Guide support structure of gas turbine

Abstract

To improve the durability of a member for guiding combustion gas or a structure for supporting the same.SOLUTION: A gas turbine 1 comprises a partition wall 30 that separates a compression section 3 and a combustion section 4, a guide member 10 that defines a gas flow passage 20 for guiding combustion gas injected from the combustion section 4 to a turbine 5, and a support part 40 that supports the guide member 10 within the combustion section 4. The support part 40 has a restriction portion 41 that restricts the displacement of the guide member 10, and an engagement portion 42 that mechanically engages with the restriction portion 41. One of the restriction portion 41 and the engagement portion 42 is provided on the partition wall 30. The other of the restriction portion 41 and the engagement portion 42 is installed on the guide member 10.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present invention relates to a guide support structure for a gas turbine. [Background technology]

[0002] Patent Document 1 discloses a gas turbine equipped with a combustion gas scroll as an example of a guide member that guides high-temperature combustion gas to the turbine. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Publication No. 9-41989 Summary of the Invention [Problem to be solved by the invention]

[0004] High thermal stress occurs in the guide member that guides the combustion gas and the structure that supports the guide member. There is room for improvement in terms of alleviating the thermal stress and improving durability.

[0005] An object of the present invention is to improve the durability of a guide member that guides combustion gas or a structure that supports the guide member. [Means for solving the problem]

[0006] One aspect of the present invention provides a guide support structure for a gas turbine comprising: a compression section that compresses intake air, a combustion section that combusts the compressed air, a partition wall that separates the compression section from the combustion section, a guide member that defines a gas flow path that guides combustion gas generated in the combustion section to a turbine, and a support section that supports the guide member within the combustion section, the support section having a regulating section and an engaging section that mechanically engages with the regulating section, wherein one of the regulating section and the engaging section is provided on the partition wall, and the other of the regulating section and the engaging section is attached to the guide member.

[0007] According to the above-mentioned configuration, the engaging portion is mechanically engaged with the restricting portion, which improves the durability of the supporting portion compared to a case in which welding is used to fix the guide member to the partition wall.

[0008] The regulating portion may be provided on the partition wall, and the engaging portion may be attached to the guide member, and the regulating portion may engage with the engaging portion so as to allow displacement of the engaging portion in one direction while regulating displacement in a direction intersecting the one direction.

[0009] According to the above-mentioned configuration, the expansion of the guide member in one direction can be absorbed by the displacement of the engagement portion, and the load acting on the support portion can be reduced. The deformation of the guide member in a direction intersecting the one direction can be restricted, and the support of the guide member by the partition wall can be maintained.

[0010] The restricting portion may have a shaft-shaped portion, and the engaging portion may have an engaging hole through which the shaft-shaped portion is inserted so as to be displaceable in an axial direction of the shaft-shaped portion.

[0011] According to the above configuration, the displacement of the engaging portion, and therefore the expansion of the guide member, can be tolerated with a simple structure.

[0012] The engagement portion may restrict displacement of the shaft portion in a direction intersecting the axial direction.

[0013] According to the above configuration, the deformation of the guide member can be restricted with a simple structure.

[0014] The restricting portion may be provided on the partition wall, the engaging portion may be attached to the guide member, and the restricting portion may be provided on an attachment member extending from the partition wall towards the combustion portion.

[0015] According to the above configuration, it is easy to realize a structure in which the guide member is supported by the partition wall, regardless of the shapes or dimensions of the partition wall and the guide member.

[0016] The mounting member may be disposed at a distance from the guide member.

[0017] According to the above configuration, heat from the guide member is less likely to be transmitted to the partition wall.

[0018] The guide member may include a first guide member and a second guide member engaged with each other so as to be relatively displaceable in the engaging direction, the regulating portion being provided on the partition wall, and the engaging portion being attached to the second guide member.

[0019] According to the above configuration, deformation of the guide member in the fitting direction can be permitted.

[0020] The second guide member may be fitted onto the outside of the first guide member and have an extension portion located away from the outer periphery of the first guide member, and the engagement portion may be provided on the extension portion.

