JP3104436B2 - Gas turbine combustor support structure - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a support structure for a gas turbine combustor, and more particularly to an improvement in a support structure for a high temperature gas turbine combustor having a high combustor outlet gas temperature, for example, a combustor liner.

[0002]

2. Description of the Related Art A conventional support structure for a combustor will be described with reference to FIGS.
A spring 3 manufactured by bending a thin plate into an arc shape is attached to the outer peripheral surface of the end of the liner 1 on the transition piece 2 side. Spring 3
A number of elongated slits 4 are cut in the arc-shaped portion of the liner 1 in the axial direction, and each spring is integrated with the rear end 5 of the spring and fixed to the liner 1 by spot welding (6).
Is a spot weld). The outer diameter of the spring 3 is the transition piece inlet inner wall 7.
Since it is made larger than the inner diameter of the spring 3, when it is inserted into the transition piece 2, it comes into elastic contact with the transition piece entrance inner wall 7 near the top 8 of the spring 3 and depends on the magnitude of the spring constant of the spring 3. Thus, a reaction force acts on the spring 3.

Accordingly, the liner 1 is structured to be slidable in the axial direction, to allow elongation due to thermal expansion, to reduce the generation of thermal stress, and to suppress the vibration of the liner 1 by its spring action. The structure described in Japanese Utility Model Publication No. 63-2782 is essentially the same from the viewpoint of liner support.

However, such a structure cannot prevent the air A from flowing into the transition piece 2 from the outside of the liner 1 through the elongated slits 4 cut in the axial direction. A structure for preventing the inflow of the air A is described in Japanese Utility Model Laid-Open No. 63-71433. Its structure consists of two circular springs.
It is a double leaf spring that does not overlap vertically with slits that are elongated in the axial direction. For this reason, the other springs close the upper and lower slits, preventing air from flowing from the outside of the liner into the transition piece through the slits.

[0005]

In such a support structure, it is possible to eliminate almost no air flowing from the outside of the liner into the transition piece through the elongated slits cut in the axial direction of the spring. . However, it became clear that there was a problem from the viewpoint of the rigidity and wear resistance of the spring.

That is, the spring requires a certain degree of rigidity in order to suppress the vibration of the combustor. However, if the rigidity is too large, assembly or disassembly becomes impossible, or elongation due to thermal expansion cannot be sufficiently absorbed. In order to obtain the same rigidity as a single spring,
It is necessary to have the same thickness as a single sheet in a state where the sheets are overlapped doubly. Looking at one spring and one spring that are doubled,
Its thickness is almost half that of a single spring. However, during operation of the gas turbine, the combustor vibrates constantly, so that the vicinity of the top of the spring which is in elastic contact is constantly worn. Since the reduction in the thickness of the spring due to wear is proportional to the time during which the spring is worn, when the springs are superimposed twice, the damage is caused in about half the time when a single spring is configured. .

SUMMARY OF THE INVENTION An object of the present invention is to substantially eliminate air flowing into the transition piece from the outside of the liner, and to provide combustion having both the rigidity and wear resistance of a spring required to support the liner with respect to the transition piece. The object is to provide a support structure for a vessel.

[0008]

In order to achieve the above-mentioned object, the present invention provides a method in which a spring provided on an outer peripheral surface of a transition piece side end of a liner has an outer diameter smaller than that of the spring and an axial length. Are provided with short springs, and axially elongated slits cut by the outer spring and the inner spring are shifted in the circumferential direction so that they do not overlap.

[0009]

With such a support structure, when the liner is inserted into the transition piece, the outer spring formed to be larger than the inner diameter of the transition piece inlet inner wall is deformed, and the vicinity of the top of the spring is elastically formed on the transition piece inlet inner wall. The outer diameter of the spring is reduced until it comes into contact. As the outer diameter becomes smaller, the outer spring elastically contacts and overlaps the small outer diameter spring provided inside the outer spring, or comes very close to the small outer diameter spring provided inside the outer spring. The gap between the spring and the inner spring is almost eliminated. Since the slit of the outer spring and the slit of the inner spring are displaced in the circumferential direction and do not overlap, in the assembled state with the liner inserted into the transition piece, the air flow path is almost closed, and from the outside of the liner It is possible to almost completely prevent air from flowing into the transition piece.

