Aerofoil stage and seal for use therein

Abstract

A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage. Each annulus filler has opposing side faces which are spaced circumferentially from the adjacent blades and which correspond in profile therewith, and resilient seal strips each including a stiffener are mounted adjacent the opposing side faces of the annulus fillers to seal the gaps between the annulus fillers and the aerofoils. The stiffeners have three-dimensional curvature. Claims are also included to the annulus filler and to the seal strip.

Description

The invention will now be described, by way of example, with reference to the accompanying drawings in which:

FIG. 1 is a perspective view of an annulus filler for a stage according to the invention;

FIG. 2 is an axial view of a seal strip for a stage according to the invention, showing details of its construction;

FIGS. 3 and 4 are axial views of a seal strip for a stage according to the invention, showing the variation in angle along the length of the seal;

FIG. 5 is a plan view of a seal strip for a stage according to the invention; and

FIGS. 6 and 7 are cross-sectional views of FIG. 3, taken respectively at the positions marked VI-VI and VII-VII.

Referring first to FIG. 1, an annulus filler of known type is shown generally at 12. In use, the upper surface 14 or lid of the annulus filler 12 bridges the gap between two adjacent fan blades and defines the inner wall of the flow annulus of the fan stage. The annulus filler 12 is mounted on a fan disc (not shown) by two hooks 16 and 18, respectively towards the forward and rearward ends of the annulus filler 12. It is also attached to the support ring (not shown) by a mounting feature 20.

The annulus filler 12 has two opposed side faces 22, 24, which in use confront the aerofoil surfaces of two adjacent fan blades (not shown). The side face 22 confronts the suction surface of one fan blade, and the side face 24 confronts the pressure surface of the adjacent fan blade. Mounted adjacent the side face 22 is a suction side seal strip 26, which extends generally outwards and downwards from the side face 22 (in use, these directions correspond respectively to circumferentially and radially inwards). A pressure side seal strip 28 is similarly mounted adjacent the side face 24.

FIG. 2 shows the construction of the seal strip 26 in more detail. The construction of seal strip 28 is essentially identical.

The seal strip 26 is adhesively mounted on the underside of the annulus filler lid 14, adjacent the side face 22. The body 32 of the seal strip 26 is formed of rubber, with a cloth reinforcing layer 34. The seal strip 26 also includes a metal stiffener 36, which extends substantially the full axial length of the seal strip 26 (in this figure, “axial” is the direction into and out of the paper). The flap 38 defines an angle θ with the annulus filler lid 14.

The reinforcing layer 34 extends through the whole radial depth of the seal strip 26. The stiffener 36, however, does not. Dimension A indicates the distance from the top of the stiffener 36 to the top of the seal strip 26. Dimension B indicates the distance from the bottom of the seal strip 26 to the bottom of the stiffener 36. The radial depth of the stiffener 36 varies along its length to ensure that the dimensions A and B remain constant, so that the stiffener cannot break through the rubber body 32 during manufacture.

In use, the flap 38 of the seal strip 26 contacts the suction surface 40 of a fan blade 42. Centrifugal forces arising from the rotation of the fan stage urge the seal strip 26 into contact with the surface 40, so that a close seal is maintained. The dimension D indicates the circumferential distance between the side face 22 and the top of the stiffener 36. The dimensions A and D are optimised to provide sufficient flexibility in the flap 38, while minimising the stresses in the adhesive joint between the seal strip 26 and the annulus filler. The dimensions A and D are also important to ensure that the stiffener 36 cannot migrate past the side face 22 and “knife” itself outwards, resulting in the loss of the seal. This “knifing” can occur if the stiffener is not supported sufficiently firmly. The centrifugal forces cause the stiffener to be forced outwards, and it may cut through the rubber and be released.

Dimension C shows the thickness of the rubber overlying the stiffener adjacent the aerofoil surface. This thickness must be sufficient to prevent the stiffener from breaking through and scratching the aerofoil surface.

Large diameter, swept fan blades have a steep blade angle α from mid-chord rearwards to the trailing edge of the blade. If the seal strip presents the same angle to the blade surface along its whole length, there is a risk that part of the seal strip may become jammed against the blade during a run-down in speed, or conversely may “flip” through the gap between the annulus filler and the blade during a run-up in speed.

To prevent this, the angle θ varies along the length of the seal strip, as illustrated by FIG. 3 (approximately at mid-chord) and FIG. 4 (close to the trailing edge). This varying shape allows the seal to conform to the fan blade shape during build and during all running conditions, ensuring a good sealing between the blade and the seal and also ensuring that the filler is built centrally between the fan blades. By varying the angle the size of the channel between the seal and the fan blade is minimised, thus maximising the aerodynamic efficiency of the assembly.