[0021] According to the above-mentioned configuration, by forming the extension portion integrally with the guide member, a new dedicated member for providing the engagement portion is not required, and the guide support structure can be simplified. Effect of the Invention

[0022] An object of the present invention is to improve the durability of a guide member that guides combustion gas or a structure that supports the guide member. [Brief description of the drawings]

[0023] [Figure 1] 1 is a cross-sectional view of a gas turbine according to an embodiment; [Diagram 2] FIG. 2 is a cross-sectional view of a guide support structure according to the embodiment. [Diagram 3] FIG. 4 is a perspective view showing the partition wall and the guide member in an assembled state as viewed from the compression unit side. [Figure 4] Cross-sectional view of the support portion. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] Hereinafter, an embodiment will be described with reference to the drawings. Note that the same or corresponding elements are designated by the same reference numerals throughout the drawings, and detailed description thereof will be omitted.

[0025] Referring to Fig. 1, a gas turbine 1 is, as a mere example, stationary on land and used as a power source for a generator (not shown). In this case, a main shaft 2 of the gas turbine 1 is connected to the generator via a reduction gear mechanism (not shown). However, the use of the gas turbine 1 is not particularly limited. In this disclosure, unless otherwise specified, the "axial direction" refers to a direction along the axis A of the main shaft 2, the "axially orthogonal direction" or the "radial direction" refers to a direction perpendicular to the axis of the main shaft 2, and the "circumferential direction" refers to a direction around the axis A.

[0026] The gas turbine 1 includes a compression section 3, a combustion section 4, and a turbine 5. The main shaft 2 includes a rotor 3a of the compression section 3 and a turbine rotor 5a of the turbine 5, and the rotor 3a is disposed on one axial side of the turbine rotor 5a. The rotor 3a and the turbine rotor 5a are disposed coaxially about an axis A, are connected in the axial direction, and rotate together about the axis A. In this disclosure, a "rotor" refers to a shaft-shaped member itself or a member having a shaft-shaped portion, which rotates about its own central axis. The main shaft 2 is rotatably supported by a casing 1A of the gas turbine 1.

[0027] The compression section 3 compresses intake air obtained by taking in outside air by the action of an impeller 3b that is integrally provided on the rotor 3a. The combustion section 4 injects fuel into the compressed air, burns the mixture, and generates high-temperature, high-pressure combustion gas. The turbine 5 is driven by the combustion gas. When the turbine 5 operates, the main shaft 2 rotates. This drives the compression section 3, and the generator (not shown) generates alternating current. The main shaft 2 extends from the rotor 3a to one axial side to extract rotational driving force for operating the generator, while exhaust gas is discharged from the turbine 5 to the other axial side.

[0028] The turbine 5 is adjacent to the other axial side of the compression section 3. The turbine 5 may have a larger diameter than the compression section 3, but has a smaller diameter here. The combustion section 4 is adjacent to the other axial side of the compression section 3 and is disposed on the radially outer periphery of the turbine 5.

[0029] The casing 1A of the gas turbine 1 includes a compressor casing 3A, a combustor casing 4A, and a turbine casing 5A.

[0030] The compressor casing 3A constitutes the compression section 3 and defines an accommodation space 3c that accommodates the impeller 3b. The compressor casing 3A has an inner wall 3d on the other axial side. The inner wall 3d is disk-shaped and has a through hole in the center that allows the rotor 3a with the impeller 3b to pass through. The inner wall 3d has a cylindrical flange 3e that protrudes from its outer circumferential edge toward the other axial side.

[0031] The turbine casing 5A constitutes the turbine 5 and is formed in a cylindrical shape. An opening on one axial end side of the turbine casing 5A is connected to a turbine nozzle 5b that is annular when viewed in the axial direction, and an opening on the other axial end side of the turbine casing 5A functions as an exhaust port 5c that discharges exhaust gas. The turbine nozzle 5b is disposed away from the inner wall 3d of the compressor casing 3A on the other axial side.

[0032] The combustor casing 4A constitutes the combustion section 4. The combustor casing 4A has a first cylindrical portion 4a surrounding the turbine nozzle 5b and the turbine casing 5A, and a second cylindrical portion 4b protruding from the first cylindrical portion 4a. The central axis of the first cylindrical portion 4a is coaxial with the axis A of the main shaft 2. The central axis of the second cylindrical portion 4b extends along a direction perpendicular to the axis A of the main shaft 2 (the radial direction of the main shaft 2). One axial end of the first cylindrical portion 4a abuts against an end face of a flange 3e of the compressor casing 3A and is fastened to the flange 3e. The other axial end of the first cylindrical portion 4a extends radially inward and is fastened to the turbine casing 5A.

