Sealing member and gas turbine

Abstract

A seal member that forms a combustion gas flow path of a gas turbine, the seal member including a first body portion having a cooling passage inside, the first body portion being composed of a first end portion that forms one end portion in a circumferential direction, a second end portion that forms the other end portion in the circumferential direction opposite to the one end portion, and an intermediate portion formed between the first end portion and the second end portion, the cooling passage including: an intermediate portion cooling passage that is inclined at a first angle with respect to an axial direction; a first end portion cooling passage that is disposed at the first end portion and is inclined at a second angle with respect to the axial direction; and a second end portion cooling passage that is disposed at the second end portion and is inclined at a third angle with respect to the axial direction, the second angle and the third angle being smaller than the first angle.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to a seal member of a combustor and a gas turbine using the same.

[0002] This application claims priority based on Japanese Patent Application No. 2021-037153 filed on March 9, 2021, and the content thereof is hereby incorporated by reference. BACKGROUND

[0003] In a gas turbine, air compressed by a compressor is mixed with fuel in a combustor and combusted, generating high-temperature combustion gas, and in a turbine having a stator and a rotor, the rotor is rotated, and electric power is extracted using a generator. A seal member is provided between the combustor and the stator of the turbine. The seal member is in contact with the high-temperature combustion gas, and therefore a cooling air passage is provided in the seal member, cooling air is supplied to the cooling air passage, and the main body of the seal member is cooled to prevent thermal damage of the seal member. An example of a cooling structure of the seal member is disclosed in Patent Literature 1.

[0004] PRIOR ART DOCUMENTS

[0005] PATENT LITERATURE

[0006] Patent Literature 1: Japanese Patent Application Publication No. 2000-257862 SUMMARY

[0007] PROBLEMS TO BE SOLVED BY THE INVENTION

[0008] However, the cooling air that cools the seal member is discharged to the combustion gas flow path after cooling the seal member, and therefore further reduction of the cooling air is sought from the viewpoint of improving the performance of the gas turbine.

[0009] An object of the present disclosure is to provide a seal member that can reduce the amount of cooling air while suppressing thermal damage caused by combustion gas of the seal member.

[0010] SOLUTION TO THE PROBLEM

[0011] One aspect of the present disclosure is a seal member that forms a combustion gas flow path of a gas turbine, in which

[0012] The seal member includes a first main body portion that extends in an axial direction and a circumferential direction and has a cooling passage inside,

[0013] The first main body portion is composed of a first end portion that forms one end portion in the circumferential direction, a second end portion that forms the other end portion in the circumferential direction opposite to the one end portion, and an intermediate portion provided between the first end portion and the second end portion,

[0014] The cooling passage includes:

[0015] an intermediate portion cooling passage which is provided in the intermediate portion, is inclined at a first angle with respect to the axial direction, extends in the axial direction, and is provided with a plurality in the circumferential direction;

[0016] a first end portion cooling passage which is provided in the first end portion, is inclined at a second angle with respect to the axial direction, extends in the axial direction, and is provided with a plurality in the circumferential direction; and

[0017] a second end portion cooling passage which is provided in the second end portion, is inclined at a third angle with respect to the axial direction, extends in the axial direction, and is provided with a plurality in the circumferential direction,

[0018] the second angle and the third angle are smaller than the first angle.

[0019] Effects of Invention

[0020] The sealing member according to the present disclosure reduces the amount of cooling air while suppressing thermal damage caused by combustion gas of the sealing member, thereby improving the performance of the gas turbine. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 is a schematic device structure diagram of a gas turbine of an embodiment of the present disclosure.

[0022] Figure 2 is a diagram showing the structure around a combustor of an embodiment of the present disclosure.

[0023] Figure 3 is a diagram showing the structure around a sealing member of an embodiment of the present disclosure.

[0024] Figure 4 is a structure diagram of a sealing member of an embodiment of the present disclosure.

[0025] Figure 5 is a configuration diagram of a cooling passage of a sealing member of an embodiment of the present disclosure, showingthe X-X cross section of Figure 4

[0026] Figure 6 is a schematic diagram of a configuration 1 of a cooling passage.

[0027] Figure 7 is a schematic diagram of a configuration 2 of a cooling passage.

[0028] Figure 8 is a structure diagram showing a modified example of a sealing member.

[0029] Figure 9 is a configuration diagram of a cooling passage of a modified example of a sealing member, showingthe Z-Z cross section of Figure 8

[0030] Figure 10 is a combined structure diagram of the seal member and the turbine stator blade. DETAILED DESCRIPTION

[0031] Hereinafter, an embodiment of the present disclosure will be described based on the drawings.

[0032] Structure of gas turbine

[0033] Reference Figure 1 A gas turbine to which a seal member is applied will be described. Note that, Figure 1 is a schematic configuration diagram of a gas turbine 1 of an embodiment to which a seal member is applied.

[0034] As Figure 1 shown, the gas turbine 1 of an embodiment is provided with: a compressor 2 for generating compressed air; a combustor 4 for generating combustion gas G using the compressed air A and fuel; and a turbine 6 that is driven by the combustion gas G to rotate. In the case of the gas turbine 1 for power generation, a power generator not shown is linked to the turbine 6, and power generation is performed by the rotational energy of the turbine 6.

[0035] Use Figure 1 Each structure in the gas turbine 1 will be described.

[0036] The compressor 2 is provided with: a compressor casing 10; an intake chamber 12 provided on the inlet side of the compressor casing 10 for taking in air; a rotor 8 provided so as to pass through the compressor casing 10 and a turbine casing 22 described later in one body; and various vanes arranged inside the compressor casing 10. The various vanes include: an inlet guide vane 14 provided on the intake chamber 12 side; a plurality of compressor stator vanes 16 fixed to the compressor casing 10 side; and a plurality of compressor rotor vanes 18 planted to the rotor 8 in a manner alternately arranged in the axial direction with respect to the compressor stator vanes 16. In such a compressor 2, the air taken in from the intake chamber 12 is compressed by the plurality of compressor stator vanes 16 and the plurality of compressor rotor vanes 18 to generate the compressed air A. The compressed air A is delivered from the compressor 2 to the combustor 4 on the downstream side in the axial direction.

[0037] The combustor 4 is arranged inside a casing 20. As Figure 1 shown, the combustor 4 is arranged in a ring shape around the rotor 8 inside the casing 20. Fuel and the compressed air A generated by the compressor 2 are supplied to the combustor 4, and the fuel is combusted, thereby generating the combustion gas G that is a working fluid of the turbine 6, which is high in temperature and pressure. The generated combustion gas G is delivered from the combustor 4 to the turbine 6 on the downstream side in the axial direction.

[0038] The turbine 6 has a turbine casing (housing) 22 and various turbine blades arranged in the turbine casing 22. The various turbine blades include a plurality of turbine vanes 24 fixed to the turbine casing 22 side and a plurality of turbine blades 26 arranged on the rotor 8 in a manner alternately arranged in the axial direction with respect to the turbine vanes 24.

[0039] Note that in the turbine 6, the rotor 8 extends in the axial direction, and the combustion gas G discharged from the turbine casing 22 is discharged to the axial downstream side to an exhaust casing 28. In Figure 1 the drawing, the left side is the axial inflow side, and the right side is the axial downstream side. Also, in the following description, in the case of simply being referred to as the radial direction, it indicates a direction orthogonal to the rotor 8. Also, in the case of being referred to as the circumferential direction, it indicates the direction of rotation of the rotor 8.

[0040] The turbine blades 24 are configured to generate a rotational driving force from the high-temperature high-pressure combustion gas G flowing in the turbine casing 22 together with the turbine vanes 24. This rotational driving force is transmitted to the rotor 8, and drives a not-illustrated generator coupled to the rotor 8.

[0041] An exhaust chamber 29 is connected to the axial downstream side of the turbine casing 22 via the exhaust casing 28. The combustion gas G after driving the turbine 6 is discharged to the outside through the exhaust casing 28 and the exhaust chamber 29.

