Stationary blade segment for compressor, and compressor

Abstract

To reduce stress acting on a stationary blade of a stationary blade segment of a compressor.SOLUTION: A stationary blade segment for a compressor according to at least one embodiment of the present disclosure includes: a plurality of stationary blades arranged in a circumferential direction, each of the blades including a blade-shaped part having a body surface oriented to one side in the circumferential direction and a back surface oriented to the other side in the circumferential direction, and an inner shroud connected to an end part of the blade shape part on a radially inner side; and a holder attached to the inner shrouds of the plurality of stationary blade. The holder satisfies at least one of a condition that a circumferential position of the end part on one side in the circumferential direction of a downstream engagement part is positioned on the other side in the circumferential direction relative to the circumferential position of the end part on the one side in the circumferential direction of an upstream engagement part, or a condition that a circumferential position of the end part on the other side in the circumferential direction of the upstream engagement part is positioned on the one side in the circumferential direction relative to the circumferential position of the end part on the other side in the circumferential direction of the downstream engagement part.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to a compressor stator vane segment and a compressor. [Background technology]

[0002] A gas turbine includes a compressor that compresses outside air to generate compressed air, a combustor that mixes fuel with the compressed air and burns it to generate combustion gas, and a turbine that is driven by the combustion gas.

[0003] Both the compressor and the rotor are axial flow fluid machines and include a rotor that rotates about a rotation axis and a casing that covers the rotor. The rotor has a rotor body that extends in an axial direction parallel to the rotation axis, and a plurality of rotor blade stages that are fixed to the outer periphery of the rotor body and arranged in the axial direction. A stator vane stage is fixed to the inner periphery of the casing at a position upstream of each rotor blade stage. One stator vane stage forms a stator vane ring in which a plurality of stator vanes are arranged in the circumferential direction and connected to each other. For assembly convenience, this stator vane ring is divided in the circumferential direction. Each of these circumferentially divided parts is generally called a stator vane segment. This stator vane segment is formed by connecting a plurality of stator vanes in the circumferential direction (see, for example, Patent Document 1). [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2015-121158 Summary of the Invention [Problem to be solved by the invention]

[0005] In the above-mentioned stator vane segments, the outer shrouds are connected to each other by outer connecting members, and the inner shrouds are connected to each other by inner connecting members. Circumferentially adjacent stator vane segments are attached to the compressor casing with the circumferential side surfaces of the inner shrouds of the stator vanes at the circumferential ends of each stator vane segment abutting against each other.

[0006] However, if a gap occurs between the side surfaces due to wear during use of the compressor, the fluid force from the fluid passing through the stator vane segments will cause the stator vane segments to move relative to the inner connecting member. As a result, the inner shroud located at the circumferential end of the stator vane segment will come into contact with the inner connecting member of the circumferentially adjacent stator vane segment, which may increase the mean stress on the stator vane body and lead to problems such as a shortened lifespan.

[0007] In view of the above, at least one embodiment of the present disclosure aims to reduce stress acting on stator vanes in a stator vane segment of a compressor. [Means for solving the problem]

[0008] (1) A compressor vane segment according to at least one embodiment of the present disclosure comprises: A compressor stator vane segment, comprising: a plurality of stator vanes arranged in the circumferential direction, each having an airfoil portion with a pressure surface facing one side in the circumferential direction and a suction surface facing the other side in the circumferential direction, and an inner shroud connected to an end of the airfoil portion on the radially inner side; a holder attached to the inner shroud of the plurality of vanes; Equipped with Each of the inner shrouds an upstream hook portion provided on the upstream side in the axial direction and adapted to engage with the holder; a downstream hook portion provided on the downstream side in the axial direction and adapted to engage with the holder; and The holder is an upstream engaging portion that engages with the upstream hook portion; a downstream engaging portion that engages with the downstream hook portion; and The holder is the circumferential position of the one end of the downstream engaging portion in the circumferential direction is located on the other side in the circumferential direction than the circumferential position of the one end of the upstream engaging portion in the circumferential direction, Or, the circumferential position of the other circumferential end of the upstream engaging portion is located on one side in the circumferential direction relative to the circumferential position of the other circumferential end of the downstream engaging portion; At least one of the following conditions is met.

[0009] (2) A compressor according to at least one embodiment of the present disclosure includes: a stator blade ring in which a plurality of stator blade segments having the configuration (1) above are arranged in the circumferential direction; Equipped with. [Effects of the Invention]

[0010] At least one embodiment of the present disclosure may reduce stresses on the vanes in a compressor vane segment. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment. [Figure 2] FIG. 1 is a front view of a stator vane stage (stator vane ring) according to some embodiments. [Figure 3] FIG. 2 is a perspective view of a stator vane segment according to some embodiments. [Figure 4A] FIG. 2 is a schematic cross-sectional view of an inner shroud and a connecting holder according to some embodiments, as viewed in the circumferential direction. [Figure 4B] 1 is a schematic cross-sectional view of a connecting holder according to some embodiments, viewed from the circumferential direction. FIG. [Figure 5] FIG. 4 is a schematic cross-sectional view of an outer shroud according to one embodiment taken along the line V in FIG. 3. [Figure 6]4B is a diagram for explaining the influence of fluid forces on a stator vane segment according to some embodiments, and is a schematic diagram corresponding to a cross section taken along the line AA in FIG. 4A. FIG. [Figure 7] 4B is a schematic diagram of a stator vane segment according to one embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. [Figure 8A] FIG. 8 is a diagram showing the vane segments shown in FIG. 7 arranged at intervals in the circumferential direction. [Figure 8B] FIG. 8 is a diagram showing two circumferentially adjacent stator vane segments, in which the two stator vane segments are the stator vane segments shown in FIG. 7. [Figure 9] 4B is a schematic diagram of a vane segment according to another embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. [Figure 10A] FIG. 10 is a diagram showing the vane segments shown in FIG. 9 arranged at intervals in the circumferential direction. [Figure 10B] 10 is a diagram showing two circumferentially adjacent stator vane segments, in which the two stator vane segments are the stator vane segments shown in FIG. 9. FIG. [Figure 11] 4B is a schematic diagram of a vane segment according to still another embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. [Figure 12A] FIG. 12 is a diagram showing the vane segments shown in FIG. 11 arranged at intervals in the circumferential direction. [Figure 12B] 12 is a diagram showing two circumferentially adjacent stator vane segments, in which the two stator vane segments are the stator vane segments shown in FIG. 11. FIG. DETAILED DESCRIPTION OF THE INVENTION

[0012] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present disclosure. For example, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement exactly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. For example, expressions representing shapes such as a square shape or a cylindrical shape not only represent shapes such as a square shape or a cylindrical shape in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0013] Hereinafter, an embodiment of an axial flow fluid machine to which a compressor stator vane segment according to an embodiment is applied will be described in detail with reference to the drawings.