[0033] The combustion section 4 has a cylindrical combustor 4c housed in the second cylindrical portion 4b. The combustor 4c generates combustion gas therein. The combustor 4c has a gas ejection port 4d for ejecting the combustion gas at one axial end thereof. The combustor 4c is disposed coaxially with the second cylindrical portion 4b (i.e., extends in the radial direction of the axis A). The one axial end of the combustor 4c is disposed relatively proximal to the axis A in the radial direction, and the other axial end is disposed relatively distal from the axis A in the radial direction.

[0034] A guide member 10 that guides the combustion gas generated in the combustion section 4 to the turbine 5 is housed within the first cylindrical section 4a. The guide member 10 defines a gas flow path 20 through which the combustion gas flows. The gas flow path 20 connects a gas ejection port 4d of the combustor 4c to the turbine nozzle 5b.

[0035] The gas flow passage 20 has an annular portion 21, a turned-back portion 22, and an outflow portion 23. The annular portion 21 is disposed on the outer periphery side of the turbine casing 5A, extends in the axial direction, and has an annular cross section perpendicular to the axis. The gas ejection port 4d communicates with the annular portion 21. The annular portion 21 is closed on the other axial side, while communicating with the turned-back portion 22 on the one axial side. The turned-back portion 22 extends from one axial end of the annular portion 21 to the radially inner periphery side. The outflow portion 23 extends from the radially inner periphery end of the turned-back portion 22 to the other axial side, and communicates with an opening on the axially one end side of the turbine nozzle 5b. The outer diameter of the outflow portion 23 is smaller than the inner diameter of the annular portion 21, and the outflow portion 23 is disposed inside the annular portion 21. The axial dimension of the outflow portion 23 is shorter than that of the annular portion 21.

[0036] The interior of the combustor casing 4A is divided into an inside and an outside by the combustor 4c and the guide member 10. The gas turbine 1 includes a partition wall 30 provided on the outside of the combustor 4c and the guide member 10. The partition wall 30 is cylindrical with a short axial dimension, coaxial with the main shaft 2, and disposed on the inner peripheral side of the flange 3e of the compressor casing 3A. The partition wall 30 is disposed on the other axial side of the compressor casing 3A and on one axial side of the combustor casing 4A, and separates the compression section 3 and the combustion section 4.

[0037] The partition wall 30 has a disk portion 32 having a shaft insertion opening 31 at its center through which the main shaft 2 passes, and a peripheral wall portion 33 extending from the outer periphery of the disk portion 32 to the other axial direction side. The disk portion 32 closely faces an inner wall 3d of the compressor casing 3A with a gap in the axial direction. The inner wall 3d and the disk portion 32 define a first compressed air flow path 6a that guides air compressed by the impeller 3b to the radially outer periphery side. The peripheral wall portion 33 closely faces a flange 3e of the compressor casing 3A with a gap in the radial direction. The flange 3e and the peripheral wall portion 33 extend from an end (downstream end) of the first compressed air flow path 6a to the other axial direction side, and define a second compressed air flow path 6b that is annular when viewed in the axial direction. The inner peripheral surface of the second cylindrical portion 4b and the outer peripheral surface of the combustor 4c extend radially outward from the other axial end (downstream end) of the second compressed air passage 6b to define a third compressed air passage 6c that is annular when viewed in the axial direction of the second cylindrical portion 4b and the combustor 4c. The combustor 4c has a compressed air intake 4e on its outer peripheral surface that takes in compressed air from the third compressed air passage 6c.

[0038] The guide member 10 also defines the other axial end (downstream end) of the second compressed air passage 6b together with the inner circumferential surface of the first cylindrical portion 4a. The guide member 10 also defines the radially inner end (upstream end) of the third compressed air passage 6c.

[0039] With reference to FIG. 2, the guide member 10 includes a first guide member 11 and a second guide member 12. The first guide member 11 and the second guide member 12 are arranged in a substantially rectangular shape.