[0042] Structure around combustor

[0043] Figure 2 An outline structure around the combustor 4 of the gas turbine 1 of one embodiment is shown. Figure 3 An outline structure around the turbine vanes 24 and the seal member 40 is shown. As Figure 2 shown, the combustor 4 is arranged in a ring shape in the housing 20 with the rotor 8 as the center, and is installed in the housing 20. The combustor 4 has a plurality of fuel nozzles 30 that supply the fuel FL to the combustor 4, and a combustion cylinder 32 that mixes the fuel FL with the compressed air A and combusts it. The combustion cylinder 32 has an inner cylinder 33 that combusts the fuel FL with the compressed air A to generate the combustion gas G, and a tail cylinder 34 that supplies the combustion gas G to the turbine 6. A flange 35 is arranged at the axial downstream end of the tail cylinder 34, and the flange 35 is connected to the turbine vane 24 via the seal member 40. The flange 35 is formed on the entire circumference of the outer periphery of the tail cylinder 34 that forms the combustion gas flow path 37.

[0044] As Figure 3A prescribed gap is provided between the flange 35 of the nozzle 34 and the turbine stator 24 connected on the axial downstream side to absorb the axial thermal expansion, and a detachable seal member 40 is inserted. The seal member 40 is provided in a plurality of rings centered on the rotor 8.

[0045] The seal member 40 is connected at the axial upstream end 42e to the flange 35 of the nozzle 34 and at the axial downstream end 42f to the turbine stator 24. The cross-sectional shape of the flange 35 of the nozzle 34 forming the combustion gas flow path 37 viewed from the axial downstream side forms a radially outer side longer annular outer edge 35b and a radially inner side shorter annular inner edge 35a, and as a whole forms a rectangular passage cross-section.

[0046] Seal member

[0047] The seal member 40 is circumferentially divided, and an inner side seal member 40a disposed on the radially inner side and an outer side seal member 40b disposed on the radially outer side are combined to constitute one set of seal members 40. One set of seal members 40 is disposed on the axial downstream side corresponding to one set of combustors 4.

[0048] The axial upstream side of the seal member 40 is connected via the flange 35 to the nozzle 34 forming the combustion gas flow path 37, and the axial downstream side of the seal member 40 is fitted to the shroud 25 of the turbine stator 24 in a detachable manner. The radially outer side surface of the inner side seal member 40a (corresponding to the outer surface of the inner edge 35a) and the radially inner side surface of the outer side seal member 40b (corresponding to the inner surface of the outer edge 35b) are in contact with the combustion gas flow path 37.

[0049] As an example of the seal member 40, Figure 4The structure of the inner sealing member 40a is shown. The inner sealing member 40a is integrally formed from a plate-shaped first main body portion 42, a plate-shaped second main body portion 46, a plate-shaped third main body portion 47, and a fitting portion 48. The plate-shaped first main body portion 42 is located radially outward, extending circumferentially from the axially upward flowing side downstream. The plate-shaped second main body portion 46 is connected to the axially upstream end 42e of the first main body portion 42, extending radially inward and circumferentially. The plate-shaped third main body portion 47 protrudes axially downstream from the radially middle position of the second main body portion 46. The fitting portion 48 is connected to the radially inner end 46a of the second main body portion 46, extending axially upward and radially outward. Between the second main body portion 46 and the fitting portion 48, the radially inner end is closed, forming a gap extending radially outward, allowing the flange 35 of the tail cylinder 34 to be inserted radially outward. Furthermore, between the first main body portion 42 and the third main body portion 47, there is a structure in which a recess 50 is formed that is recessed from the axially downstream end 42f of the first main body portion 42 toward the axially upward flowing side, and a protrusion 25a is provided toward the leading edge 24a side of the turbine stator blade 24 and protrudes toward the axially upward flowing side of the shroud 25. Figure 3 (Matching). It should be noted that the inner sealing member 40a has a cooling passage 50, which will be described later, in order to suppress thermal damage caused by heat input from the combustion gas flow path 37. The cooling air supplied to the cooling passage 50 is compressed air A within the space 21 surrounded by the housing 20.

[0050] Structure of Cooling Pathways

[0051] like Figure 4 As shown, the outer surface 42a of the first main body 42, facing radially outward, forms a gas passage surface facing the combustion gas flow path 37. Therefore, to suppress thermal damage caused by the heat input from the combustion gas G flowing in the combustion gas flow path 37, the first main body 42 includes a cooling passage 50 inside. Multiple cooling passages 50 extend axially and are arranged at circumferential intervals, connecting to the opening 42b formed in the combustion gas flow path 37 at the axial downstream end 42f of the first main body 42. Except for a portion, the cooling passages 50 are formed as inclined passages with an angle α relative to the axial direction. Inside the second main body 46, which is connected to the axial upstream end 42e of the first main body 42 and extends radially, multiple radially extending supply passages 58 are arranged at circumferential intervals. An opening 46b connecting to the supply passage 58 is formed at the radially inner end 46a of the second main body 46. The supply passage 58 is located radially outside the second main body 46 and connects via a connection point 42h to a cooling passage 50 disposed inside the first main body 42. The supply passage 58 connects via an opening 46b to the space 21 (enclosed by the housing 20). Figure 2(Connection). It should be noted that the cooling passage 50 and the supply passage 58 may have the same orifice diameter d, or the orifice diameter d of the cooling passage 50 may be smaller than that of the supply passage 58. By making the orifice diameter d of the supply passage 58 larger than that of the cooling passage 50, the pressure loss of the cooling air in the supply passage 58 is reduced, and higher pressure cooling air is supplied to the cooling passage 50. An embodiment of the arrangement of the cooling passage 50 disposed in the first main body 42 will be described below.

[0052] Implementation Method

[0053] Figure 5 Show Figure 4 The XX-section diagram shows the configuration of the cooling passage 50 arranged in the first main body 42 as viewed from the radially outer side. Figure 5 As shown, the first main body portion 42 is divided into three regions with different arrangements of cooling passages 50 in the circumferential direction of the first main body portion 42. The first main body portion 42 includes: a middle portion 43, which is disposed in the middle region in the circumferential direction of the first main body portion 42; a first end portion 44, which is disposed in the region from one end portion of the first main body portion 42 in the circumferential direction, namely the first end face 42c, to the middle portion 43; and a second end portion 45, which is disposed in the region from the other end portion of the first main body portion 42 in the circumferential direction, namely the second end face 42d, to the middle portion 43. The cooling passages 50 formed in the first main body portion 42 are composed of a middle portion cooling passage 52 formed in the middle portion 43, a first end portion cooling passage 54 formed in the first end portion 44, and a second end portion cooling passage 56 formed in the second end portion 45.

[0054] Intermediate Cooling Passage

[0055] The cooling passage 50 of the first main body 42 is formed by a plurality of inclined passages having an inclination angle α relative to the axial direction. The intermediate cooling passage 52 is composed of a plurality of straight inclined passages having the same inclination angle α1 (first angle) relative to the axial direction and arranged at a certain interval (space) LP in the circumferential direction. The upstream end of the intermediate cooling passage 52 is formed inside the second main body 46 and is connected via a connection point 42h to a plurality of supply passages 58 arranged at a certain interval (space) LP in the circumferential direction. The supply passages 58 extend radially along the second main body 46 and are individually connected to the cooling passages 50 of the first main body 42 one by one. Here, the opening density can also be used instead of the circumferential arrangement spacing (space) LP of the cooling passages 50. That is, the intermediate cooling passage 52 is formed by the cooling passage 50, which is composed of a plurality of inclined passages that are parallel to each other in the circumferential direction and have the same opening density. It should be noted that when the aperture d and the arrangement spacing (space) LP of the cooling passage 50 are set, the opening density can be expressed as [d / LP]. Figure 5In the present embodiment, the inclination angle a (a1, a2, a3) of the cooling passage 50 with respect to the axial direction refers to an acute angle with respect to the clockwise rotation direction of the axial direction.