In such a state at the time of assembly,
The vibration of the combustor is suppressed only by the spring action of the outer spring. That is, only the outer spring contributes to the stiffness of the support spring, while the inner spring has little or no contribution to the stiffness of the spring. For this reason, the plate thickness of the outer spring required to obtain the required rigidity of the spring is the same as the conventional structure supported by one spring shown in FIG. 3 or FIG. In other words, compared to a structure in which the spring is doubled to eliminate the air flowing into the transition piece from the outside of the liner, the thickness of the single spring is about twice as large, and the thickness of the spring due to abrasion is increased. Reduces the life of the spring before it can be damaged by about twice.

In the above description, the supporting structure has been described by taking as an example the connecting portion of the combustor liner and the transition piece, but this can be applied to the connecting portion of other combustor parts.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to an example in which a combustor liner and a transition piece are joined. FIG. 5 shows a state where the liner 1 is about to be inserted into the transition piece 2. A spring 3 manufactured by bending a thin plate into an arc shape is attached to the outer peripheral surface of the end of the liner 1 on the transition piece 2 side. A number of elongated slits 4 are cut in the arc-shaped portion of the spring 3 in the axial direction of the liner 1, and each spring is integrated at a spring rear end 5 and fixed to the liner 1 by spot welding.
(6 is a spot weld). The outer diameter of the spring 3 is made larger than the inner diameter of the transition piece inlet inner wall 7. Between the liner 1 inside the spring 3 is mounted a spring 3 'which is also made by bending a thin plate into an arc. The arc-shaped portion of the inner spring 3 'is also provided with a number of elongated slits 4' in the axial direction of the liner 1, and each spring is integrated at the rear end 5 'of the spring, and is fixed to the liner 1 by spot welding. (6 'is a spot weld). The outer diameter of the inner spring 3 ′ is substantially equal to the inner diameter of the transition piece inlet inner wall 7 minus the thickness of the outer spring 3. The axial length of the inner spring 3 ′ is shorter than the axial length of the outer spring 3, and the inner spring 3 ′ is sandwiched between the outer spring 3 and the liner 1 so that the rear end of the spring Fixed at 5 '. The portions where the outer springs 3 and the inner springs 3 'rise from the rear ends 5, 5' of the inner springs 3 to the arc-shaped portions having the slits 4, 4 'are located at the same position in the axial direction of the liner 1. I have. The positional relationship between the slit 4 cut by the outer spring 3 and the slit 4 'cut by the inner spring 3' is shifted in the circumferential direction, and the slits do not overlap.

FIGS. 1 and 2 show a state where the liner 1 is inserted into the transition piece 2 and assembled. The outer spring 3 is deformed until the vicinity of its top elastically contacts the transition piece inlet inner wall 7, and its outer diameter becomes smaller. The inner spring 3 'is made so that its outer diameter is substantially equal to the inner diameter of the transition piece inlet inner wall 7 minus the thickness of the outer spring 3, so that the liner 1 is inserted into the transition piece 2. In a state where the outer diameter of the outer spring 3 is reduced, the outer spring 3 just elastically contacts and overlaps the outer spring 3 as shown in FIG. 1 or almost overlaps with the outer spring 3 as shown in FIG. There are no gaps. Since the slits 4 of the outer spring 3 and the slits 4 'of the inner spring 3' are shifted in the circumferential direction and the slits do not overlap with each other, there is almost no flow path through which air flows from the outside of the liner 1 to the inside of the transition piece 2. Gone,
Very little air will leak.

As described above, with the liner 1 inserted into the transition piece 2 and assembled, the outer spring 3 and the inner spring 3 '
Are elastically in contact with each other and overlap, or there is almost no gap, so that the liner 1 is supported on the transition piece 2 only by the outer spring 3. Thus, the vibration of the combustor is suppressed only by the spring action of the outer spring 3, that is, the stiffness of the spring. The spring action of the inner spring 3 'acts only as an absorption when the liner 1 or the transition piece 2 is deformed. For this reason, only the outer spring 3 obtains the rigidity of the spring required to support the liner 1, and its plate thickness is determined by the single spring 3 shown in FIG. 3 or FIG. It becomes the same as the conventional structure to support. as a result,
The period during which the spring 3 is damaged due to a reduction in the thickness of the spring 3 due to wear caused by the vibration of the combustor is equivalent to that of the conventional one.

In the support structure in which the double springs are overlapped from the beginning, the two springs are stacked to support the liner with respect to the transition piece with the rigidity of the two springs, as shown in FIG. 3 or FIG.
It is necessary to make the thickness of the springs 3 the same. That is, 2
The thickness of each of the one and one springs that are superimposed on each other is approximately half that of the case where the liner 1 is supported by one spring 3. Since the period of time during which the thickness of the spring decreases due to wear and leads to damage is proportional to the thickness, the life of the spring is almost half that of the support structure of the present invention.