[0040] The first guide member 11 has an outer cylinder portion 11a, an inner cylinder portion 11b, an annular bottom portion 11c (see FIG. 1), a protruding cylinder portion 11d, an extending portion 11e, and a curved portion 11f. The outer cylinder portion 11a and the inner cylinder portion 11b are cylindrical and coaxial with each other. The inner cylinder portion 11b is disposed inside the outer cylinder portion 11a. The annular bottom portion 11c is annular when viewed in the axial direction, and radially connects the other axial ends of the outer cylinder portion 11a and the inner cylinder portion 11b. The inner peripheral surface of the outer cylinder portion 11a, the outer peripheral surface of the inner cylinder portion 11b, and the inner surface of the annular bottom portion 11c form the annular portion 21 of the gas flow passage 20. The protruding cylinder portion 11d is cylindrical and protrudes radially outward from the outer cylinder portion 11a. The protruding cylindrical portion 11d is fitted onto one axial end of the combustor 4c, whereby the gas ejection port 4d communicates with the annular portion 21. The outer cylindrical portion 11a and the inner cylindrical portion 11b are open to the other axial side.

[0041] One axial end of the inner cylindrical portion 11b is folded back in a U-shape so as to face the radially inner circumferential side and the other axial side. The extending portion 11e extends from the axial end of the inner cylindrical portion 11b toward the radially inner circumferential side. The curved portion 11f curves from the radially inner circumferential end of the extending portion 11e toward the other axial side. A flange having an annular shape when viewed in the axial direction is provided at the tip of the curved portion 11f, and the first guide member 11 is fastened to the outer circumferential edge portion of the turbine nozzle 5b at this flange.

[0042] The second guide member 12 has an outer wall portion 12a that is annular when viewed in the axial direction. The outer peripheral edge of the outer wall portion 12a is curved so as to be directed toward the other axial side as it approaches the radial outer periphery. The outer peripheral edge of the outer wall portion 12a is fitted onto the outer tube portion 11a of the first guide member 11. One axial end of the outer tube portion 11a of the first guide member 11 and the outer peripheral edge of the outer wall portion 12a of the second guide member 12 form the outer fitting portion 10a of the guide member 10. The fitting direction of the outer fitting portion 10a is the axial direction, and the outer peripheral edge of the outer wall portion 12a and one axial end of the outer tube portion 11a are overlapped in the radial direction.

[0043] The second guide member 12 has an extension portion 12b continuing from the outer peripheral edge portion of the outer wall portion 12a (in other words, the outer fitting portion 10a). The extension portion 12b extends from the outer fitting portion 10a to the other axial direction. The extension portion 12b includes an expanded diameter portion 12c expanded radially toward the outer periphery as it moves from the outer fitting portion 10a to the other axial direction, and an outer peripheral wall portion 12d extending further to the other side along the axial direction from the other axial end portion of the expanded diameter portion 12c. The outer peripheral wall portion 12d is cylindrical with a constant diameter in the axial direction. While the extension portion 12b has the expanded diameter portion 12c, the outer tube portion 11a is cylindrical with a constant diameter in the axial direction, so that the outer peripheral wall portion 12d surrounds the outer tube portion 11a with a radial gap from the outer peripheral surface of the outer tube portion 11a.

[0044] The radially inner circumferential side of the outer wall portion 12a is curved so as to bend toward the other axial side as it approaches the radially inner circumferential side. The outer wall portion 12a faces the extending portion 11e of the first guide member 11 in the axial direction. The inner circumferential edge portion of the outer wall portion 12a extends along the axial direction, faces the curved portion 11f of the first guide member 11 in the radial direction, and faces the inner circumferential edge portion of the turbine nozzle 5b in the axial direction. A ring material 14 is welded to the inner circumferential edge portion of the outer wall portion 12a of the second guide member 12, and the ring material 14 is fastened to the periphery of the shaft insertion opening 31 of the partition wall 30 together with the inner circumferential edge portion of the turbine nozzle 5b.

[0045] In this manner, the guide member 10 is attached to the combustor 4c on the outer peripheral surface side. The guide member 10 is fastened to the radially inner peripheral portion of the partition wall 30 on one axial side and the radially inner peripheral side.

[0046] 2 and 3, the guide member 10 is supported by a support portion 40 on one axial side and on the outer circumferential side in the radial direction.

[0047] The support portion 40 spans between the radially outer periphery of the partition wall 30 and the guide member 10. The support portion 40 has a restricting portion 41, an engaging portion 42 (not shown in FIG. 3 ), and an attachment member 43. One of the restricting portion 41 and the engaging portion 42 is provided on the partition wall 30, and the other of the restricting portion 41 and the engaging portion 42 is attached to the guide member 10.