[0056] The first end portion cooling passage

[0057] As Figure 5 illustrated, the first end portion cooling passage 54 is arranged on the first end portion 44 side in such a manner as to be adjacent to the cooling passage 52a closest to the first end surface 42c among the intermediate portion cooling passages 52 in the circumferential direction. The first end portion cooling passage 54 is formed by a plurality of cooling passages 50 arranged at a prescribed interval in the circumferential direction between the first end surface 42c and the intermediate portion 43. The cooling passages 50 constituting the first end portion cooling passage 54 are arranged so that, at an axial intermediate position, the arrangement pitch (interval) LP in the circumferential direction becomes larger, or the inclination angle a with respect to the axial direction becomes larger, or the opening density becomes smaller, as the intermediate portion cooling passages 52 are approached in the circumferential direction from the first end surface 42c side. That is, the first end portion cooling passage 54 is constituted by linearly inclined passages inclined in the same direction as the intermediate portion cooling passages 52 at an inclination angle a2 (second angle) smaller than the inclination angle al (first angle) of the intermediate portion cooling passages 52 with respect to the axial direction. The first end portion cooling passage 54 is connected at the axial upstream end 42e of the first main body portion 42 to the supply passage 58 formed inside the second main body portion 46 via a connection point 42h. The supply passage 58 in the radially extending supply passage 58 of the second main body portion 46, which is connected to the first end portion cooling passage 54 at the radially outer end, is arranged at a certain interval (the same arrangement pitch LP) in the circumferential direction of the second main body portion 46. Therefore, the arrangement pitch LP in the circumferential direction of the cooling passages 50 at the axial upstream end 42e of the first end portion cooling passage 54 to which the supply passage 58 is connected is arranged at the same arrangement pitch LP as the supply passage 58. Note that the cooling passage 54a arranged closest to the first end surface 42c among the cooling passages 50 constituting the first end portion cooling passage 54 is arranged along the axial direction substantially in parallel to the first end surface 42c.

[0058] As Figure 5As shown, the first end portion cooling passage 54 is arranged in the range from the first end surface 42c of the first main body portion 42 toward the end portion on the other side in the circumferential direction, that is, the second end surface 42d, up to the intermediate portion cooling passage 52, as described above. As described above, the cooling passages 50 at the axial upstream end 42e of the first end portion cooling passage 54 are arranged at the same arrangement pitch (interval) LP or opening density in the circumferential direction, but can be smaller than the arrangement pitch (interval) LP in the circumferential direction of the cooling passages 50 at the axial upstream end 42e of the intermediate portion cooling passage 52, or can have a larger opening density. On the other hand, the arrangement pitch (interval) LP in the circumferential direction of the cooling passages 50 at the axial downstream end 42f of the first end portion cooling passage 54 or the inclination angle a with respect to the axial direction is formed so as to gradually increase from the first end surface 42c side toward the intermediate portion cooling passage 52, and the opening density is formed so as to gradually decrease from the first end surface 42c side toward the intermediate portion cooling passage 52.

[0059] Second end portion cooling passage

[0060] As Figure 5 shown, the second end portion cooling passage 56 is arranged on the second end portion 45 side on the opposite side in the circumferential direction of the first end portion cooling passage 54 in such a manner as to be adjacent to the cooling passage 52b of the intermediate portion cooling passage 52 that is closest to the second end surface 42d. The second end portion cooling passage 56 is formed by a plurality of cooling passages 50 arranged at a prescribed interval in the circumferential direction between the second end surface 42d and the intermediate portion 43. The cooling passages 50 that constitute the second end portion cooling passage 56 are arranged so as to, at an axial intermediate position, increase in the circumferential arrangement pitch (interval) LP or increase in the inclination angle a with respect to the axial direction or decrease in the opening density as the second end surface 42d side is approached in the circumferential direction toward the intermediate portion cooling passage 52. That is, the second end portion cooling passage 56 is constituted by straight-line-shaped inclined passages that are inclined in the same direction as the cooling passages 50 of the intermediate portion cooling passage 52 at an inclination angle a3 (third angle) that is smaller than the inclination angle al (first angle) of the intermediate portion cooling passage 52 with respect to the axial direction. The second end portion cooling passage 56 is connected at the axial upstream end 42e of the first main body portion 42 to a supply passage 58 formed inside the second main body portion 46 via a connection point 42h. The supply passage 58 of the second main body portion 46 is constituted by supply passages 58 arranged parallel to each other in the circumferential direction of the second main body portion 46. Note that the cooling passage 56a arranged closest to the second end surface 42d side among the cooling passages 50 that constitute the second end portion cooling passage 56 is arranged along the axial direction in approximately parallel relation to the second end surface 42d.

[0061] As described above, the second end portion cooling passages 56 are arranged between the second end surface 42d of the first main body portion 42 and the intermediate portion cooling passages 52. The cooling passages 50 at the axial downstream end 42f of the second end portion cooling passages 56 are arranged at the same arrangement pitch (interval) LP or opening density in the circumferential direction as the intermediate portion cooling passages 52. On the other hand, the arrangement pitch (interval) LP of the cooling passages 50 in the circumferential direction at the axial upstream end 42e of the second end portion cooling passages 56 is formed so as to gradually increase as it goes from the second end surface 42d side toward the intermediate portion cooling passages 52, and the opening density is formed so as to gradually decrease as it goes from the second end surface 42d side toward the intermediate portion cooling passages 52. Note that the second end portion cooling passages 56 are connected to the supply passages 58 of the second main body portion 46 one-to-one via the connection points 42h at the axial upstream end 42e, similarly to the first end portion cooling passages 54. The arrangement pitch (interval) LP of the supply passages 58 in the circumferential direction in the second main body portion 46 is arranged in parallel with the arrangement pitch (interval) LP of the second end portion cooling passages 56 at the axial upstream end 42e of the first main body portion 42.

[0062] As Figure 5 shown, the intermediate portion cooling passages 52 are formed by the inclined passages of all of the cooling passages 50 at the same inclination angle al, and are composed of straight inclined passages having an inclination angle a with respect to the axial direction that is larger than that of the cooling passages 50 of the first end portion cooling passages 54 and the second end portion cooling passages 56. The opening density of the cooling passages 50 in the circumferential direction at the axial intermediate position is formed so as to be larger for the intermediate portion cooling passages 52 than for the first end portion cooling passages 54 and the second end portion cooling passages 56, and the arrangement pitch (interval) LP of the cooling passages 50 in the circumferential direction at the axial intermediate position is formed so as to be smaller for the intermediate portion cooling passages 52 than for the first end portion cooling passages 54 and the second end portion cooling passages 56.

[0063] The intermediate portion cooling passages 52 formed in the intermediate portion 43, the first end portion cooling passages 54 formed on the first end portion 44 side, and the second end portion cooling passages 56 formed on the second end portion 45 side are set by the arrangement of the cooling passages 50 as described above. As Figure 5As shown, the first body portion 42 is formed with a width that is substantially the same at the circumferential width of the axial upstream end 42e and the axial downstream end 42f. Therefore, when the intermediate portion cooling passage 52 is provided in the intermediate portion 43 of the first body portion 42, the circumferential width of the intermediate portion cooling passage 52 is formed with a width that is the width of the circumferential direction between the cooling passage 52a and the cooling passage 52b, and the circumferential width at the axial upstream end 42e and the circumferential width at the axial downstream end 42f are formed with substantially the same width. On the other hand, the intermediate portion cooling passage 52 is formed by an inclined passage, and therefore the intermediate portion 43 in which the intermediate portion cooling passage 52 is provided is sandwiched in the circumferential direction, and the circumferential width at the axial upstream end 42e and the axial downstream end 42f of the first end portion 44 side and the second end portion 45 side are not formed with the same width, but one is formed with a larger circumferential width and the other is formed with a smaller circumferential width. In Figure 5 In the case of the embodiment shown, the circumferential width at the axial upstream end 42e of the first end portion 44 side in which the first end portion cooling passage 54 is formed is formed with a smaller circumferential width than the circumferential width at the axial downstream end 42f, and the circumferential width at the axial upstream end 42e of the second end portion 45 side in which the second end portion cooling passage 56 is formed is formed with a larger circumferential width than the circumferential width at the axial downstream end 42f.

[0064] Figure 5 The cooling passage 50 shown is an example in which the cooling passage 50 is configured so as to be inclined toward the direction in which the second end surface 42d side is approached from the first end surface 42c side as the axial downstream side is approached, and is configured with an inclined angle a that forms an acute angle with respect to the axial direction in the clockwise direction. On the other hand, conversely, the cooling passage 50 that is configured in the entire first body portion 42 can also be a configuration in which the cooling passage 50 is configured so as to be inclined toward the direction in which the first end surface 42c side is approached from the second end surface 42d side as the axial downstream side is approached, and is configured with an inclined angle a that forms an acute angle with respect to the axial direction in the counterclockwise direction. In this case, the circumferential width at the axial upstream end 42e of the first end portion 44 side in which the first end portion cooling passage 54 is formed is formed with a larger circumferential width than the circumferential width at the axial downstream end 42f. In addition, the circumferential width at the axial upstream end 42e of the second end portion 45 side in which the second end portion cooling passage 56 is formed is formed with a smaller circumferential width than the circumferential width at the axial downstream end 42f. That is, the circumferential width at the axial upstream end 42e of the first end portion 44 side in which the first end portion cooling passage 54 is configured and the circumferential width at the axial downstream end 42f, and the circumferential width at the axial upstream end 42e of the second end portion 45 side in which the second end portion cooling passage 56 is configured and the circumferential width at the axial downstream end 42f become in a reverse relationship. Note that the above description is described with the circumferential width at the axial upstream end 42e and the axial downstream end 42f of the first body portion 42 being formed with substantially the same width, but the same consideration method can also be applied in the case in which the circumferential width at the axial upstream end 42e is larger than the axial downstream end 42f of the first body portion 42.