[0014] FIG. 1 is a schematic configuration diagram of a gas turbine according to one embodiment. As shown in FIG. 1, the gas turbine 100 includes a compressor 1 that compresses outside air to generate compressed air, a plurality of combustors 6 that mix fuel from a fuel supply source with the compressed air and combust it to generate combustion gas, and a turbine 7 that is driven by the combustion gas.

[0015] The compressor 1 and the turbine 7 are both axial flow fluid machines and include rotors 2 and 8 that rotate about a rotational axis Ar and casings 5 ​​and 9 that cover the rotors 2 and 8. The compressor rotor 2 and the turbine rotor 8 rotate about the same rotational axis Ar and are connected to each other. A plurality of combustors 6 are fixed to the turbine casing 9 at equal intervals in a circumferential direction Dc around the rotational axis Ar. Hereinafter, the direction in which the rotational axis Ar extends is referred to as the axial direction Da, and the radial direction relative to the rotational axis Ar is simply referred to as the radial direction Dr. In addition, in the axial direction Da, the compressor 1 side with respect to the turbine 7 is referred to as the upstream side, and the turbine 7 side with respect to the compressor 1 is referred to as the downstream side.

[0016] The compressor rotor 2 has a rotor body 3 extending in the axial direction Da, and a plurality of rotor blade stages 4 fixed to the outer periphery of the rotor body 3 and aligned in the axial direction Da. On the inner periphery side of the compressor casing 5, a stator vane stage 10 is fixed at a position upstream of each rotor blade stage 4.

[0017] FIG. 2 is a front view of a stator blade stage (stator blade ring) according to some embodiments. As shown in Fig. 2, one stator vane stage 10 is formed as a stator vane ring in which a plurality of stator vanes 20 are arranged in an annular shape and connected to one another. For the convenience of assembly, this stator vane ring is divided in the circumferential direction. Each of these circumferentially divided parts constitutes a stator vane segment 11. This stator vane segment 11 is formed by arranging some of the stator vanes 20 that make up the stator vane ring in the circumferential direction Dc and connecting them to one another.

[0018] FIG. 3 is a perspective view of a stator vane segment according to some embodiments. FIG. 4A is a schematic cross-sectional view of an inner shroud and a connection holder according to some embodiments, as viewed in the circumferential direction. FIG. 4B is a schematic cross-sectional view of the connecting holder according to some embodiments, as viewed in the circumferential direction. FIG. 5 is a schematic cross-sectional view of an outer shroud according to one embodiment taken along the line V in FIG. 3 . FIG. 6 is a diagram for explaining the influence of fluid forces on a stator vane segment according to some embodiments, and is a schematic diagram corresponding to a cross section taken along the line AA in FIG. 4A. FIG. 7 is a schematic diagram of a stator vane segment according to one embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. 8A is a diagram showing the vane segments shown in FIG. 7 arranged at intervals in the circumferential direction. FIG. 8B is a diagram showing two circumferentially adjacent stator blade segments, and shows a case where the two stator blade segments are the stator blade segments shown in FIG. FIG. 9 is a schematic diagram of a stator vane segment according to another embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. 10A is a diagram showing the vane segments shown in FIG. 9 arranged at intervals in the circumferential direction. FIG. 10B is a diagram showing two circumferentially adjacent stator blade segments, and shows a case where the two stator blade segments are the stator blade segments shown in FIG. FIG. 11 is a schematic diagram of a stator vane segment according to yet another embodiment, corresponding to a cross section taken along the line AA in FIG. 4A. FIG. 12A is a diagram showing the vane segments shown in FIG. 11 arranged at intervals in the circumferential direction. FIG. 12B is a diagram showing two circumferentially adjacent stator blade segments, and shows a case where the two stator blade segments are the stator blade segments shown in FIG.

[0019] As shown in FIG. 3, the stator vane segment 11 according to some embodiments has a plurality of stator vanes 20 arranged in the circumferential direction Dc, a connecting holder (inner connecting member) 40 to which the radially inner portions of the plurality of stator vanes 20 are attached, and a connecting band (outer connecting member) 50 that connects the radially outer portions of the plurality of stator vanes 20 to each other in the circumferential direction Dc.

[0020] As shown in Figures 4A and 5, the stator vane 20 according to some embodiments has a stator vane body (airfoil portion) 21 extending in the radial direction Dr, an inner shroud 22 provided radially inside the stator vane body 21, and an outer shroud 32 provided radially outside the stator vane body 21.

[0021] (Inner shroud 22) 4A , an inner shroud 22 according to some embodiments includes a plate-shaped shroud main body 23 provided radially inside the vane main body 21 and extending in the circumferential direction Dc, a protruding portion 24 protruding radially inward from the shroud main body 23, an upstream lip portion 25 extending upstream from a side surface of the protruding portion 24 on the upstream side in the axial direction, and a downstream lip portion 27 extending downstream from a side surface of the protruding portion 24 on the downstream side in the axial direction. An upstream engagement groove 28 is formed between the shroud main body 23 and the upstream lip portion 25, and is recessed downstream and extends in the circumferential direction Dc. Furthermore, a downstream engagement groove 29 is formed between the shroud main body 23 and the downstream lip portion 27, and is recessed upstream and extends in the circumferential direction Dc. The groove bottoms of these engagement grooves 28, 29 are both formed by the side surface of the protruding portion 24 facing the axial direction Da.