As described above, the support structure of the present invention can substantially eliminate air flowing into the transition piece from the outside of the liner, and also requires the rigidity of the spring required to support the liner with respect to the transition piece. And abrasion resistance can be satisfied.

FIGS. 6 and 7 show an embodiment in which the outer spring 3 and the inner spring 3 'are combined with springs having shapes different from those shown in FIG. Although the shape of the arcuate portion of the spring is different, the configuration and operation are the same as in FIG. 5, and the same effect is obtained.

[0018]

According to the present invention, the flow path through which air flows from the outside of the liner to the inside of the transition piece can be almost eliminated, so that very little air flows and the liner is supported by the transition piece. Since the outer spring is made of a single spring, the required rigidity and wear resistance of the spring can be satisfied.

In the above description, the supporting structure has been described by taking as an example the connecting portion of the combustor liner and the transition piece. However, the cylindrical component constituting the combustor is replaced by a cylindrical component having a slightly larger inner diameter. This is a support structure that can be applied everywhere as long as it is a coupling portion to be inserted into the connector.

[Brief description of the drawings]

FIG. 1 is a cross-sectional view showing one embodiment of a support structure of the present invention in a state where a combustor liner is inserted into a transition piece.

FIG. 2 is a sectional view showing an embodiment of the support structure of the present invention in a state where a combustor liner is inserted into a transition piece.

FIG. 3 is a partially cutaway view of a conventional support structure with a combustor liner inserted into a transition piece.

FIG. 4 is a partially cutaway view of a conventional support structure with a combustor liner inserted into a transition piece.

FIG. 5 is a sectional view and a front view showing an embodiment of the support structure of the present invention in a state where a combustor liner is about to be inserted into a transition piece.

FIG. 6 is a sectional view showing another embodiment of the support structure of the present invention in a state where the combustor liner is about to be inserted into the transition piece.

FIG. 7 is a sectional view showing another embodiment of the support structure of the present invention in a state where the combustor liner is about to be inserted into the transition piece.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Liner, 2 ... transition piece, 3, 3 '... Spring, 4, 4' ... Slit, 5, 5 '... Spring rear end part, 6, 6' ... Spot welding part, 7 ... Transition pipe entrance inner wall, 8 ... the top of the spring, A ... air.

──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Shigeyuki Akatsu 502 Kandate-cho, Tsuchiura-shi, Ibaraki Pref. Machinery Research Laboratory, Hitachi, Ltd. Hitachi Works Hitachi Works (72) Inventor Kazuyuki Ito 4026 Kuji-cho, Hitachi City, Ibaraki Prefecture Hitachi Works, Ltd.Hitachi Research Laboratory Co., Ltd. (72) Inventor Tamio 502 Kandachicho, Tsuchiura City, Ibaraki Prefecture, Hitachi Machinery Research Institute (72) Inventor Hiroshi Inoue 502, Kandate-cho, Tsuchiura-shi, Ibaraki Pref. In Hitachi, Ltd.Mechanical Laboratory (72) Inventor Shohei Yoshida 502, Kantate-cho, Tsuchiura-City, Ibaraki Pref.Inc. Satoshi 502, Kandate-cho, Tsuchiura-city, Ibaraki Pref.Hitachi, Ltd.Mechanical Research Laboratory (56) References Japanese Utility Model Application Showa 63-17959 (JP, U) Japanese Utility Model Application Showa 63-71433 (JP, U) Japanese Utility Model Application Showa 63-7282 (JP, Y2) (58) Field surveyed (Int. Cl. ⁷ , DB name) F02C 7/20 F23R 3/60

Claims (1)

(57) [Claims] 1. A joint for inserting a cylindrical part of a gas turbine combustor into a cylindrical part having a slightly larger inner diameter than the cylindrical part, and an annular gap between the inserted part and the inserted part. A spring having a convex arc that can elastically contact the inner wall of the component to be inserted is fixed to an outer wall of a rear end portion of the component into which the spring is inserted, and a rear end portion of the spring and the component to be inserted. Between the outer walls, a convex arc spring whose axial length is shorter than that of the spring and whose outer diameter is substantially equal to the inner diameter of the component to be inserted minus the plate thickness of the spring is installed. A support structure for a gas turbine combustor, wherein the spring is fixed to an outer wall at a rear end portion of the component to be inserted like the spring so that axial slits of the spring do not overlap inside and outside.