[0065] However, the outer surface 42a of the first main body 42 faces the combustion gas flow path 37 and is therefore heated due to the heat input from the combustion gas G. Therefore, the first main body 42 needs to be cooled to a temperature below the permissible metal temperature. In particular, the middle portion 43 is more easily heated than the first end 44 and second end 45 on both sides in the circumferential direction, and the permissible metal temperature is suppressed to be lower. On the other hand, the first end 44 and second end 45 have relatively lower heat loads and less thermal constraint from other adjacent sealing members 40 in the circumferential direction compared to the middle portion 43, thus generating less thermal stress. Therefore, the permissible metal temperature of the first end 44 and second end 45 can be set higher than the permissible metal temperature of the middle portion 43. That is, the arrangement density of the cooling passages 50 disposed at the first end 44 and second end 45 can be lower than the arrangement density of the cooling passages 50 disposed at the middle portion 43, within a range not exceeding the permissible metal temperature. That is, the circumferential spacing (interval) LP of the cooling passages 50 disposed on the first end 44 side and the second end 45 side is larger than the circumferential spacing (interval) LP of the cooling passages 50 disposed on the middle part 43 which are in the same axial position, thereby reducing the passage surface area of ​​the cooling passages 50 per unit area of ​​the first main body part 42. Here, the configuration density of the cooling passages 50 refers to the passage surface area of ​​the cooling passages 50 disposed on the first main body part 42 within a range of unit area.

[0066] Cooling capacity of cooling pathways

[0067] Next, the relationship between the tilt angle α of the cooling path, which is a tilted path, and the cooling capacity will be explained. Figure 6 This is a schematic diagram of the configuration 1 of the cooling passage 50. Figure 7 This is a schematic diagram of the configuration 2 of the cooling passage 50. Figure 6 and Figure 7 The cooling structure formed inside the same flat plate 60 has multiple cooling passages 50 that extend axially and are arranged at predetermined intervals in the circumferential direction, and the plate 60 is cooled by cooling air flowing in the cooling passages 50. Figure 6 The configuration 1 shown indicates that the cooling passage 50 extends in the same direction as the axial direction. Figure 7 The configuration 2 shown represents a cooling passage 50 having an inclined passage with an inclination angle [α0] relative to the axial direction. Figure 6 Configuration 1 and Figure 7 The relationship between the tilt angle α of the cooling passage 50 and the cooling capacity is compared with configuration 2 to illustrate this.

[0068] like Figure 3 and Figure 4As shown, in the sealing member 40 shown in the present embodiment, the first body portion 42 is heated due to heat input from the combustion gas G of the gas passage surface, that is, the outer surface 42a, which is in contact with the combustion gas G, and thus the first body portion 42 is cooled by the cooling air flowing inside the cooling passage 50. Figure 6 and Figure 7 The plate material 60 shown is equivalent to the first body portion 42 of the sealing member 40.

[0069] Figure 6 The cooling passage 50 of the configuration 1 shown is formed inside the plate material 60 and is a structure in which the cooling passages 50 extending in the axial direction at an inclination angle of 0 degrees with respect to the axial direction of the plate material 60 are arranged at a prescribed arrangement pitch LP0 in the circumferential direction of the plate material 60, and is the most basic cooling structure of the plate material based on general convection cooling.

[0070] Figure 6 The cross section Y1-Y1 of the configuration 1 shown is a cross section of the plate material 60 viewed from the axial direction downstream side and shows a structure in which the cooling passages 50 are arranged at the arrangement pitch LP0 in the circumferential direction. The cooling passages 50 of the arrangement pitch LP0 in the circumferential direction shown in the configuration 1 cool the heat input of the combustion gas from the outside into the plate material 60 and are arranged in such a manner that the metal temperature at the axial direction downstream end 60b of the plate material 60 becomes equal to or less than the allowable value, thereby suppressing thermal damage to the plate material 60. That is, the cooling capacity of each of the plurality of cooling passages 50 arranged in the circumferential direction is proportional to the passage surface area of the cooling passage 50. In addition, as the range of the plate material 60 that each of the cooling passages 50 can cool, a certain region of the plate material 60 that expands from the central axis 50a of the cooling passage 50 to both sides in the circumferential direction is set as a heated region 61. In the configuration 1 shown, the heated region 61 is set as a region in which the central axis 50a of the cooling passage 50 is set as a center line, and a rectangular shaped region having an axial direction width L1 and a circumferential direction width LP0 equivalent to the passage length of the cooling passage 50 is surrounded by two first intermediate lines 61a that determine the intermediate positions between the cooling passages 50 on both sides adjacent in the circumferential direction and the axial direction upstream end 60a and the axial direction downstream end 60b of the plate material 60. Figure 6 In the configuration 1 shown, the heated region 61 is centered on the central axis 50a of the cooling passage 50, has a width in the circumferential direction of the plate material 60 equivalent to the arrangement pitch LP0, and is demarcated up to the axial direction upstream end 60a and the axial direction downstream end 60b of the plate material 60. That is, the heated region 61 is demarcated as a region in which the central axis 50a of the cooling passage 50 is set as a center line, and a rectangular shaped region having an axial direction width L1 and a circumferential direction width LP0 equivalent to the passage length of the cooling passage 50 is surrounded by two first intermediate lines 61a that determine the intermediate positions between the cooling passages 50 on both sides adjacent in the circumferential direction and the axial direction upstream end 60a and the axial direction downstream end 60b of the plate material 60. The passage length L1 of the cooling passage 50 in the configuration 1 is the same length as the axial direction width L1 of the plate material 60.

[0071] The basic idea of selecting the configuration of the cooling passage 50 in the configuration 1 is as follows: heat input from the combustion gas G enters the heated region 61 of the plate 60, the heat input entering the heated region 61 is cooled by the cooling air flowing in the cooling passage 50 disposed in the heated region 61, so that the metal temperature at the axial downstream end 60b of the plate 60 is restrained within the allowable value, and the metal temperature of the plate 60 at the axial downstream end 60b becomes a certain metal temperature in the circumferential direction. If the configuration 1 of this consideration method is selected, each heated region 61 of the plate 60 provided with the plurality of cooling passages 50 is cooled by the respective corresponding cooling passages 50, the metal temperature of the plate 60 at the entire region of the plate 60 provided with the cooling passages 50 is restrained within the allowable value, and it can be considered that the metal temperature of the plate 60 in the circumferential direction at the axial downstream end 60b is maintained constant.

[0072] On the other hand, Figure 7 The basic idea of the cooling structure of the cooling passage 50 of the configuration 2 shown is as follows. The cooling passage 50 of the configuration 2 is a slanted passage in which the extension direction of the cooling passage 50 is not coincident with the axial direction and the inclination angle [a0] with respect to the axial direction is slanted. The configuration 2 differs from the configuration 1 in that, by providing the configuration of the cooling passage 50 as a slanted passage having the inclination with respect to the axial direction, the cooling surface area of the cooling passage 50 can be increased, the cooling capacity can be increased, and the amount of cooling air can be reduced, as compared with the configuration 1. Figure 7 The cross section Y2-Y2 shown indicates the cross section of the plate 60 of the configuration 2 as viewed from the axial downstream end 60b, and the cross section Y3-Y3 indicates the cross section as viewed from the axial upstream end 60a of the plate 60. The arrangement pitch (interval) LP of the cooling passages 50 in the circumferential direction is the same as the arrangement pitch LPO of the cooling passages 50 of the configuration 1 at the axial upstream end 60a, but the arrangement pitch LPl at the axial downstream end 60b is larger than the arrangement pitch LPO at the axial upstream end 60a.