[0022] 7, the side surface 22s in the circumferential direction Dc of the inner shroud 22, i.e., the side surface in the circumferential direction Dc of the shroud main body 23, the side surface in the circumferential direction Dc of the protruding portion 24, the side surface in the circumferential direction Dc of the upstream lip portion 25, and the side surface in the circumferential direction Dc of the downstream lip portion 27 are inclined with respect to the axial direction Da so as to move from one side to the other in the circumferential direction Dc as they move from the upstream side to the downstream side in the axial direction Da. That is, the shroud main body 23 of the inner shroud 22 shown in FIG. 7 has a parallelogram shape when viewed in the radial direction Dr.

[0023] In the embodiments shown in each of Figures 7 to 12B, the pressure surface 21P of the stator vane main body 21 faces one side of the circumferential direction Dc, and the suction surface 21S faces the other side of the circumferential direction Dc, as shown in Figure 6. In the embodiments shown in each of FIGS. 7 to 12B, the side surface 22s of the inner shroud 22 in the circumferential direction Dc is a flat surface without any steps.

[0024] 9 and 11, the side surface 22s in the circumferential direction Dc of the inner shroud 22 is located at the same position in the circumferential direction Dc on the upstream side in the axial direction Da and on the downstream side in the axial direction Da. That is, the shroud main body 23 of the inner shroud 22 shown in Fig. 9 and 11 has a rectangular shape when viewed in the radial direction Dr.

[0025] (Outer shroud 32) In some embodiments, the outer shroud 32 includes a plate-shaped shroud body 33 that is provided radially outside the vane body 21 and extends in the circumferential direction Dc, an upstream leg 34 that extends radially outward from an upstream portion of the shroud body 33, an upstream lip 35 that extends upstream from a radially outer end of the upstream leg 34, a downstream leg 36 that extends radially outward from a downstream portion of the shroud body 33, and a downstream lip 37 that extends downstream from the radially outer end of the downstream leg 36. A band groove 31 that is recessed from the radially outer side to the radially inner side and extends in the circumferential direction Dc is formed between the upstream leg 34 and the downstream leg 36. A portion of the connecting band 50 in the circumferential direction Dc fits into this band groove 31. The connecting band 50 is joined by welding or the like to the outer shrouds 32 of the stator blades 20 at least at both ends of the stator blade segment 11 in the circumferential direction Dc.

[0026] (connection holder 40) 4B , in some embodiments, the connecting holder 40 has a seal retaining portion 43 extending in the circumferential direction Dc, an upstream leg portion 44 formed along the upstream edge of the seal retaining portion 43 and extending radially outward, an upstream flange portion 45 extending downstream from the radially outer end of the upstream leg portion 44 and fitting into the upstream engagement groove 28 of the inner shroud 22, a downstream leg portion 46 formed along the downstream edge of the seal retaining portion 43 and extending radially outward, and a downstream flange portion 47 extending upstream from the radially outer end of the downstream leg portion 46 and fitting into the downstream engagement groove 29 of the inner shroud 22. A plurality of seal fins 48 extending in the circumferential direction Dc and providing a seal with the rotor body 3 ( FIG. 1 ) of the compressor rotor 2 are provided radially inside the seal retaining portion 43 at intervals in the axial direction Da. Between the upstream leg portion 44 and the downstream leg portion 46, a shroud storage groove 41 is formed, which is recessed radially inward and extends in the circumferential direction Dc. The groove bottom of this shroud storage groove 41 is formed by the seal retaining portion 43. That is, the bottom surface 41b (see FIG. 4B) of the shroud storage groove 41 is the surface on the radially outer side of the seal retaining portion in the radial direction Dr. When the multiple stator vanes 20 constituting the stator vane segment 11 are lined up in the circumferential direction Dc, the protrusion 24, upstream lip portion 25, and downstream lip portion 27 of the inner shroud 22 of each stator vane 20 fit into this shroud storage groove 41.

[0027] Within the shroud storage groove 41, a region recessed toward the upstream side in the axial direction and configured so that the upstream lip portion 25 of the inner shroud 22 of each stator blade 20 can be inserted therein is defined as an upstream engagement portion 41U. Within the shroud storage groove 41, a region recessed toward the downstream side in the axial direction and configured so that the downstream lip portion 27 of the inner shroud 22 of each stator blade 20 can be inserted therein is defined as a downstream engagement portion 41D. The upstream engaging portion 41U is a groove extending in the circumferential direction Dc and defined by a side wall surface 41Ui on the inside in the radial direction Dr, a side wall surface 41Uo on the outside in the radial direction Dr, and a bottom surface 41Uu on the upstream side in the axial direction Da. The downstream engaging portion 41D is a groove extending in the circumferential direction Dc and defined by a side wall surface 41Di on the inside in the radial direction Dr, a side wall surface 41Do on the outside in the radial direction Dr, and a bottom surface 41Dd on the downstream side in the axial direction Da.

[0028] The upstream leg 44 extends from the same position in the radial direction Dr as the bottom surface 41b of the shroud storage groove 41 to the same position in the radial direction Dr as the side wall surface 41Uo on the radially outer side of the upstream engagement portion 41U. Similarly, the downstream leg 46 extends from the same position in the radial direction Dr as the bottom surface 41b of the shroud storage groove 41 to the same position in the radial direction Dr as the side wall surface 41Do on the radially outer side of the downstream engagement portion 41D.

[0029] As shown in FIG. 4A , in some embodiments, the connecting holder 40 is connected to, for example, the inner shroud 22 a of the stator blade 20 a located at both ends of the circumferential direction Dc in the stator blade segment 11 by a pin 49, and restricts movement of the inner shroud 22 in the circumferential direction Dc relative to the connecting holder 40. In addition, the pin 49 is omitted from FIG. 6 and subsequent figures.