[0048] In this embodiment, the restricting portion 41 is provided on the partition wall 30 via an attachment member 43. The engaging portion 42 is attached to the guide member 10. Specifically, the engaging portion 42 is attached to the second guide member 12 of the guide member 10. More specifically, the engaging portion 42 is attached to the extension portion 12b of the second guide member 12. Even more specifically, the engaging portion 42 is attached to the outer circumferential wall portion 12d of the extension portion 12b.

[0049] In the gas turbine 1 according to this embodiment, as shown in Fig. 3, the guide support structure includes a plurality of support parts 40. The plurality of support parts 40 are arranged at intervals from one another in the circumferential direction. As an example, 18 support parts 40 are arranged at approximately equal intervals.

[0050] 4, flanges 34 are provided on the inner peripheral surface of the peripheral wall portion 33 of the partition wall 30, the flanges 34 being spaced apart from each other in the circumferential direction. The flanges 34 are plate-shaped and protrude from the peripheral wall portion 33 toward the other axial direction. One or more (e.g., three) screw holes 34a are formed in the flange 34. The base end of the mounting member 43 is placed on the outer surface of the flange 34 and fastened to the flange 34. A sheet-shaped shim 44 is interposed between the mounting member 43 and the flange 34. A bolt 45 is inserted through the mounting member 43 and the shim 44 in this order from the radially outer peripheral side to the radially inner peripheral side, and is screwed into the screw hole 34a of the flange 34. The axial direction of the bolt 45 and the plate thickness directions of the flange 34, the mounting member 43, and the shim 44 are oriented in the radial direction of the spindle 2 (direction perpendicular to the axis A). Reference numeral 43a denotes a through hole formed in the base end portion of the mounting member 43, through which a bolt 45 is inserted.

[0051] The restricting portion 41 is provided at the tip of the mounting member 43. The engaging portion 42 mechanically engages with the restricting portion 41. The restricting portion 41 restricts the displacement of the guide member 10. Moreover, the restricting portion 41 engages with the engaging portion 42 in such a manner as to permit displacement of the engaging portion 42 in one direction and restrict displacement in a direction intersecting the one direction.

[0052] In this embodiment, the regulating portion 41 has a shaft-like portion 50. The term "shaft-like" is essentially synonymous with a cylindrical, columnar, or pin-like shape, and the outer diameter does not necessarily have to be uniform in the axial direction. The engaging portion 42 has an engaging hole 42a through which the shaft-like portion 50 is inserted. The shaft-like portion 50 engages with the engaging portion 42 so as to be displaceable in the axial direction of the shaft-like portion 50. On the other hand, the displacement of the shaft-like portion 50 in a direction intersecting the axial direction of the shaft-like portion 50 (typically, a direction perpendicular to the axis of the shaft-like portion 50) is restricted by the inner peripheral surface of the engaging hole 42a.

[0053] The engagement portion 42 is constituted by a bushing 55 with a flange. The bushing 55 has an intermediate cylindrical portion 55a and a pair of flanges 55b, 55c that protrude radially from both ends of the intermediate cylindrical portion 55a. The bushing 55 is fitted into a through hole formed in the second guide member 12 (specifically, the outer peripheral wall portion 12d). One flange 55b abuts against the outer surface of the outer peripheral wall portion 12d, and the other flange 55c abuts against the inner surface of the outer peripheral wall portion 12d. The bushing 55 has a through hole having a constant diameter over the entire axial direction from one flange 55b to the other flange 55c, and this through hole serves as the engagement hole 42a. The engagement hole 42a (the through hole of the bushing 55) has a circular cross section.

[0054] Shaft-like portion 50 protrudes from the inner surface of mounting member 43 toward the inner periphery in the radial direction (direction perpendicular to axis A) of spindle 2. That is, in this embodiment, the "one direction" as the permissible displacement direction of regulating portion 41 is the radial direction of spindle 2 (direction perpendicular to axis A).

