JP2000320677A - Seal ring - Google Patents

Abstract

(57) [Summary] [PROBLEMS] To improve airtightness by keeping a gap small from a low temperature to a high temperature. SOLUTION: A radial cut 13 is formed at one position in a circumferential direction.
Insert A groove 14 penetrating in the width direction is provided at a required depth at the center of one end face portion by the cut 13. At the center of the other end face by the cut, a protrusion 15 having a shape matching the concave groove 14 is provided. The projection 15 is fitted in the groove 14 so as to be slidable in the circumferential direction. The fitting between the concave groove 14 and the protrusion 15 is always maintained even when the assembly-side component thermally expands and contracts.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a seal ring used in a high-temperature environment such as an outer peripheral portion of a turbine housing of a jet engine.

[0002]

2. Description of the Related Art For example, a turbofan engine having a high bypass ratio, which is one of jet engines, has a fan 1, a compressor 2, a combustor 3, and a turbine 4 in that order from the front end, as schematically shown in FIG. Are arranged in the turbine axial direction (indicated by the axis O), and the fan 1 driven by the turbine 4
The air is taken in from the air inlet 5 by the rotation of, and most of the air is ejected from the bypass duct 6 to generate propulsion, and the remaining part is compressed by the compressor 2 driven by the turbine 4, and the compressed air The fuel is burned in the combustor 3 and the turbine 4 is driven by the high-speed combustion air flow.

The turbine 4 in the high bypass ratio turbofan engine is partially enlarged in FIG.
It has a moving blade 4a and a stationary blade 4b as turbine blades.
A seal ring 9 is assembled between a turbine housing 7 located on the outer periphery of a and a shroud 8 outside the turbine housing 7 to prevent air flowing in the turbine housing 7 from leaking outside the turbine housing 7.

[0004] Since the seal ring 9 and the turbine housing 7 become high in temperature during operation and thermally expand, the seal ring 9 assembled on the outer periphery of the turbine housing 7 has an example in FIG. As shown in the drawing, a cut 10 oblique to the thickness direction is made, or as shown in FIG. 6, a cut 11 having a crank shape is made to follow the thermal expansion of the turbine housing 7 to avoid excessive stress generation. I can do it.

[0005]

However, the cuts 10 and 11 of the seal ring 9 need to be formed large in consideration of the thermal expansion of the seal ring 9. , There is a problem that the airtightness is reduced. On the other hand, in the case of the crank-shaped cut 11, even when the temperature is low, a part is engaged, so that airtightness can be maintained for a time. As shown by a two-dot chain line, when the end of the portion where the cut 11 is made undergoes thermal deformation relatively inward and outward, there is a problem that the gap increases and the airtightness decreases. This problem also applies to the case of the oblique cut 10.

Accordingly, an object of the present invention is to provide a seal ring capable of improving the airtightness by keeping the gap small from a low temperature to a high temperature.

[0007]

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems, the present invention forms a required elongation allowance by making a cut in the circumferential direction at one location in the circumferential direction. A groove having a required depth is provided at the center in the thickness direction of one end face so as to penetrate in the width direction, and matches the groove at the center in the thickness direction of the other end face formed by the cut. The structure is provided with a protrusion.

Since the projection is slidably fitted in the groove, the engagement between the groove and the projection is maintained even at a low temperature or at a high temperature. The relative displacement of the part inward and outward is prevented. Therefore, since only the gap for sliding between the concave groove and the protrusion can be used as the gap, high airtightness is maintained.

In addition, the airtightness can be further improved by adopting a structure in which a plurality of combinations of the concave groove and the convexity are provided.

[0010]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows an embodiment of the present invention. As shown in FIG. 4, in a seal ring 12 used in a high-temperature environment such as an outer peripheral portion of a turbine housing 7, one seal ring in a circumferential direction is provided. A notch 13 along the thickness direction (radial direction) is formed at a place to form a required elongation allowance e. Is provided so as to penetrate in the width direction, and a projection 15 having a shape matching the concave groove 14 is slidable in the circumferential direction at the center in the thickness direction of the other end face formed by the cut 13. It is configured to be inserted into a fitted state.

The seal ring 12 of the present invention has a cut 13
Since the concave groove 14 and the projection 15 provided in the portion are slidably fitted, even if the component on the assembly side undergoes thermal expansion or thermal contraction, the concave groove 14 and the projection 15 Following deformation can be performed while maintaining the fitted state. Further, even if the end on the side of the concave groove 14 and the end on the side of the protrusion 15 are relatively thermally deformed inward and outward due to uneven pressure conditions and temperature distribution between the inside and outside of the assembled portion, this thermal deformation is not affected. This can be prevented by fitting the concave groove 14 and the projection 15. Therefore, since the gap is only a minimum gap for the sliding of the concave groove 14 and the protrusion 15, high airtightness can be maintained from a low temperature to a high temperature.

Next, FIG. 2 shows another embodiment of the present invention. In a seal ring 12 having the same structure as that shown in FIG. Are provided at a plurality of places (two places in the figure) in the thickness direction.

As shown in FIG. 2, since a plurality of fitting structures for the concave grooves 14 and the protrusions 15 can be provided in the thickness direction, airtightness can be further improved, which is advantageous.

It should be noted that the cross-sectional shape in the thickness direction of the seal ring 12 can be selected to be an arbitrary shape according to the situation of the assembled portion. ,
Of course, various changes can be made without departing from the scope of the present invention.

[0016]

As described above, according to the seal ring of the present invention, a notch along the thickness direction is formed at one location in the circumferential direction to form a required extension allowance. At the center in the thickness direction of the end face portion, a groove having a required depth is provided so as to penetrate in the width direction, and at the center in the thickness direction of the other end face portion formed by the cut, a protrusion corresponding to the groove is provided. Is provided, so that the fitting state between the groove and the protrusion can be always maintained, so that high airtightness can be maintained from a low temperature to a high temperature, and the groove and the protrusion can be maintained. By providing a configuration in which a plurality of combinations are provided, an excellent effect such as that airtightness can be further improved is exhibited.

[Brief description of the drawings]

FIG. 1 is a partial view showing one embodiment of a seal ring of the present invention.

FIG. 2 is a partial view showing another embodiment of the present invention.

FIG. 3 is a schematic diagram of a high bypass turbofan engine showing an example of a jet engine.

FIG. 4 shows an example of an assembling position of a seal ring.
FIG.

FIG. 5 is a partial view showing an example of a conventional seal ring.

FIG. 6 is a partial view showing another example of a conventional seal ring.

[Explanation of symbols]

 12 seal ring 13 cut 14 concave groove 15 protrusion e elongation allowance

Claims (2)

[Claims] 1. A required extension is formed by making a cut in the thickness direction at one location in the circumferential direction, and a recess of a required depth is formed at the center in the thickness direction of one end face formed by the cut. A seal ring, wherein a groove is provided so as to penetrate in the width direction, and a projection corresponding to the concave groove is provided at a center in a thickness direction of the other end face formed by the cut. 2. The seal ring according to claim 1, wherein a plurality of combinations of the grooves and the protrusions are provided.