[0030] (Effect of fluid forces on stationary vane segments) The influence of fluid forces on the stator vane segment 11 will be described with reference to FIG. As described above, in the stator vane segment 11 according to some embodiments, the pressure surface 21P of the stator vane body 21 faces one side in the circumferential direction Dc, and the suction surface 21S faces the other side in the circumferential direction Dc. Generally, in the stator vane segment 11 of the compressor 1, the pressure is higher on the pressure surface 21P of the stator vane body 21 than on the suction surface 21S. The pressure difference between the pressure surface 21P and the suction surface 21S is greater on the axially upstream side. Therefore, in general, in the stator vane segment 11 of the compressor 1, a fluid force acts to press the stator vane body 21 in a direction from the pressure surface 21P to the suction surface 21S. However, since the pressure difference between the pressure surface 21P and the suction surface 21S is larger on the axial upstream side, a rotational force acts on each stator vane body 21 on the axial upstream side, tending to rotate the stator vane body 21 in a direction from the pressure surface 21P to the suction surface 21S, as shown by arrow a in FIG. 6.

[0031] Since a rotational force acts on each stator vane body 21 to rotate the stator vane body 21 as shown by arrow a, a rotational force acts on the entire group of multiple stator vane bodies 21 held by the connecting holder 40 such that one side of the circumferential direction Dc is directed axially upstream and the other side of the circumferential direction Dc is directed axially downstream, as shown by arrow b in Figure 6.

[0032] Generally, in the stator vane segment 11 of the compressor 1, at least a portion of either of the inner shrouds 22a of the stator vanes 20a located at both ends in the circumferential direction Dc protrudes in the circumferential direction Dc from the end of the connecting holder 40 in the circumferential direction Dc. For example, in the example shown in Fig. 6, the inner shroud 22a of the stator vane 20a located at one end in the circumferential direction Dc protrudes from the end of the connecting holder 40 in the circumferential direction Dc to one side in the circumferential direction Dc. The upstream flange portion 45 of the connecting holder 40 of the adjacent stator vane segment 11 on one side in the circumferential direction Dc is fitted into the upstream engagement groove 28 in the protruding portion of the inner shroud 22a.

[0033] Generally, in the stator vane segments 11 of the compressor 1, adjacent stator vane segments 11 in the circumferential direction Dc are attached to the casing 5 of the compressor 1 with the circumferential Dc side surfaces 22s of the inner shrouds 22a of the stator vanes 20a located at the ends of each stator vane segment 11 in the circumferential direction Dc abutting against each other.

[0034] However, if gaps occur between the side surfaces 22s due to wear during use of the compressor 1, the fluid force from the fluid passing through the stator vane segment 11 will cause the stator vane segment 11 to move relative to the connecting holder 40 as shown by arrow b in Figure 6, as described above. Therefore, in the stator vane 20a located at the end of the circumferential direction Dc of the stator vane segment 11, the groove bottom of the upstream engagement groove 28 and the upstream lip portion 25 of the inner shroud 22a protruding from the connecting holder 40 may come into contact with the upstream leg portion 44 and the upstream flange portion 45 of the connecting holder 40 of the adjacent stator vane segment 11 in the circumferential direction Dc, which may increase the average stress of the stator vane body 21 and lead to problems such as a shortened lifespan.

[0035] Therefore, in some embodiments, the stator vane segment 11 is configured as follows so that the portion of the inner shroud 22a protruding from the connecting holder 40 does not come into contact with the connecting holder 40 of the stator vane segment 11 adjacent in the circumferential direction Dc in the axial direction Da.

[0036] (When the shroud body 23 has a parallelogram shape) A case will be described in which the shape of the shroud main body 23 is a parallelogram when viewed from the radial direction Dr, like the inner shroud 22 shown in FIG. In such a stator vane segment 11, the corner portion 23e of the shroud body 23, which generally forms an acute corner portion when viewed from the radial direction Dr, protrudes from the connecting holder 40 in the circumferential direction Dc. Although not shown, in the conventional stator vane segments 11, this protruding corner portion 23e is adapted to be inserted into the connecting holders 40 of adjacent stator vane segments 11 in the circumferential direction Dc when assembled into the stator vane stage 10. The position in the circumferential direction Dc of the end portion of the connecting holder 40 in the circumferential direction Dc is the same in the axially upstream region and the axially downstream region.

[0037] As described above, a rotational force acts on the entire plurality of stator vane bodies 21 held by the connecting holder 40 such that the other side in the circumferential direction Dc moves toward the axial downstream side, as shown by arrow b in Fig. 6. Therefore, in the conventional stator vane segment 11, the axially downstream corner 23e of the inner shroud 22a located at the end on the other side in the circumferential direction Dc may come into contact in the axial direction Da with a region on one side in the circumferential direction Dc and on the axial downstream side of the connecting holder 40 of the adjacent stator vane segment 11 on the other side in the circumferential direction Dc.

[0038] Furthermore, in the conventional stator vane segment 11, the axially upstream corner 23e of the inner shroud 22a located at one end in the circumferential direction Dc may come into contact in the axial direction Da with the area on the other side in the circumferential direction Dc and axially upstream of the connecting holder 40 of the adjacent stator vane segment 11 on one side in the circumferential direction Dc.

[0039] 7 to 8B, in the stator vane segment 11 according to some embodiments, the position in the circumferential direction Dc of the end portion 41De on one side in the circumferential direction of the downstream engagement portion 41D is located on the other side in the circumferential direction Dc of the end portion 41Ue on one side in the circumferential direction Dc of the upstream engagement portion 41U. In other words, the position in the circumferential direction Dc of the end portion 41De on one side in the circumferential direction of the downstream engagement portion 41D is retracted to the other side in the circumferential direction Dc. This makes it possible to prevent the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc from coming into contact with the groove bottom of the downstream engagement groove 29 or the downstream lip portion 27 in the inner shroud 22a located on the other side of the adjacent stator vane segment 11 in the circumferential direction Dc.

[0040] 7 to 8B , in the stator vane segment 11 according to some embodiments, the position in the circumferential direction Dc of the end portion 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U is positioned to one side in the circumferential direction Dc of the end portion 41De on the other side in the circumferential direction Dc of the downstream engagement portion 41D. In other words, the position in the circumferential direction Dc of the end portion 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U is retracted to one side in the circumferential direction Dc. This makes it possible to prevent the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc from coming into contact with the groove bottom of the upstream engagement groove 28 or the upstream lip portion 25 in the inner shroud 22a located on the one side of the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc.