[0055] The shaft-shaped portion 50 is composed of a bolt 51, a washer 52, and a pin 53. The bolt 51 has a head, a shank, and a male threaded portion. The head is provided at one end of the shank, and the male threaded portion is provided at the other end of the shank, and the shank has a smaller diameter than the head and the male threaded portion. The pin 53 is cylindrical with both ends open, and has an internal thread on its inner circumferential surface. One end of the pin 53 is provided with a protrusion 53a, and the outer diameter of the protrusion 53a is smaller than the other portions of the pin 53.

[0056] A bolt insertion hole 43b is formed at the tip of the mounting member 43. With the washer 52 placed on the outer surface of the mounting member 43, the bolt 51 is inserted through the washer 52 and the bolt insertion hole 43b. The male thread is positioned on the inner periphery of the mounting member 43, and the pin 53 is screwed into the male thread from the protruding portion 53a side. The protruding portion 53a fits into the bolt insertion hole 43b of the mounting member 43, the pin 53 is fastened to the inner surface of the mounting member 43, and the head is fastened to the outer surface of the mounting member 43. In this way, the shaft-shaped portion 50 and therefore the restricting portion 41 are fixedly provided to the partition wall 30 via the mounting member 43.

[0057] The shaft-shaped portion 50 is inserted into the engagement hole 42a. The outer diameter of the pin 53 is smaller than the inner diameter of the engagement hole 42a. Therefore, the shaft-shaped portion 50 is displaceable relative to the engagement hole 42a (bush 55) in the axial direction (radial direction of the axis A).

[0058] In the gas turbine 1 configured as described above, intake air is compressed in the compressor section 3, and the compressed air flows to the radially outer periphery at the other axial end of the compressor section 3 through the first compressed air passage 6a, flows to the other axial side through the second compressed air passage 6b, is guided to the combustion section 4, flows to the radially outer periphery through the third compressed air passage 6c, and flows into the combustor 4c through the compressed air intake port 4e. The compressed air is mixed with fuel in the combustor 4c. The combustor 4c burns the mixture to generate combustion gas. The generated combustion gas flows out of the combustor 4c through the gas injection port 4d and flows into the annular portion 21 of the gas passage 20. The combustion gas flows through the annular portion 21, the turn-back portion 22, and the outflow portion 23 in sequence, and flows into the turbine nozzle 5b. The combustion gas drives the turbine 5 while flowing through the turbine casing 5A.

[0059] The guide member 10 defines a gas flow path 20 through which high-temperature and high-pressure combustion gas flows, and therefore expands and deforms due to the influence of heat input from the combustion gas. The first guide member 11 and the second guide member 12 can expand both radially and axially.

[0060] When attempting to expand in the radial direction, the bushing 55 can be displaced radially outward along the shaft-shaped portion 50. This allows the load acting on the support portion 40 to be reduced. When attempting to expand in the axial direction, the first guide member 11 and the second guide member 12 can be relatively displaced in the axial direction because the fitting direction of the outer fitting portion 10a is the axial direction. This allows the load acting on the guide member 10 to be reduced.

[0061] In this way, while deformation of the guide member 10 is permitted, the engagement portion 42 constituting the support portion 40 is directly attached to the guide member 10 that defines the gas flow path 20. Compared to a case in which a dedicated support member that does not contribute to defining the gas flow path 20 is attached by separate welding to a member that defines the gas flow path 20 and the support portion is attached to the dedicated support member, the number of welded portions of the guide member 10 or the support portion 40 can be reduced. This makes it possible to reduce thermal stress acting on the guide member 10 and the support portion 40 that supports it, and improve their durability.

[0062] The engagement portion 42 is provided on the extension portion 12b, and the extension portion 12b is disposed at a distance from the portion that defines the gas flow path 20. This can reduce heat input to the support portion 40, improving the durability of the support portion 40. The attachment member 43 is also disposed at a distance from the guide member 10. This also reduces heat input to the support portion 40, improving the durability of the support portion 40.

[0063] Although the embodiment has been described above, the above configuration can be appropriately modified, added, or deleted within the scope of the present invention.

[0064] In the above embodiment, the support portion 40 includes the attachment member 43 that is independent of both the partition wall 30 and the guide member 10. However, the attachment member 43 is not essential. Depending on the positional relationship between the partition wall 30 and the guide member 10, the attachment member 43 may be omitted and the restriction portion 41 may be provided on the flange 34 of the partition wall 30.