[0073] Figure 7The cooling passage 50 of the configuration 2 is a slanted passage having a slant angle [a0] with respect to the axial direction, and thus the passage length L2 of each of the cooling passages 50 is longer than that of the cooling passage 50 of the configuration 1 if the center axis 50a is taken as a reference, and the passage surface area of the cooling passage 50 is expanded. The cooling capacity of each of the cooling passages 50 is increased by the increase in the passage surface area of the cooling passage 50. The increase in the cooling capacity of the cooling passage 50 resulting from the provision of the cooling passage 50 as a slanted passage is based on the idea that, in the configuration 2, the cooling capacity of each of the cooling passages 50 is increased by the increase in the passage length L2, and the increase in the cooling capacity of the cooling passage 50 cools the increased portion of the heat input from the combustion gas G. That is, the cooling area of the heated region 61 of the plate member 60, which receives the heat input from the combustion gas G, is increased by the provision of the cooling passage 50 as a slanted passage. The heat input from the combustion gas G is increased from the increased portion of the area of the heated region 61, and the increased portion of the cooling surface area of the cooling passage 50 cools the increased portion of the heat input, whereby the metal temperature of the plate member 60 is suppressed within the allowable value, and the cooling air amount can be reduced.

[0074] That is, the cooling structure of the plate member 60 having the cooling passage 50 of the configuration 2 can be regarded as a cooling structure having a cooling capacity equivalent to that of the cooling passage 50 of the configuration 1 by the increase in the cooling capacity of the cooling passage 50 resulting from the provision of the cooling passage 50 as a slanted passage. The cooling passage 50 having an equivalent cooling capacity means that the cooling capacity per unit area of the heated region 61 of the plate member 60 is the same. That is, in the configuration 2 in which the cooling passage 50 having an increased cooling capacity is provided as a slanted passage, the cooling area of the heated region 61 is increased in correspondence with the amount of the increase in the cooling capacity, and thus the capacity to absorb the heat input from the combustion gas G is increased. The idea is that the length and the width of the plate member 60 are the same, but the cooling capacity per unit area of the heated region 61 of the plate member 60 of the configuration 2 of the slanted passage is set to be the same as that of the heated region 61 of the cooling passage 50 of the configuration 1 in which the cooling passage 50 extends in parallel with the axial direction taken as a reference. Note that, in the configuration 2, the increase in the heated region 61 of the plate member 60 means that the arrangement pitch (interval) LP of the circumferential direction of the cooling passage 50 at the upstream end 60a in the axial direction of the plate member 60 is fixed, and thus the slant angle [a0] with respect to the axial direction of the cooling passage 50 is increased, and thus the circumferential width of the heated region 61, or the arrangement pitch (interval) LP of the circumferential direction of the cooling passage 50, is expanded. It can be said that the cooling area of the heated region 61 is increased by the expansion of the arrangement pitch (interval) LP of the circumferential direction of the cooling passage 50.

[0075] In the following description, the cooling structure of the cooling passage 50 of the configuration 2 is described in comparison with the configuration 1. As Figure 7As shown, in the case of the cooling passage 50 with an inclination angle [α0] relative to the axial direction in configuration 2, the passage length L2 along the central axis 50a of the cooling passage 50, from the upstream end 60a to the downstream end 60b of the plate 60, is formed to be longer than the passage length L1 of the cooling passage 50 in configuration 1 by a difference DL. That is, in the case of the cooling passage 50 in configuration 2, compared with configuration 1, the passage surface area of ​​the cooling passage 50, which is equivalent to the difference DL between the passage length L2 of configuration 2 and the passage length L1 of configuration 1, becomes larger, and the cooling capacity of the cooling plate 60 increases.

[0076] On the other hand, such as Figure 7 As shown, in the heated area 63 of the plate 60 corresponding to the cooling passage 50 of configuration 2, the heated area 61 of the plate 60 expands as the cooling capacity of the cooling passage 50 increases. That is, for the setting of the heated area 63 of configuration 2, based on the cooling area of ​​the heated area 61 corresponding to the cooling passage 50 of the passage length L1 of configuration 1, a heated area 62 equivalent to the difference DL of the passage length L2 of configuration 2 is calculated based on the ratio of the difference DL of the passage length increase relative to the passage length L1 of configuration 1. As the area where the heated area 62 is added to the heated area 61 of configuration 1, the heated area 63 of configuration 2 after the increase in cooling capacity is selected.

[0077] In configuration 2, such as Figure 7 As shown, the arrangement spacing (interval) LP at the axial upstream end 60a of the plate 60 is fixed with the same arrangement spacing LP0 as in configuration 1. On the other hand, the arrangement spacing (interval) LP at the axial downstream end 60b is expanded to an arrangement spacing LP1 that is larger than the arrangement spacing LP0 in configuration 1. Specifically, as Figure 7 As shown, the heated region 61 in configuration 2, which has the same cooling area as the heated region 61 in configuration 1, corresponds to a rhomboid region surrounded by line segments P1P2, P2R2, R2R1, and R1P1. Furthermore, a heated region 62, corresponding to the increase in cooling capacity of the cooling passage 50 accompanying the inclined passage, is formed adjacent to both sides of the heated region 61 in the circumferential direction. It is assumed that the cooling area of ​​the heated region 62, corresponding to the increase in cooling capacity of the passage surface area corresponding to the increase in the passage length L2 of the accompanying cooling passage 50, is equally divided into two regions and formed on both sides of the heated region 61 in the circumferential direction.

[0078] Specifically, the heated increased region 62 is constituted by a first increased region 62a of a triangular shape surrounded by the line segment P1R1, the line segment R1Q1, and the line segment Q1P1 adjacent to one side in the circumferential direction of the heated region 61, and a second increased region 62b of a triangular shape surrounded by the line segment P2R2, the line segment R2Q2, and the line segment Q2P2 arranged adjacent to the other side in the circumferential direction of the heated region 61. By increasing the first increased region 62a and the second increased region 62b in the heated region 61, the heated region 63 of the plate material 60 corresponding to one cooling passage 50 in the arrangement 2 is demarcated. That is, the region after the heated increased region 62 is added to the heated region 61 having the same cooling area as the arrangement 1 becomes the heated region 63 of the arrangement 2 having an expanded cooling area of the plate material 60.

[0079] By allocating the amount of increase in the cooling capacity of the cooling passage 50 to the heated increased region 62 constituted by the first increased region 62a and the second increased region 62b as described above, the line segment R1Q1 of the first increased region 62a and the line segment R2Q2 of the second increased region 62b become the amount of increase DLP in the arrangement pitch (interval) LP of the cooling passage 50 in the circumferential direction at the axial downstream end 60b in the arrangement 2.

[0080] The amount of increase in the arrangement pitch (interval) LP of the cooling passage 50 in the circumferential direction corresponding to the first increased region 62a and the second increased region 62b at the axial downstream end 60b of the plate material 60, respectively, becomes 1 / 2DLP. Therefore, the arrangement pitch LP1 of the cooling passage 50 at the axial downstream end 60b in the arrangement 2 is a value obtained by increasing the arrangement pitch LP of the heated increased region 62 by the amount of increase DLP with respect to the arrangement pitch LPO of the arrangement 1.

[0081] With regard to the cooling structure of the cooling passage 50 of the arrangement 1, at the axial downstream end 60b of the plate material 60, in a case where the metal temperature of the plate material 60 is maintained within the allowable value and the circumferential metal temperature is maintained constant, as described above, even in the cooling structure of the cooling passage 50 of the arrangement 2 having the same cooling capacity as the cooling passage 50 of the arrangement 1, it can be considered that the metal temperature at the axial downstream end 60b of the plate material 60 is maintained within the allowable value and the circumferential metal temperature is maintained at a substantially constant temperature.

[0082] The relationship between the inclination angle a of the cooling passage 50 and the cooling capacity when the configuration of the cooling passage 50 is changed from configuration 1 to configuration 2 becomes the above-described relationship. Therefore, as the inclination angle a of the cooling passage 50 becomes larger, the cooling capacity of the cooling passage 50 increases, the cooling area of the heated region 63 expands, and the cooling capacity that can absorb the heat input from the combustion gas G of the heated region 63 increases. In addition, along with the increase in the cooling area of the heated region 63 due to the increase in the inclination angle a of the cooling passage 50, the arrangement pitch (interval) LP in the circumferential direction of the cooling passage 50 expands. Note that, by expanding the inclination angle a of the cooling passage 50, the passage length L2 of the cooling passage 50 becomes longer, and the temperature increase of the cooling air flowing inside progresses. However, for example, even if the temperature of the cooling air flowing inside the cooling passage 50 increases, the advantage of the increase effect of the cooling capacity along with the expansion of the passage surface area due to the increase in the passage length is great.