[0041] In some embodiments of the stator vane segment 11, as shown in Figures 7 to 8B, the circumferential position in the circumferential direction Dc of the end portion 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc may be the same as the circumferential position in the circumferential direction Dc of the end portion 27e on one side of the downstream lip portion 27 in the inner shroud 22a located on the furthest side in the circumferential direction Dc, or may be located on the other side of that position in the circumferential direction Dc. As a result, the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc does not come into contact with the groove bottom of the downstream engagement groove 29 or the downstream lip portion 27 in the inner shroud 22a located on the other side of the adjacent stator vane segment 11 in the circumferential direction Dc.

[0042] Furthermore, in some embodiments of the stator vane segment 11, as shown in Figures 7 to 8B, the position in the circumferential direction Dc of the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc may be the same as the position in the circumferential direction Dc of the end portion 25e on the other side of the upstream lip portion 25 in the circumferential direction Dc of the inner shroud 22a located on the other side most in the circumferential direction Dc, or may be located to one side of that position in the circumferential direction Dc. As a result, the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc does not come into contact with the groove bottom of the upstream engagement groove 28 or the upstream lip portion 25 in the inner shroud 22a located on the one side of the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc.

[0043] In addition, in order to set the circumferential position Dc of one end 41De of the downstream engagement portion 41D in the circumferential direction Dc to the above-mentioned position, the positions of one end of the downstream leg portion 46 and the downstream flange portion 47, which are radially outward in the radial direction Dr than the side wall surface 41Di on the inner side in the radial direction Dr of the downstream engagement portion 41D, may also be set to the above-mentioned position. Alternatively, in order to set the circumferential position Dc of one end 41De of the downstream engagement portion 41D in the circumferential direction Dc to the above-mentioned position, the positions of one end of the downstream leg portion 46 and the downstream flange portion 47 in the circumferential direction Dc that are radially outward from the bottom surface 41b of the shroud storage groove 41 may be set to the above-mentioned position.

[0044] Similarly, in order to set the circumferential position of the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc to the above-mentioned position, the positions of the other end portions in the circumferential direction Dc of the upstream leg portion 44 and the upstream flange portion 45, which are radially outwardly disposed in the radial direction Dr than the side wall surface 41Ui on the inner side in the radial direction Dr of the upstream engagement portion 41U, may be set to the above-mentioned positions. Alternatively, in order to set the circumferential position Dc of the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc to the above-mentioned position, the positions of the other ends in the circumferential direction Dc of the upstream leg portion 44 and the upstream flange portion 45, which are radially outer than the bottom surface 41b of the shroud storage groove 41, may be set to the above-mentioned positions.

[0045] (When the shroud body 23 has a rectangular shape: Part 1) A case where the shape of the shroud main body 23 is rectangular when viewed from the radial direction Dr, like the inner shroud 22 shown in FIG. 9, will be described. In such a stator vane segment 11, generally, one of the inner shrouds 22a located at both ends in the circumferential direction Dc protrudes in the circumferential direction Dc from the connecting holder 40. In the inner shroud 22 shown in Fig. 9, a part of the inner shroud 22a located at one end in the circumferential direction Dc protrudes from the connecting holder 40 to one side in the circumferential direction Dc. Although not shown, in the conventional stator vane segment 11, the portion of the inner shroud 22a protruding from the connecting holder 40 is inserted into the connecting holder 40 of the stator vane segment 11 adjacent in the circumferential direction Dc when assembled into the stator vane stage 10. The position in the circumferential direction Dc of the end of the connecting holder 40 in the circumferential direction Dc is the same in the axially upstream region and the axially downstream region.

[0046] As described above, a rotational force acts on the entire plurality of stator vane bodies 21 held by the connecting holder 40 such that the other side in the circumferential direction Dc moves toward the axial downstream side, as shown by arrow b in Fig. 6. Therefore, in the conventional stator vane segment 11, when a part of the inner shroud 22a protrudes from the connecting holder 40 to one side in the circumferential direction Dc as shown in Fig. 9, there is a risk that the axially upstream corner 23e of the inner shroud 22a located at the end on one side in the circumferential direction Dc may come into contact, in the axial direction Da, with a region on the other side in the circumferential direction Dc and upstream of the connecting holder 40 of the stator vane segment 11 adjacent on one side in the circumferential direction Dc.

[0047] 9 to 10B, in the stator vane segment 11 according to some embodiments, the position in the circumferential direction Dc of the end portion 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U is positioned to one side in the circumferential direction Dc of the end portion 41De on the other side in the circumferential direction Dc of the downstream engagement portion 41D. In other words, the position in the circumferential direction Dc of the end portion 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U is retracted to one side in the circumferential direction Dc. This makes it possible to prevent the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc from coming into contact with the groove bottom of the upstream engagement groove 28 or the upstream lip portion 25 in the inner shroud 22a located on the one side of the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc.

[0048] In some embodiments of the stator vane segment 11, as shown in Figures 9 to 10B, the position in the circumferential direction Dc of the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc may be the same as the position in the circumferential direction Dc of the end portion 25e on the other side of the upstream lip portion 25 in the circumferential direction Dc of the inner shroud 22a located on the other side most in the circumferential direction Dc, or may be located to one side of that position in the circumferential direction Dc. As a result, the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc does not come into contact with the groove bottom of the upstream engagement groove 28 or the upstream lip portion 25 in the inner shroud 22a located on the one side of the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc.

[0049] In addition, in order to set the circumferential position Dc of the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc to the above-mentioned position, the positions of the other end portions in the circumferential direction Dc of the upstream leg portion 44 and the upstream flange portion 45, which are radially outer than the radially inner side wall surface 41Ui of the upstream engagement portion 41U, may also be set to the above-mentioned positions. Alternatively, in order to set the circumferential position Dc of the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc to the above-mentioned position, the positions of the other ends in the circumferential direction Dc of the upstream leg portion 44 and the upstream flange portion 45, which are radially outer than the bottom surface 41b of the shroud storage groove 41, may be set to the above-mentioned positions.