[0065] In the above embodiment, the restricting portion 41 is the shaft-shaped portion 50, and the engaging portion 42 is a bushing 55 having an engaging hole 42a through which the shaft-shaped portion 50 is inserted. However, this is merely an example. The supporting portion 40 may be configured in any manner as long as it is capable of supporting the guide member 10 while allowing the guide member 10 to be displaced in one direction (as an example, the radial direction of the spindle 2). In addition, the displacement allowable direction by the supporting portion 40 is not limited to the radial direction of the spindle 2.

[0066] In the above embodiment, the restricting portion 41 is provided on the partition wall 30 and the engaging portion 42 is attached to the guide member 10, but the present invention is not limited to this configuration. Even if the engaging portion 42 is provided on the partition wall 30 and the restricting portion 41 is attached to the guide member 10, the same effects as those of the above embodiment can be achieved. [Explanation of symbols]

[0067] 1. Gas turbine 1A Casing 2 main shaft 3 Compression section 3A Compressor casing 3a Rotor 3b Impeller 3c Containment Space 3d interior wall 3e flange 4 Combustion section 4A Combustor casing 4a 1st cylinder part 4b Second cylinder part 4c Combustor 4d Gas nozzle 4e Compressed air intake 5. Turbine 5A Turbine casing 5a Turbine rotor 5b Turbine nozzle 5c Exhaust port 6a First compressed air passage 6b Second compressed air flow path 6c 3rd compressed air passage 10 Guide member 10a Outer fitting part 11 First guide member 11a Outer cylinder part 11b Inner cylinder part 11c Circular bottom 11d Projecting cylinder part 11e Extension 11f Curved section 12 Second guide member 12a Exterior wall 12b Extension part 12c Expanded section 12d Outer wall 14 Ring material 20 Gas flow path 21 Circular Ring 22 Turned part 23 Outflow 30 Partition Wall 31 Shaft insertion port 32 Disc Section 33 Peripheral wall part 34 Flange 34a screw hole 40 Support part 41 Regulatory Department 42 Engagement part 42a Engagement hole 43 Mounting material 43a, 43b Bolt insertion holes 44 Sim 45 Volts 50 Shaft-shaped part 51 Volts 52 Washer 53 Pin 53a Protrusion 55 Bush 55a Intermediate cylindrical section 55b,55c flange A axis B Center axis

Claims

1. A compression section that compresses the intake air; A combustion section that burns the compressed air; A partition wall that separates the compression section and the combustion section; a guide member defining a gas flow path that guides the combustion gas generated in the combustion section to a turbine; a support portion that supports the guide member within the combustion portion, the support portion having a restricting portion that restricts displacement of the guide member and an engaging portion that mechanically engages with the restricting portion; Equipped with One of the restricting portion and the engaging portion is provided on the partition wall, the other of the restricting portion and the engaging portion is attached to the guide member; A guide support structure for a gas turbine.

2. The restricting portion is provided on the partition wall, and the engaging portion is attached to the guide member, the restricting portion engages with the engaging portion in a manner allowing displacement of the engaging portion in one direction and restricting displacement of the engaging portion in a direction intersecting the one direction; The guide support structure of a gas turbine according to claim 1 .

3. The restricting portion has a shaft-shaped portion, and the engaging portion has an engaging hole through which the shaft-shaped portion is inserted so as to be displaceable in an axial direction of the shaft-shaped portion. The guide support structure of a gas turbine according to claim 2 .

4. The engagement portion restricts displacement of the shaft portion in a direction intersecting the axial direction. The guide support structure of a gas turbine according to claim 3.

5. The restricting portion is provided on the partition wall, and the engaging portion is attached to the guide member, The restricting portion is provided on a mounting member extending from the partition wall toward the combustion portion. The guide support structure for a gas turbine according to any one of claims 1 to 4.

6. The mounting member is disposed in spaced relation to the guide member. The guide support structure of a gas turbine according to claim 5.

7. The guide member includes a first guide member and a second guide member that are fitted to each other so as to be relatively displaceable in a fitting direction, The restricting portion is provided on the partition wall, and the engaging portion is attached to the second guide member. The guide support structure for a gas turbine according to any one of claims 1 to 4.

8. the second guide member is fitted onto the first guide member and has an extension portion located away from the outer circumferential side of the first guide member, The engagement portion is provided on the extension portion. The guide support structure of a gas turbine according to claim 7.

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