Also, in contrast to known seals, the position of the seal strip relative to the side face varies along the length of the seal strip. This is shown in FIGS. 5, 6 and 7. In FIG. 5, the bonding platform 54 is bonded in use to the annulus filler lid 14. The flap 38 of the seal strip projects from the bonding platform 54. An additional seal portion 58 is bonded in use beneath the leading edge of the annulus filler lid 14, and provides a seal between the annulus filler 12 and the spinner fairing (not shown). The varying position of the flap 38 relative to the bonding platform 54 is clearly visible in FIG. 5. The arrows VI-VI and VII-VII indicate the positions of the cross-sectional views of FIGS. 6 and 7, which show this variation in more detail.

The dimension D is relatively small towards the forward end of the seal strip 26 (FIG. 6), and relatively large towards its rearward end (FIG. 7). This arrangement has the further advantage that the gap E between the side face 22 of the annulus filler 12 and the surface 40 of the adjacent blade 42 is substantially constant, and relatively small. A large gap E would increase the risk of misalignment of the annulus filler 12 on assembly.

By tuning the relative stiffness of the pressure and suction side seals, the seals can be used to guide the filler into position between the fan blades during build, and to ensure that it locates in the correct position between the two blades. In this embodiment, the stiffness of the suction side seal strip 26 is designed to be slightly higher than the stiffness of the pressure side seal strip 28.

It will be appreciated that various modifications are possible to the embodiment described in this specification, without departing from the spirit and scope of the claimed invention.

For example, the seal strip 26 may be mounted on the annulus filler 12 by mechanical fasteners or by any other convenient method.

The body 32 of the seal strip 26 may be formed of any suitable resilient material. To suit certain manufacturing methods, the stiffener 36 may be coated on one side only with resilient material, instead of being embedded in it.

The seal strips may be formed in composite material, incorporating an integral stiffener. The seal strip may form an integral part of a larger composite component.

The stiffener 36 may be formed of a suitable non-metallic material. It may be formed in a single piece, or in several segments along the length of the seal strip 26. Although the invention is particularly suited to use in annulus fillers of fan stages, it could equally well be applied to any other application in which a varying gap has to be sealed. Such applications may include others in which the components are subjected to centrifugal loads, but may also include non-rotating structures such as the fan outlet guide vane stage of a gas turbine engine, in which the gaps between stationary vanes are bridged by infill panels which define the inner wall of a flow annulus.

Claims

1. A stage for a gas turbine engine comprising a plurality of circumferentially spaced apart radially extending aerofoils, a plurality of annulus fillers being provided to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage, each annulus filler having opposite side faces which are spaced circumferentially from the adjacent aerofoils and which correspond in profile therewith, resilient seal strips each including a stiffener being mounted adjacent the opposite side faces of the annulus fillers, characterised in that the stiffener has three-dimensional curvature.

2. A stage as in claim 1, in which the stiffener has curvature in the radial, axial and tangential directions.

3. A stage as in claim 1, in which each annulus filler bridges a space between a suction surface of one aerofoil and a pressure surface of an adjacent aerofoil, and in which the seal strip adjacent the suction surface is stiffer than the seal strip adjacent the pressure surface.

4. A stage as in claim 1, in which each annulus filler bridges a space between a suction surface of one aerofoil and a pressure surface of an adjacent aerofoil, and in which the seal strip adjacent the pressure surface is stiffer than the seal strip adjacent the suction surface.

5. A stage as in claim 1, in which each seal strip is mounted adjacent the respective side face of the annulus filler so as to define an angle between the seal strip and the respective side face, and in which the angle for at least one seal strip varies along the length of that seal strip.

6. A stage as in claim 1, in which each seal strip is mounted adjacent the respective side face of the annulus filler so as to define a circumferential offset between the seal strip and the respective side face, and in which the offset for at least one seal strip varies along the length of that seal strip.

7. A stage as in claim 6, in which the offset is at a minimum adjacent the leading edge of the aerofoils and is at a maximum adjacent the trailing edge of the aerofoils.

8. A stage as in claim 1, in which the depth of at least one stiffener varies along the length of its associated seal strip.

9. A stage as in claim 8, in which the depth varies such that the distances from the bottom of the seal strip to the bottom of the stiffener, and from the top of the stiffener to the top of the seal strip, are constant along the length of the seal strip.

10. A stage as in claim 1, in which the seal strips are adhesively mounted adjacent the opposite side faces of the annulus fillers.

11. A stage as in claim 10, in which the radial and tangential distances between the stiffeners and their respective side faces have been optimised to minimise the stress in the adhesive joints.