[0050] (When the shroud body 23 has a rectangular shape: Part 2) A case where the shape of the shroud main body 23 is rectangular when viewed from the radial direction Dr, like the inner shroud 22 shown in FIG. 11, will be described. In the inner shroud 22 shown in FIG. 11, a part of the inner shroud 22a located at the end on the other side in the circumferential direction Dc protrudes from the connecting holder 40 to the other side in the circumferential direction Dc.

[0051] As described above, a rotational force acts on the entire plurality of stator vane bodies 21 held by the connecting holder 40 such that the other side in the circumferential direction Dc moves toward the axial downstream side, as shown by arrow b in Fig. 6. Therefore, in the conventional stator vane segment 11, when a part of the inner shroud 22a protrudes from the connecting holder 40 to the other side in the circumferential direction Dc as shown in Fig. 11, there is a risk that the axially downstream corner 23e of the inner shroud 22a located at the end on the other side in the circumferential direction Dc may come into contact in the axial direction Da with a region on one side in the circumferential direction Dc and on the axial downstream side of the connecting holder 40 of the stator vane segment 11 adjacent on the other side in the circumferential direction Dc.

[0052] 11 to 12B, in the stator vane segment 11 according to some embodiments, the position in the circumferential direction Dc of the end portion 41De on one side in the circumferential direction Dc of the downstream engagement portion 41D is located on the other side in the circumferential direction Dc with respect to the position in the circumferential direction Dc of the end portion 41Ue on one side in the circumferential direction Dc of the upstream engagement portion 41U. In other words, the position in the circumferential direction Dc of the end portion 41De on one side in the circumferential direction of the downstream engagement portion 41D is retracted to the other side in the circumferential direction Dc. This makes it possible to prevent the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc from coming into contact with the groove bottom of the downstream engagement groove 29 or the downstream lip portion 27 in the inner shroud 22a located on the other side of the adjacent stator vane segment 11 in the circumferential direction Dc.

[0053] In some embodiments of the stator vane segment 11, as shown in Figures 11 to 12B, the circumferential position in the circumferential direction Dc of the end portion 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc may be the same as the circumferential position in the circumferential direction Dc of the end portion 27e on one side of the downstream lip portion 27 in the inner shroud 22a located on the furthest side in the circumferential direction Dc, or may be located on the other side of that position in the circumferential direction Dc. As a result, the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc does not come into contact with the groove bottom of the downstream engagement groove 29 or the downstream lip portion 27 in the inner shroud 22a located on the other side of the adjacent stator vane segment 11 in the circumferential direction Dc.

[0054] In addition, in order to set the circumferential position Dc of one end 41De of the downstream engagement portion 41D in the circumferential direction Dc to the above-mentioned position, the positions of one end of the downstream leg portion 46 and the downstream flange portion 47, which are radially outward in the radial direction Dr than the side wall surface 41Di on the inner side in the radial direction Dr of the downstream engagement portion 41D, may also be set to the above-mentioned position. Alternatively, in order to set the circumferential position Dc of one end 41De of the downstream engagement portion 41D in the circumferential direction Dc to the above-mentioned position, the positions of one end of the downstream leg portion 46 and the downstream flange portion 47 in the circumferential direction Dc that are radially outward from the bottom surface 41b of the shroud storage groove 41 may be set to the above-mentioned position.

[0055] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0056] The contents described in each of the above embodiments can be understood, for example, as follows. (1) A stator vane segment 11 of a compressor 1 according to at least one embodiment of the present disclosure includes a plurality of stator vanes 20 arranged in the circumferential direction Dc, each of which has an airfoil portion (stator vane main body 21) with a pressure surface 21P facing one side in the circumferential direction Dc and a suction surface 21S facing the other side in the circumferential direction Dc, and an inner shroud 22 connected to an end of the airfoil portion (stator vane main body 21) inside the radial direction Dr. The stator vane segment 11 of a compressor 1 according to at least one embodiment of the present disclosure includes holders (connecting holders 40) attached to the inner shrouds 22 of the plurality of stator vanes 20. Each of the inner shrouds 22 has an upstream hook portion (upstream lip portion 25) provided upstream in the axial direction Da and engaging with the holder (connecting holder 40), and a downstream hook portion (downstream lip portion 27) provided downstream in the axial direction Da and engaging with the holder (connecting holder 40). The holder (connecting holder 40) has an upstream engagement portion 41U that engages with the upstream hook portion (upstream lip portion 25) and a downstream engagement portion 41D that engages with the downstream hook portion (downstream lip portion 27). The holder (connecting holder 40) satisfies at least one of the following conditions: the position in the circumferential direction Dc of one end portion 41De of the downstream engagement portion 41D in the circumferential direction Dc is located on the other side in the circumferential direction Dc of the end portion 41Ue of one side in the circumferential direction Dc of the upstream engagement portion 41U, or the position in the circumferential direction Dc of the other end portion 41Ue of the upstream engagement portion 41U is located on one side in the circumferential direction Dc of the end portion 41De of the other side in the circumferential direction Dc of the downstream engagement portion 41D.

[0057] The stator vane segments 11 have holders (connecting holders 40) attached to the multiple inner shrouds 22. If adjacent stator vane segments 11 in the circumferential direction Dc are attached to the casing 5 of the compressor 1 with the side surfaces 22s in the circumferential direction Dc of the inner shrouds 22a of the stator vanes 20a at the ends of the stator vane segments 11 in the circumferential direction Dc abutting against each other, a gap may be formed between the side surfaces 22s due to wear during use of the compressor 1. If such a gap is formed, the stator vane segment 11 moves relative to the holder (connecting holder 40) due to fluid force from the fluid passing through the stator vane segment 11. Therefore, the inner shroud 22a located at the end of the stator vane segment 11 in the circumferential direction Dc may abut against the holder (connecting holder 40) of the adjacent stator vane segment 11 in the circumferential direction Dc, which may increase the mean stress of the airfoil portion (stator vane main body 21), leading to problems such as a shortened lifespan.

