Seal for turbofan engine

Abstract

A seal for sealing a gap between a vane and a liner of an outlet guide vane is provided. The seal includes: a joint section for joining with the liner; a flexible fillet section elongated from the joint section and tapering toward a tip so as to form a round corner between the vane and the liner when the tip is placed in contact with the vane; and a flexible rib section projecting from an inner surface and so dimensioned as to get in contact with an upper surface of an external structure for securing the vane to keep gas tightness.

Claims

1. A seal for sealing a gap between a vane and a liner of an outlet guide vane, comprising: a joint section for joining with the liner; a flexible fillet section elongated from the joint section and tapering toward a tip so as to form a round corner between the vane and the liner when the tip is placed in contact with the vane; and a flexible rib section projecting from an inner surface and so dimensioned as to get in contact with an upper surface of an external structure for securing the vane to keep gas tightness.

2. The seal of claim 1, wherein the rib section comprises a shape of a cylindrical column, an elliptic column, a polygonal column, or a fillet shape tapering toward a tip.

3. The seal of claim 1, wherein the rib section is hollow so as to facilitate elastic crush.

4. The seal of claim 1, wherein the fillet section and the rib section are formed in a unitary body.

5. The seal of claim 1, wherein the fillet section is curved upward.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a schematic sectional view of a turbofan engine.

(2) FIG. 2 is a perspective view of an outlet guide vane into which seals are integrated in accordance with an embodiment.

(3) FIG. 3A is a partial sectional view of the outlet guide vane, particularly showing a relation between the seal and a structure for securing the vane.

(4) FIG. 3B is a partial sectional view of the outlet guide vane, showing a magnified view of the seal in particular.

(5) FIG. 4 is a sectional view of the seal with a part of a liner.

(6) FIG. 5 is a sectional view of the seal in accordance with a modified example.

(7) FIG. 6 is a sectional view of the seal in accordance with another modified example.

(8) FIG. 7 is a sectional view of the seal in accordance with still another modified example.

DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS

(9) Exemplary embodiments will be described hereinafter with reference to the appended drawings. It is particularly noted that these drawings are not always drawn to scale exactly and therefore dimensional relations among elements are not limited to those shown therein.

(10) Referring to FIG. 1, a turbofan engine 1 is, as an example, comprised of a fan 3 at its center, and an inner wall of a nacelle 5 surrounding its circumference and a core portion 7 define a bypass duct. Part a of an airflow generated by the fan 3 flows into a low-pressure compressor 9 and is used by combustion in the engine but another part b thereof flows into the bypass duct. The part b of the airflow passing through the bypass duct is rectified by outlet guide vanes comprised of a plurality of vanes 11 and then gushes out rearward.

(11) Referring to FIG. 2, each vane 11 is a plate-like structure having an airfoil shape for airflow rectification and being elongated in the radial direction. Its outer end is pinched by a support structure 13, and its inner end is pinched by a similar support structure 15, thereby being fixed to the nacelle 5 and the core portion 7.

(12) Adjacent to the structure 13 for fixing the outer end, having its edge in contact with a face of the vane 11, an outer liner 17 is disposed. Similarly, adjacent to the structure 15 for fixing the inner end, having its edge in contact with the face of the vane 11, an inner liner 19 is disposed. Plural combinations of the vanes 11 and the liners 17, 19 are arranged circumferentially to meet side by side, thereby constituting a circular structure. The plurality of outer liners 17 arranged in a cylindrical shape constitutes a part of the inner wall of the nacelle 5, and the plurality of inner liners 19 similarly constitutes a part of the outer wall of the core portion. The outer liners 17 and the inner liners 19 thus define the bypass duct.

(13) Referring to FIGS. 3A and 3B in combination with FIG. 2, a seal 21 of the present embodiment is used for sealing a gap between the inner liner 19 and the vane 11 for example. Of course it may be applied to a gap between the outer liner 17 and the vane 11 or used in order to seal any other arbitrary gaps. An example where the seal is applied to the inner liner 19 will be described hereinafter but is of course not limiting.

