118) bonded to the plate (98).
  3. The assembly (20) of claim 1 or 2, wherein the fastener (100) rotationally secures the seal ring (23) to the seal land (93).
  4. The assembly (20) of claim 1, 2 or 3, wherein the seal carrier (33) and the seal ring (23) are clamped between the head (116) and the plate (98).
  5. The assembly (20) of any preceding claim, wherein: the head (116) is abutted against the seal carrier (33) at the first side of the seal carrier (33).
  6. The assembly (20) of any preceding claim, wherein: the head (116) is seated in a recess (50) in the seal carrier (33) at the first side of the seal carrier (33).
  7. The assembly (20) of any preceding claim, wherein the plate (98) is abutted against the seal carrier (33) at the second side of the seal carrier (33).
  8. The assembly (20) of any preceding claim, wherein: the seal carrier (33) includes an annular first side member (34) and an annular second side member (36); the annular first side member (34) is disposed at the first side of the seal carrier (33); the annular second side member (36) is disposed at the second side of the seal carrier (33); and the annular groove (66) is formed by and between the annular first side member (34) and the annular second side member (36).
  9. The assembly (20) of claim 8, wherein the head (116) engages the annular first side member (34) and the plate (98) engages the annular second side member (36).
  10. The assembly (20) of claim 8 or 9, wherein: the annular first side member (34) has a first member thickness (126); the annular second side member (36) has a second member thickness (127); and the plate (98) has a plate thickness (124) that is less than at least one of the first member thickness (126) or the second member thickness (127).
  11. The assembly (20) of claim 8, 9 or 10, wherein: the annular first side member (34) has a first member height (132); the annular second side member (36) has a second member height (133); and the plate (98) has a plate height (130) that is less than at least one of the first member height (132) or the second member height (133).
  12. The assembly (20) of any preceding claim, wherein: the plate (98) is an arcuate body.
  13. The assembly (20) of any preceding claim, wherein: the seal ring (23) circumscribes the seal land (93); and the seal carrier (33) circumscribes the seal ring (23).
  14. The assembly (20) of any preceding claim, further comprising: a flowpath wall (22, 136) that includes the seal carrier (33); and a support structure (24, 146) that includes the seal land (93).

Description

TECHNICAL FIELD This disclosure relates generally to a gas turbine engine and, more particularly, to an anti-rotation joint between engine components. BACKGROUND INFORMATION A gas turbine engine may include a seal ring for sealing a gap between engine components. Various techniques are known in the art for retaining the seal ring in position relative to the engine components. While these known techniques have various benefits, there is still room in the art for improvement. EP 3348814 B1 discloses a prior art assembly according to the preamble of claim 1. SUMMARY According to an aspect of the present disclosure, an assembly is provided for a gas turbine engine according to claim 1. The following optional features may be applied to any of the above aspects: The assembly may also include a second fastener. This second fastener may include a second head and a second elongated member connected to the second head. The seal head may be at the first side of the seal carrier. The second elongated member may project out from the second head through the seal carrier, the seal ring and the plate. The second elongated member may be bonded to the plate. The fastener may rotationally secure the seal ring to the seal land. The seal carrier and the seal ring may be clamped between the head and the plate. The head may be abutted against the seal carrier at the first side of the seal carrier. The head may be seated in a recess in the seal carrier at the first side of the seal carrier. The plate may be abutted against the seal carrier at the second side of the seal carrier. The seal carrier may include an annular first side member and an annular second side member. The annular first side member may be disposed at the first side of the seal carrier. The annular second side member may be disposed at the second side of the seal carrier. The annular groove may be formed by and/or may be between the annular first side member and the annular second side member. The head may engage the annular first side member. The plate may engage the annular second side member. The annular first side member may have a first member thickness. The annular second side member may have a second member thickness. The plate may have a plate thickness that may be less than the first member thickness and/or the second member thickness. The annular first side member may have a first member height. The annular second side member may have a second member height. The plate may have a plate height that may be less than the first member height and/or the second member height. The plate may have an arcuate body. The seal ring may circumscribe the seal land. The seal carrier may circumscribe the seal ring. The assembly may also include a flowpath wall and a support structure. The flowpath wall may include the seal carrier. The support structure may include the seal land. The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof. The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a partial side sectional illustration of an assembly for a gas turbine engine.FIG. 2 is a partial end view illustration of a first engine component.FIG. 3 is a partial cross-sectional illustration of the first engine component.FIG. 4 is a partial end view illustration at a first circumferential location along a second engine component.FIG. 5 is a partial end view illustration at a second circumferential location along the second engine component.FIG. 6 is a partial perspective cutaway illustration of the engine assembly.FIG. 7 is another partial perspective cutaway illustration of the engine assembly.FIG. 8 is a partial side sectional illustration of the gas turbine engine at a vane array.FIG. 9 is a partial side sectional illustration of another assembly for the gas turbine engine.FIG. 10 is a side schematic illustration of a turbojet gas turbine engine with which the engine assembly may be included. DETAILED DESCRIPTION FIG. 1 illustrates an assembly 20 for a gas turbine engine. This engine assembly 20 includes a plurality of engine components 22-24 and at least one component retention assembly 25. The first engine component 22 is configured as a stationary component within the gas turbine engine. This first engine component 22 extends axially along a centerline axis 28 to an axial end 30 of the first engine component 22. Briefly, this centerline axis 28 may be a centerline axis of the engine assembly 20 and/or any one or more or all of its engine components 22-25, and may also be coaxial with a rotational axis and/or a centerline axis of the gas turbine engine. The first engine component 22 extends circumferentially about (e.g., completely around) the centerline axis 28 providing the first engine component 22 with, for example, a full-hoop body. The first eng