[0083] Note that, in the case of configuration 3 (not shown) of the cooling passage 50 constituted by an inclined passage having a certain inclination angle a applied instead of configuration 1 of the cooling passage 50, the passage length of the cooling passage 50 becomes longer compared to configuration 1, and the cooling capacity of the cooling passage 50 increases by an amount corresponding to the difference DL in the passage length. On the other hand, the heated region 61 in configuration 3 is not added with an increase region but maintains the state of configuration 1, and the arrangement pitch LP of the cooling passage 50 is not changed. In the case of configuration 3 in which the same arrangement pitch LP0 as configuration 1 is selected in the range from the axial upstream end 60a to the axial downstream end 60b of the plate material 60, the amount of increase in the cooling capacity corresponding to the difference DL in the passage length of the cooling passage 50 will be excessive. As a result, the plate material 60 becomes an over-cooled state, the amount of cooling air is lost due to the supply of excessive cooling air, and the efficiency of the gas turbine is reduced. That is, in the case of changing the configuration of the cooling passage 50 from configuration 1 to configuration 3, it is desirable to reduce the amount of cooling air in accordance with the amount of increase in the cooling capacity. Therefore, if the arrangement pitch LP (interval) in the circumferential direction of the cooling passage 50 is selected in such a manner that the cooling capacity of the cooling passage 50 in the case of configuration 1 and the cooling capacity of the cooling passage in the case of configuration 2 become equivalent as the cooling capacity per unit area of the plate material 60, and an appropriate amount of cooling air is selected together, the amount of cooling air is reduced, and the loss of the amount of cooling air is suppressed.

[0084] Figure 5The configuration of the cooling passages 50 of the first end portion 44 and the second end portion 45 is selected based on the following idea. As described above, when the cooling passages 50 are provided as inclined passages, the inclination angle a of the cooling passages 50 and the cooling area of the heated region 63 that increases in accordance with the increase in the cooling capacity of the corresponding cooling passages 50 are set, and the arrangement pitch (interval) LP is set based on the set cooling area. In the case of the first end portion cooling passages 54 arranged in the first end portion 44, for the arrangement of the cooling passages 50 at the axial intermediate position, the arrangement of the cooling passages 50 is selected with reference to the cooling passage 54a having the inclination angle [0 degrees] with respect to the axial direction that is closest to the first end surface 42c, and the inclination angle a of the cooling passages 50 gradually increases in the circumferential direction. That is, as the intermediate portion cooling passages 52 are approached in the circumferential direction from the first end surface 42c of the first main body portion 42, the inclination angle a of the cooling passages 50 in the axial direction increases, the cooling area of the heated region 63 increases in accordance with the increase in the cooling capacity of the cooling passages 50, and the arrangement pitch (interval) LP in the circumferential direction of the cooling passages 50 increases, so that the arrangement in which the opening density is small is selected.

[0085] In the case of the second end portion cooling passages 56 arranged in the second end portion 45, for the arrangement of the cooling passages 50 at the axial intermediate position, the arrangement of the cooling passages 50 is selected with reference to the cooling passage 56a having the inclination angle [0 degrees] with respect to the axial direction that is closest to the second end surface 42d. That is, as the intermediate portion cooling passages 52 are approached in the circumferential direction from the second end surface 42d of the first main body portion 42, the inclination angle a of the cooling passages 50 in the axial direction increases, the cooling area of the heated region 63 increases in accordance with the increase in the cooling capacity of the cooling passages 50, and the arrangement pitch (interval) LP in the circumferential direction increases, so that the arrangement in which the opening density is small is selected. In this regard, it is the same idea as the first end portion cooling passages 54. However, in the case of the second end portion cooling passages 56, the arrangement pitch (interval) LP in the circumferential direction is large at the axial upstream end 42e having a low metal temperature compared to the axial downstream end 42f having a high metal temperature. Therefore, the arrangement pitch (interval) LP at the axial downstream end 42f is set to be the same as the arrangement pitch (interval) LP of the intermediate portion cooling passages 52 in such a manner that the metal temperature at the axial downstream end 42f does not exceed the allowable value.

[0086] In comparing the configurations of the first end portion cooling passages 54 and the second end portion cooling passages 56, the configurations of the first end portion cooling passages 54 and the second end portion cooling passages 56 are substantially the same configurations as each other with the exception of the fact that the arrangement pitch (interval) LP or the opening density of the cooling passages 50 changes in the opposite direction as the axial upstream side or the downstream side is approached. That is, the arrangement pitch (interval) LP of the cooling passages 50 of the first end portion cooling passages 54 becomes larger, or the opening density becomes smaller, as the axial downstream side is approached. On the other hand, the arrangement pitch (interval) LP of the cooling passages 50 of the second end portion cooling passages 56 becomes smaller, or the opening density becomes larger, as the axial downstream side is approached. Note that the proportion of the change in the inclination angle a of the cooling passages 50 of the first end portion cooling passages 54 and the second end portion cooling passages 56 from the first end surface 42c or the second end surface 42d toward the circumferential direction of the intermediate portion 43 is substantially the same.

[0087] From another perspective, in Figure 5 , it can be seen that the configuration of the first end portion cooling passages 54 and the configuration of the second end portion cooling passages 56 are in a substantially symmetrical positional relationship centered on the midpoint (middle point) SO of the circumferential direction and the axial direction of the first main body portion 42. That is, in a case where an arbitrary position on the axial upstream side from the axial downstream end 42f of the nth cooling passage 54n of the first end portion cooling passages 54 to the first end surface 42c is set as a point SI, and an arbitrary position on the axial downstream side from the axial upstream end 42e of the same nth cooling passage 56n of the second end portion cooling passages 56 to the second end surface 42d is set as a point S2, if the length from the axial downstream end 42f to the point SI and the length from the axial upstream end 42e to the point S2 are made the same length, it can be seen that the positional relationship of the point SI and the point S2 is in a substantially symmetrical positional relationship centered on the midpoint SO. Therefore, if the number of the configurations of the cooling passages 50 of the first end portion cooling passages 54 and the second end portion cooling passages 56 is the same, and the inclination angle a or the arrangement pitch (interval) LP or the opening density of the nth cooling passage 54n, 56n from the first end surface 42c and the second end surface 42d is the same, the cooling area of each heated region 63 of each cooling passage 50 in the first end portion cooling passages 54 and the second end portion cooling passages 56 becomes substantially the same area. In addition, the configuration density of the cooling passages 50 in the first end portion cooling passages 54 and the second end portion cooling passages 56 is substantially the same, and the cooling capacity is also substantially the same.

[0088] On the other hand, in a case where the arrangement pitch LP of the cooling passages 50 in the circumferential direction at the axial upstream end 42e of the first end portion cooling passage 54 is smaller than the arrangement pitch (interval) LP of the cooling passages 50 in the circumferential direction at the axial upstream end 42e of the intermediate portion cooling passage 52, or the opening density of the cooling passages 50 in the circumferential direction at the axial upstream end 42e of the first end portion cooling passage 54 is larger than the opening density of the cooling passages 50 in the circumferential direction at the axial upstream end 42e of the intermediate portion cooling passage 52, the arrangement density of the cooling passages 50 of the first end portion cooling passage 54 is larger than the arrangement density of the cooling passages 50 of the second end portion cooling passage 56. Also, in a case where the arrangement pitch (interval) LP or the opening density of the cooling passages 50 in the circumferential direction of the nth cooling passage 54n from the first end surface 42c of the first end portion cooling passage 54 and the nth cooling passage 56n from the second end surface 42d of the second end portion cooling passage 56 is compared, the arrangement pitch (interval) LP in the circumferential direction of the cooling passages 50 of the first end portion cooling passage 54 is smaller, and the opening density in the circumferential direction of the cooling passages 50 is larger, as compared with the cooling passages 50 of the second end portion cooling passage 56. That is, the arrangement density of the cooling passages 50 in the first main body portion 42 is larger, and the cooling capacity is larger, in the first end portion cooling passage 54 as compared with the second end portion cooling passage 56. Also, further, if the inclination angle a of the nth cooling passage 56n from the second end surface 42d of the second end portion cooling passage 56 is made larger than the inclination angle a of the nth cooling passage 54n from the first end surface 42c of the first end portion cooling passage 54, the arrangement density of the cooling passages 50 of the first end portion cooling passage 54 is further larger than the arrangement density of the cooling passages 50 of the second end portion cooling passage 56. In this way, the arrangement of the first end portion cooling passage 54 and the second end portion cooling passage 56 is selected to be a symmetrical arrangement with the midpoint SO of the first main body portion 42 as the center, and at the same time, the arrangement pitch LP or the opening density or the inclination angle a with respect to the circumferential direction of the cooling passages 50 is sometimes selected to be a different arrangement as appropriate. The reason for this is as described below.