[0058] According to the configuration (1) above, the position of the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc satisfies the above-mentioned conditions, thereby making it possible to prevent the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc from coming into contact with the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the other side of the circumferential direction Dc of the adjacent stator vane segment 11 on one side of the circumferential direction Dc. According to the configuration (1) above, the position in the circumferential direction Dc of the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc satisfies the above-mentioned conditions, thereby making it possible to prevent the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc from coming into contact with the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the one side furthest in the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc. This reduces the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1, and extends the life of the stator blades 20.

[0059] (2) In some embodiments, in the configuration described in (1) above, each side surface 22s in the circumferential direction Dc of the inner shroud 22 may be inclined with respect to the axial direction Da so as to move from one side in the circumferential direction Dc to the other side as it moves from the upstream side to the downstream side in the axial direction Da. The position in the circumferential direction Dc of the end 41De on one side in the circumferential direction Dc of the downstream engagement portion 41D is located on the other side in the circumferential direction Dc of the end 41Ue on one side in the circumferential direction Dc of the upstream engagement portion 41U, and the position in the circumferential direction Dc of the end 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U is located on the one side in the circumferential direction Dc of the end 41De on the other side in the circumferential direction Dc of the downstream engagement portion 41D.

[0060] According to the configuration (2) above, it is possible to prevent the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc from coming into contact with the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the other side of the circumferential direction Dc of the adjacent vane segment 11 on one side of the circumferential direction Dc. According to the configuration (2) above, it is possible to prevent the end 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc from coming into contact with the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the one side furthest in the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc. This makes it possible to reduce the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1.

[0061] (3) In some embodiments, in the configuration described in (2) above, the position in the circumferential direction Dc of one end 41De of the downstream engagement portion 41D in the circumferential direction Dc may be the same as or be located on the other side of the circumferential direction Dc of one end 27e of the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the one side in the circumferential direction Dc. The position in the circumferential direction Dc of the other end 41Ue of the upstream engagement portion 41U in the circumferential direction Dc may be the same as or be located on the one side of the circumferential direction Dc of the other end 25e of the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the other side in the circumferential direction Dc.

[0062] According to the configuration (3) above, the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc does not come into contact with the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the other side of the circumferential direction Dc of the adjacent vane segment 11 on one side of the circumferential direction Dc. According to the configuration (3) above, the end 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc does not come into contact with the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the most one side in the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc. This allows the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1 to be reduced.

[0063] (4) In some embodiments, in the configuration described in (1) above, the side surface 22s of each inner shroud 22 in the circumferential direction Dc may be located at the same position in the circumferential direction Dc between the upstream side in the axial direction Da and the downstream side in the axial direction Da. The end portion (side surface 22s) on one side in the circumferential direction Dc of the inner shroud 22a of the stator blade 20 located furthest to one side in the circumferential direction Dc among the multiple stator blades 20 may protrude further to one side in the circumferential direction Dc than the holder (connection holder 40). The position in the circumferential direction Dc of the end portion 41Ue on the other side in the circumferential direction Dc of the upstream engagement portion 41U may be located further to one side in the circumferential direction Dc than the position in the circumferential direction Dc of the end portion 41De on the other side in the circumferential direction Dc of the downstream engagement portion 41D.

[0064] According to the configuration (4) above, it is possible to prevent the end 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc from coming into contact with the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the most one side in the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc. This makes it possible to reduce the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1.

[0065] (5) In some embodiments, in the configuration of (4) above, the position in the circumferential direction Dc of the end portion 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc may be the same as the position in the circumferential direction Dc of the end portion 25e on the other side of the upstream hook portion (upstream lip portion 25) in the circumferential direction Dc of the inner shroud 22a located on the other side furthest in the circumferential direction Dc, or may be located to one side of that position in the circumferential direction Dc.

[0066] According to the configuration (5) above, the end 41Ue on the other side of the upstream engagement portion 41U in the circumferential direction Dc does not come into contact with the upstream hook portion (upstream lip portion 25) of the inner shroud 22a located on the one side furthest in the circumferential direction Dc of the adjacent stator vane segment 11 on the other side of the circumferential direction Dc. This allows the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1 to be reduced.

[0067] (6) In some embodiments, in the configuration described in (1) above, the side surface 22s of each inner shroud 22 in the circumferential direction Dc may be located at the same position in the circumferential direction Dc between the upstream side in the axial direction Da and the downstream side in the axial direction Da. The other end portion (side surface 22s) of the inner shroud 22a of the stator blade 20a located furthest in the other side in the circumferential direction Dc of the inner shroud 22a may protrude further in the other side in the circumferential direction Dc than the holder (connection holder 40). The position in the circumferential direction Dc of the end portion 41De on one side in the circumferential direction Dc of the downstream engagement portion 41D may be located further in the circumferential direction Dc than the position in the circumferential direction Dc of the end portion 41Ue on one side in the circumferential direction Dc of the upstream engagement portion 41U.

[0068] According to the configuration (6) above, it is possible to prevent the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc from coming into contact with the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the other side of the circumferential direction Dc of the adjacent vane segment 11 on one side of the circumferential direction Dc. This makes it possible to reduce the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1.

[0069] (7) In some embodiments, in the configuration of (6) above, the position in the circumferential direction Dc of the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc may be the same as the position in the circumferential direction Dc of the end 27e on one side of the circumferential direction Dc of the downstream hook portion (downstream lip portion 27) in the inner shroud 22a located on the farthest side in the circumferential direction Dc, or may be located on the other side of that position in the circumferential direction Dc.

[0070] According to the configuration (7) above, the end 41De on one side of the downstream engagement portion 41D in the circumferential direction Dc does not come into contact with the downstream hook portion (downstream lip portion 27) of the inner shroud 22a located on the other side of the circumferential direction Dc of the adjacent stator vane segment 11 on one side of the circumferential direction Dc. This allows the stress acting on the stator blades 20 in the stator blade segment 11 of the compressor 1 to be reduced.