12. A stage as in claim 1, in which each stiffener is coated in resilient material only on the side adjacent its respective aerofoil.

13. A stage as in claim 1, in which each stiffener is completely embedded in resilient material.

14. A stage as in claim 12, in which the resilient material is rubber.

15. A stage as in claim 1, in which the stiffener is manufactured as an integral part of a composite seal strip.

16. A stage as in claim 1, in which the seal strips are manufactured as an integral part of a composite component.

17. A stage as in claim 1, in which the aerofoils are stator vanes.

18. A stage as in claim 1, in which the aerofoils are rotor blades.

19. An annulus filler for bridging in use the space between two adjacent aerofoils of a gas turbine engine to define an inner wall of a flow annulus through the stage, the annulus filler having opposite side faces, resilient seal strips each including a stiffener being mounted adjacent the opposite side faces of the annulus filler, characterised in that the stiffener has three-dimensional curvature.

20. An annulus filler as in claim 19, in which the stiffener has curvature in the radial, axial and tangential directions.

21. An annulus filler as in claim 19, in which in use the annulus filler bridges a space between a suction surface of one aerofoil and a pressure surface of an adjacent aerofoil, and in which the seal strip adjacent the suction surface in use is stiffer than the seal strip adjacent the pressure surface in use.

22. An annulus filler as in claim 19, in which in use the annulus filler bridges a space between a suction surface of one aerofoil and a pressure surface in use of an adjacent aerofoil, and in which the seal strip adjacent the pressure surface is stiffer than the seal strip adjacent the suction surface in use.

23. An annulus filler as in claim 19, in which each seal strip is mounted adjacent the respective side face of the annulus filler so as to define an angle between the seal strip and the respective side face, and in which the angle for at least one seal strip varies along the length of that seal strip.

24. An annulus filler as in claim 19, in which each seal strip is mounted adjacent the respective side face of the annulus filler so as to define a circumferential offset between the seal strip and the respective side face, and in which the offset for at least one seal strip varies along the length of that seal strip.

25. An annulus filler as in claim 24, in which in use the offset is at a minimum adjacent the leading edge of the aerofoils and is at a maximum adjacent the trailing edge of the aerofoils.

26. An annulus filler as in claim 19, in which the depth of at least one stiffener varies along the length of its associated seal strip.

27. An annulus filler as in claim 26, in which the depth varies such that the distances from the bottom of the seal strip to the bottom of the stiffener, and from the top of the stiffener to the top of the seal strip, are constant along the length of the seal strip.

28. An annulus filler as in claim 19, in which the seal strips are adhesively mounted adjacent the opposite side faces of the annulus filler.

29. An annulus filler as in claim 28, in which the radial and tangential distances between the stiffeners and their respective side faces have been optimised to minimise the stress in the adhesive joints.

30. An annulus filler as in claim 19, in which each stiffener is completely embedded in resilient material.

31. An annulus filler as in claim 30, in which the resilient material is rubber.

32. An annulus filler as in claim 19, in which the stiffener is manufactured as an integral part of a composite seal strip.

33. An annulus filler as in claim 19, in which the seal strips are manufactured as an integral part of a composite component.

34. A seal strip for an annulus filler of a gas turbine engine, the seal strip including a stiffener, characterised in that the stiffener has three-dimensional curvature.

35. A seal strip as in claim 34, in which the stiffener has curvature in the radial, axial and tangential directions.

36. A seal strip as in claim 34, which in use is mounted adjacent a side face of an annulus filler so as to define an angle between the seal strip and the side face, and in which the angle varies along the length of the seal strip.

37. A seal strip as in claim 34, which in use is mounted adjacent a side face of an annulus filler so as to define a circumferential offset between the seal strip and the side face, and in which the offset varies along the length of the seal strip.

38. A seal strip as in claim 34, in which the depth of the stiffener varies along the length of the seal strip.

39. A seal strip as in claim 38, in which the depth varies such that the distances from the bottom of the seal strip to the bottom of the stiffener, and from the top of the stiffener to the top of the seal strip, are constant along the length of the seal strip.

40. A seal strip as in claim 34, in which in use the seal strip is adhesively mounted adjacent a side face of an annulus filler.

41. A seal strip as in claim 40, in which the radial and tangential distances between the stiffener and the side face have been optimised to minimise the stress in the adhesive joint.

42. A seal strip as in claim 34, in which the stiffener is completely embedded in resilient material.

43. A seal strip as in claim 42, in which the resilient material is rubber.

44. A seal strip as in claim 34, in which the stiffener is manufactured as an integral part of a composite seal strip.