[0089] The cooling passages 50 of the first end portion cooling passages 54 and the second end portion cooling passages 56 are heated by heat input from the combustion gas G as they go toward the axial downstream side. In addition, the circumferential arrangement pitch LP of the cooling passages 50 of the first end portion cooling passages 54 becomes larger and the opening density becomes smaller as they go toward the axial downstream side. On the other hand, the circumferential arrangement pitch LP of the cooling passages 50 of the second end portion cooling passages 56 becomes smaller and the opening density becomes larger as they go toward the axial downstream side. That is, the first end portion cooling passages 54 have a higher degree of heating than the second end portion cooling passages 56, and the metal temperature at the axial downstream end 42f becomes higher. In order to correct this, the configuration of the cooling passages 50 of the first end portion cooling passages 54 is such that the circumferential arrangement pitch LP of the cooling passages 50 is reduced, or the opening density is increased, or the inclination angle a is reduced, as they go toward the axial downstream side, compared to the configuration of the cooling passages 50 of the second end portion cooling passages 56, thereby increasing the cooling capacity of the first end portion cooling passages 54. However, in comparison between the first end portion cooling passages 54 and the intermediate portion cooling passages 52, the circumferential arrangement pitch LP of the cooling passages 50 at the axial intermediate position of the first end portion cooling passages 54 is larger and the opening density is smaller than the circumferential arrangement pitch LP of the cooling passages 50 at the same axial intermediate position of the intermediate portion cooling passages 52. In addition, the inclination angle a of the cooling passages 50 of the first end portion cooling passages 54 is smaller than that of the intermediate portion cooling passages 52. Therefore, the intermediate portion cooling passages 52 have a larger cooling capacity than the first end portion cooling passages 54 and the second end portion cooling passages 56 in terms of the cooling capacity of the cooling passages 50.

[0090] The above description is for the inner side sealing member 40a, but the same structure and the configuration of the cooling passages 50 can be applied to the outer side sealing member 40b. However, in the case of the outer side sealing member 40b, "radial outer side" in the above description of the inner side sealing member 40a is replaced with "radial inner side", and "radial inner side" is replaced with "radial outer side".

[0091] Characteristics of the Cooling Passages

[0092] The following describes the characteristics of the configuration of the cooling passages 50 of the sealing member 40 described above.

[0093] The first feature point is that all of the cooling passages 50 except for the cooling passages 54a and 56a disposed adjacent to the first end surface 42c and the second end surface 42d on both sides of the circumferential direction of the first body portion 42 are constituted by inclined passages having an inclination angle a with respect to the axial direction. Also, the cooling passages 50 disposed in the first body portion 42 have a configuration in which the cooling passages 50 disposed in the intermediate portion 43 in the circumferential direction of the first body portion 42 and the cooling passages 50 of the first end portion 44 on the first end surface 42c side and the second end portion 45 on the second end surface 42d side sandwiching the intermediate portion 43 are different.

[0094] That is, all of the cooling passages 50 disposed in the intermediate portion 43 have a larger inclination angle a than the cooling passages 50 disposed in the first end portion 44 and the second end portion 45, and the passage length from the upstream end 42e in the axial direction to the downstream end 42f in the axial direction is the longest, and the cooling passages 50 are longer than the first end portion cooling passages 54 and the second end portion cooling passages 56. Also, all of the cooling passages 50 of the intermediate portion cooling passages 52 are parallel to each other, and have a cooling structure in which the arrangement pitch (interval) LP in the circumferential direction is the smallest and the opening density of the cooling passages 50 is the largest, compared to the first end portion cooling passages 54 and the second end portion cooling passages 56.

[0095] The second feature point is that the configurations of the cooling passages 50 of the first end portion cooling passages 54 and the second end portion cooling passages 56 are different. As described above, the first end portion cooling passages 54 have a configuration in which the inclination angle a with respect to the axial direction of the cooling passages 50 increases, and the arrangement pitch (interval) LP in the circumferential direction of the cooling passages 50 at the axial intermediate position increases and the opening density decreases, as the first end surface 42c side is approached toward the second end surface 42d side on the opposite side of the circumferential direction. In this way, by selecting a configuration in which the inclination angle a of the cooling passages 50 increases as the first end surface 42c is distanced, the cooling capacity of the cooling passages 50 is increased, the heated region 61 is increased, and the metal temperature of the first end portion 44 at the downstream end 42f in the axial direction of the cooling passages 50 of the first end portion cooling passages 54 is maintained at an appropriate temperature that is below the allowable value, and thermal damage due to heat input from the combustion gas G can be suppressed.

[0096] On the other hand, the second end portion cooling passage 56 has a configuration in which, as it goes from the second end surface 42d side toward the first end surface 42c side in the opposite direction in the circumferential direction, the inclination angle a with respect to the axial direction of the cooling passage 50 increases, the arrangement pitch (interval) LP in the circumferential direction of the cooling passage 50 increases, and the opening density decreases. However, the arrangement pitch (interval) LP or the opening density in the axial direction of the cooling passage 50 changes in the opposite direction from the first end portion cooling passage 54. That is, the second end portion cooling passage 56 has a configuration in which, as it goes toward the downstream side in the axial direction of the cooling passage 50, the arrangement pitch (interval) LP in the circumferential direction decreases, and the opening density increases, and at the axial direction downstream end 42f, the arrangement pitch (interval) LP and the opening density of the cooling passage 50 are the same as those of the intermediate portion cooling passage 52. By selecting such a configuration, as with the first end portion 44, the metal temperature of the first end portion 44 at the axial direction downstream end 42f of the cooling passage 50 of the second end portion cooling passage 56 is maintained at an appropriate temperature that is below the allowable value, while heat damage due to heat input from the combustion gas G is suppressed.

[0097] Further, the first end portion cooling passage 54 and the second end portion cooling passage 56 each have a smaller passage surface area per unit area of the first body portion 42 (the plate member 60) than the intermediate portion cooling passage 52.

[0098] However, the first end portion cooling passage 54 and the second end portion cooling passage 56 have a smaller heat load from the combustion gas G than the intermediate portion cooling passage 52, and thus the allowable metal temperature can be set to be higher, and thus the cooling air amount can be reduced while maintaining the metal temperature of the first body portion 42 at the axial direction downstream end 42f to be within the allowable value. Next, a modification of the configuration of the cooling passage 50 of the seal member 40 provided to the first body portion 42 will be described.

[0099] <Modification Example>

[0100] Figure 8 is a configuration diagram of a cooling passage of a modification example of a seal member, Figure 9 is a Z-Z cross section of Figure 8 Figure 10 is a configuration diagram of a modification example of a seal member in combination with a turbine vane. As shown in Figure 8 and Figure 9 , the cooling passage 50 of the seal member 40 of the present modification example differs from the embodiment in the configuration of the intermediate portion cooling passage 52. The other structures are the same as in the embodiment, including the configurations of the first end portion cooling passage 54 and the second end portion cooling passage 56.

[0101] As shown in Figure 8 and Figure 9 ​As shown, the intermediate cooling passage 52 in this modified example is composed of a first intermediate cooling passage 53a opening at the axial downstream end 42f of the first main body 42, and a second intermediate cooling passage 53b opening at the inner surface 42i of the radially inner side of the first main body 42. Figure 9 As shown, when viewing the intermediate cooling passage 52 of this modified example from the radial outside, the first intermediate cooling passage 53a and the second intermediate cooling passage 53b are arranged alternately in the circumferential direction and are arranged parallel to each other. However, the first intermediate cooling passage 53a and the second intermediate cooling passage 53b are the same as the cooling passage 50 of the intermediate cooling passage 52 in this embodiment in terms of the circumferential spacing (interval) LP, the axial tilt angle α, and the opening density.