(14) Referring mainly to FIG. 3A and FIG. 3B, while the inner end lie of the vane 11 is pinched by the structure 15 for fixing the inner end as described above, the structure 15 has a flat top face just above the inner end lie. The seal 21 has its tip in contact with the surface of a face of the vane 11 and as well gets in contact with this top face, thereby sealing airflow.

(15) Referring to FIG. 4, the seal 21 is combined with an end of the inner liner 19 and then used. The seal 21 is comprised of a joint section 23, which may have a proper structure adapted to combination with the inner liner 19. Such a structure may be either a proper concave-convex as shown in the drawing for the purpose of engagement or any other structure increasing contact area. Increase in contact area is advantageous for bonding the seal 21 with the inner liner 19.

(16) The seal 21 around its proximal end is comparable in thickness to the inner liner 19 for example but has a fillet section 27 that makes gradually thinner toward its tip. The seal 21 is, at least at the fillet section 27, flexible but may alternatively be totally flexible. To give flexibility thereto, an elastomer such as synthetic rubber may be applied to the seal 21. The fillet section 27 is so flexible to warp upward when it gets contact with the vane 11, thereby forming a round corner between the inner liner 19 and the vane 11. To make it easy to warp upward, the fillet section 27 may be formed in advance to be curved upward as shown in the drawing.

(17) In addition, the seal 21 has a rib section 25 projecting from its inner surface. The rib section 25 is a projection along the lengthwise direction of the seal 21 and spans substantially its entire length. The rib section 25 is also flexible so as to elastically crush when it gets contact with the top face of the structure 15 for fixing the vane 11 and then comes in close contact therewith. The rib section 25 thus keeps gas tightness in combination with the top face of the structure 15. Proper position and dimensions are selected in the rib section 25 in accordance with the position of the top face of the structure 15 and the distance from the seal 21 to the top face of the structure 15.

(18) The rib section 25 and the fillet section 27 are preferably formed in a unitary body as shown in FIG. 4. However, they may be separate bodies like as a rib 25t and a fillet 27f in a seal 21 as shown in FIG. 5. In this case, the rib section 25t is directly joined with the inner liner 19.

(19) To a shape for the rib section applicable is a hollow and cylindrical column having a hole 25h in its interior in order to facilitate elastic crush, but a solid rib section 25s as shown in FIG. 6 may be also applicable. Alternatively, instead of the column, an elliptic column, a polygonal column, or any other proper shape may be selected. Still alternatively, as shown in FIG. 7, a fillet shape tapering toward a tip may be also applied to the rib section 25f. The rib section 25f may be properly warped so as to generate force pressing the fillet section 27 toward the vane 11 when it gets in contact with the structure 15.

(20) In any of the embodiments described above, the seal 21 is, in a state of being combined with the inner liner 19, served for assembly. When integrated into the outlet guide vane along with the inner liner 19, the fillet section 27 at its tip gets contact with the face of the vane 11 and then warps upward so as to form a round corner that is unlikely to disturb airflow. As the vane 11 is formed in a curved surface, any structures could hardly establish gas-tight contact throughout its total length. The fillet section 27 of the present embodiment is no exception. The rib section 25, however, gets in contact with the top face of the structure 15 so as to, in place of the fillet section 27, keep gas tightness. The seal 21 thereby successfully seals airflow in the bypass dust.

(21) More specifically, the seal of the present embodiment does not necessitate laborsome work but only require being attached to the liner and integrated in the outlet guide vane in order to seal airflow, and also does not cause turbulence in the airflow.

(22) Although certain embodiments have been described above, modifications and variations of the embodiments described above will occur to those skilled in the art, in light of the above teachings.

INDUSTRIAL APPLICABILITY

(23) A seal that merely requires being attached to a liner and, along with the liner and a vane, being integrated into outlet guide vanes is provided.