[0071] (8) In some embodiments, in any of the configurations (1) to (7) above, the holder (connecting holder 40) may be provided with a pin 49 that restrains the movement of the stator blades 20a located at both ends of the circumferential direction Dc among the multiple stator blades 20 in the circumferential direction Dc.

[0072] According to the configuration (8) above, the movement of the multiple stator blades 20 in the circumferential direction Dc relative to the holder (connecting holder 40) is restricted, thereby reducing the occurrence of problems such as undesired wear due to the movement of the multiple stator blades 20 in the circumferential direction Dc relative to the holder (connecting holder 40).

[0073] (9) The compressor 1 according to at least one embodiment of the present disclosure includes a stator blade ring (stator blade stage 10) in which a plurality of stator blade segments 11 of any one of (1) to (8) above are arranged in the circumferential direction Dc.

[0074] According to the configuration (9) above, the life of the stator blades 20 can be extended, and therefore the reliability of the compressor 1 can be improved. [Explanation of symbols]

[0075] 1 Compressor 10 Stator blade ring (Stator blade stage) 11 Stator vane segment 20 Stator blade 21 Stator blade body (airfoil section) 21P ventral surface 21S back 22, 22a Inner shroud 22s side 23 Shroud body 24 Protrusion 25 Upstream lip 25e end 27 Downstream lip 27e end 32 outer shroud 40 Connection holder (inner connection member) 41 Shroud storage groove 41D Downstream engaging part 41De end 41U Upstream engagement part 41Ue end 49 pins

Claims

1. A compressor stator vane segment, comprising: a plurality of stator vanes arranged in the circumferential direction, each having an airfoil portion with a pressure surface facing one side in the circumferential direction and a suction surface facing the other side in the circumferential direction, and an inner shroud connected to an end of the airfoil portion on the radially inner side; a holder attached to the inner shroud of the plurality of vanes; Equipped with Each of the inner shrouds an upstream hook portion provided on the upstream side in the axial direction and adapted to engage with the holder; a downstream hook portion provided on the downstream side in the axial direction and adapted to engage with the holder; and The holder is an upstream engaging portion that engages with the upstream hook portion; a downstream engaging portion that engages with the downstream hook portion; and The holder is the circumferential position of the one end of the downstream engaging portion in the circumferential direction is located on the other side in the circumferential direction than the circumferential position of the one end of the upstream engaging portion in the circumferential direction, Or, the circumferential position of the other circumferential end of the upstream engaging portion is located on one side in the circumferential direction relative to the circumferential position of the other circumferential end of the downstream engaging portion; At least one of the following conditions must be met: Compressor stator vane segment.

2. each of the circumferential side surfaces of the inner shroud is inclined with respect to the axial direction so as to move from one side to the other side in the circumferential direction as it moves from the upstream side to the downstream side in the axial direction; a circumferential position of an end portion on one side in the circumferential direction of the downstream engagement portion is located on the other side in the circumferential direction with respect to a circumferential position of an end portion on one side in the circumferential direction of the upstream engagement portion, and, a circumferential position of an end portion of the upstream engagement portion on the other side in the circumferential direction is located on one side in the circumferential direction with respect to a circumferential position of an end portion of the downstream engagement portion on the other side in the circumferential direction; The compressor vane segment of claim 1 .

3. a circumferential position of an end portion on one side in the circumferential direction of the downstream engagement portion is the same as a circumferential position of an end portion on one side in the circumferential direction of the downstream hook portion of the inner shroud located furthest on the one side in the circumferential direction, or is located on the other side in the circumferential direction relative to that position, and, a circumferential position of an end portion on the other side in the circumferential direction of the upstream engaging portion is the same as a circumferential position of an end portion on the other side in the circumferential direction of the upstream hook portion of the inner shroud located on the other side in the circumferential direction, or is located on one side in the circumferential direction of the circumferential position. The compressor vane segment of claim 2 .

4. the circumferential position of each of the circumferential side surfaces of the inner shroud is the same on the upstream side in the axial direction and on the downstream side in the axial direction, an end portion on one side in the circumferential direction of the inner shroud of the stator vane located furthest on one side in the circumferential direction among the plurality of stator vanes protrudes toward the one side in the circumferential direction beyond the holder, a circumferential position of an end portion of the upstream engagement portion on the other side in the circumferential direction is located on one side in the circumferential direction with respect to a circumferential position of an end portion of the downstream engagement portion on the other side in the circumferential direction; The compressor vane segment of claim 1 .

5. a circumferential position of an end portion on the other side in the circumferential direction of the upstream engaging portion is the same as a circumferential position of an end portion on the other side in the circumferential direction of the upstream hook portion of the inner shroud located on the other side in the circumferential direction, or is located on one side in the circumferential direction of the circumferential position. The compressor vane segment of claim 4 .

6. the circumferential position of each of the circumferential side surfaces of the inner shroud is the same on the upstream side in the axial direction and on the downstream side in the axial direction, an end portion on the other side in the circumferential direction of the inner shroud of the stator vane that is located furthest on the other side in the circumferential direction among the plurality of stator vanes protrudes toward the other side in the circumferential direction beyond the holder, a circumferential position of an end portion on one side in the circumferential direction of the downstream engaging portion is located on the other side in the circumferential direction with respect to a circumferential position of an end portion on one side in the circumferential direction of the upstream engaging portion; The compressor vane segment of claim 1 .

7. a circumferential position of an end portion on one side in the circumferential direction of the downstream engagement portion is the same as a circumferential position of an end portion on one side in the circumferential direction of the downstream hook portion of the inner shroud located furthest on the one side in the circumferential direction, or is located on the other side in the circumferential direction from that position; The compressor vane segment of claim 6 .

8. pins that restrain movement of the stator vanes located at both ends in the circumferential direction among the plurality of stator vanes relative to the holder in the circumferential direction; Equipped with A compressor vane segment according to any one of claims 1 to 7.

9. A stator blade ring in which a plurality of stator blade segments according to any one of claims 1 to 7 are arranged in the circumferential direction. A compressor comprising:

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