[0102] The first intermediate cooling passage 53a, like the cooling passage 50 of the intermediate cooling passage 52 in the embodiment, is an inclined flow path with an inclination angle α relative to the axial direction, and opens at the axial downstream end 42f of the first main body 42. On the other hand, the second intermediate cooling passage 53b is an inclined flow path with an inclination angle α relative to the axial direction and also inclined in the radial direction, and opens at the opening 53c formed on the inner surface 42i of the first main body 42.

[0103] like Figure 10 As shown, the sealing member 40 in this modified example is similar to the sealing member 40 shown in the embodiment, with a recess 50 in the first main body 42 recessed from the axial downstream end 42f toward the axial upward flow side between the first main body 42 and the third main body 47. The turbine stator 24, arranged adjacent to it on the axial downstream side, has a protrusion 25a protruding from the leading edge 24a side of the shroud 25 toward the axial upward flow side. The protrusion 25a of the shroud 25 is inserted into the recess 50 of the sealing member 40 from the axial downstream side, thereby fitting the sealing member 40 with the turbine stator 24. A predetermined gap is provided between the sealing member 40 and the turbine stator 24 in the axial direction to absorb the axial thermal expansion difference between the sealing member 40 and the turbine stator 40 generated during the operation of the gas turbine 1. On the other hand, a fixed seal 49 is provided between the third main body 47 and the protrusion 25a to seal the gap 70 between the sealing member 40 and the turbine stator 24 and the space 21 of the housing 20, so that the cooling air (compressed air A) in the space 21 of the housing 20 does not flow out from the gap 70 between the sealing member 40 and the turbine stator 24 into the combustion gas G.

[0104] However, in some cases, a portion of the high-temperature combustion gas G is drawn into the gap portion 70 between the first main body portion 42 of the seal member 40 and the protruding portion 25a of the turbine vane 24 due to a pressure fluctuation of the combustion gas G flowing in the combustion gas flow passage 37, and the first main body portion 42 of the seal member 40 and the protruding portion 25a are thermally damaged. According to the intermediate portion cooling passage 52 of the seal member 40 according to the above-described modification example, the first intermediate portion cooling passage 53a constituting the intermediate portion cooling passage 52 discharges cooling air from the opening 42b of the axially downstream end 42f of the first main body portion 42, and thus it is possible to cool the gas passage surface on the outer surface 42a side of the first main body portion 42. On the other hand, the second intermediate portion cooling passage 53b discharges cooling air from the opening 53c formed on the radially inner side of the first main body portion 42 toward the gap portion 70, and thus the combustion gas G drawn into the gap portion 70 is blown toward the combustion gas flow passage 37 side, the atmospheric gas temperature in the gap portion 70 is reduced, and it is possible to cool the inner surface 42i of the first main body portion 42. Therefore, according to the intermediate portion cooling passage 52 according to the present modification example, it is possible to uniformly cool the gas passage surface and the inner surface 42i of the first main body portion 42, and thermal damage of the seal member 40 and the protruding portion 25a of the turbine vane 24 is suppressed.

[0105] The size, material, shape, relative arrangement, and the like of the constituent members shown in the above-described embodiments and modifications or the drawings are not intended to limit the scope of the application thereto, but are merely illustrative. For example, expressions indicating relative or absolute arrangement such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric", or "coaxial" indicate not only such arrangement in a strict sense, but also a state in which there is a relative displacement in an angle or a distance to the extent that the same function is obtained with a tolerance. For example, expressions indicating a state in which things are equal such as "same", "equal", and "uniform" indicate not only a state in which they are strictly equal, but also a state in which there is a difference to the extent that the same function is obtained with a tolerance.

[0106] For example, expressions indicating shapes such as a quadrangular shape and a cylindrical shape indicate not only a shape in a strict sense of geometry, but also a shape including a concave-convex portion, a chamfered portion, and the like to the extent that the same effect is obtained. On the other hand, expressions such as "provided with", "containing", "equipped with", "including", or "having" a constituent element are not exclusive expressions that exclude the presence of other constituent elements.

[0107] The above-described embodiments and modifications are understood as follows.

[0108] (1) The sealing member of the first embodiment forms a combustion gas flow path for a gas turbine. The sealing member includes a first main body extending axially and circumferentially and having a cooling passage inside. The first main body is composed of a first end forming one end in the circumferential direction, a second end forming the other end on the opposite side of the circumferential direction, and an intermediate portion formed between the first end and the second end. The cooling passage includes: an intermediate cooling passage disposed in the intermediate portion, inclined at a first angle relative to the axial direction, extending along the axial direction, and having a plurality of such passages in the circumferential direction; a first end cooling passage disposed in the first end, inclined at a second angle relative to the axial direction, extending along the axial direction, and having a plurality of such passages in the circumferential direction; and a second end cooling passage disposed in the second end, inclined at a third angle relative to the axial direction, extending along the axial direction, and having a plurality of such passages in the circumferential direction. Both the second angle and the third angle are smaller than the first angle.

[0109] According to the sealing member described in (1) above, compared with the first angle of the intermediate cooling passage, the second angle of the first end cooling passage and the third angle of the second end cooling passage are formed to be smaller. Therefore, the cooling area of ​​the intermediate cooling passage in the high temperature region becomes larger, and the metal temperature of the intermediate part of the first main body can be suppressed to below the allowable value.

[0110] (2) The sealing member of the second embodiment forms a combustion gas flow path for a gas turbine. The sealing member includes a first main body extending axially and circumferentially and having a cooling passage inside. The first main body is composed of a first end forming one end in the circumferential direction, a second end forming the opposite end in the circumferential direction, and an intermediate portion formed between the first end and the second end. The cooling passage includes: an intermediate cooling passage disposed in the intermediate portion, extending with a certain inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction; a first end cooling passage disposed in the first end, extending with a predetermined inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction; and a second end cooling passage disposed in the second end, extending with a predetermined inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction. The opening density of the cooling passage at the axial upstream end of either the first end cooling passage or the second end cooling passage is smaller than the opening density of the cooling passage at the axial downstream end.

[0111] According to the sealing member described in (2) above, the opening density of the cooling passage of one of the first end cooling passage and the second end cooling passage is set to be larger at the upstream end than at the downstream end. This results in a larger cooling area in the middle of the high-temperature region, thereby suppressing the metal temperature in the middle. Furthermore, the opening density of the upstream side of the first or second end, which has a higher allowable metal temperature, is reduced compared to the downstream side to decrease the cooling area and thus reduce the cooling air volume. Therefore, it is possible to suppress the metal temperature of the first body portion within an allowable value while maintaining a low cooling air volume.

[0112] (3) The sealing member of the third embodiment forms a combustion gas flow path for a gas turbine. The sealing member includes a first main body extending axially and circumferentially and having a cooling passage inside. The first main body is composed of a first end forming one end in the circumferential direction, a second end forming the opposite end in the circumferential direction, and an intermediate portion formed between the first end and the second end. The cooling passage includes: an intermediate cooling passage disposed in the intermediate portion, extending with a certain inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction; a first end cooling passage disposed in the first end, extending with a predetermined inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction; and a second end cooling passage disposed in the second end, extending with a predetermined inclination relative to the axial direction, and having a plurality of such passages in the circumferential direction. The spacing between the cooling passages at the axial upstream end of either the first end cooling passage or the second end cooling passage is greater than the spacing between the cooling passages at the axial downstream end.

[0113] According to the sealing member described in (3) above, the arrangement spacing of either the first end cooling passage or the second end cooling passage is set to be larger at the upstream end than at the downstream end, thereby obtaining a larger cooling area in the middle part of the high temperature region to suppress the metal temperature in the middle part, and reducing the arrangement spacing of the upstream side of the first end or the second end with a higher allowable metal temperature compared to the downstream side to reduce the cooling area, thereby reducing the amount of cooling air.

[0114] Therefore, it is possible to keep the metal temperature of the first main body within an acceptable range while using a low amount of cooling air.

[0115] (4) The sealing member of the fourth scheme is based on the sealing member of (1), and the angle of at least one of the second angle of the first end cooling passage and the third angle of the second end cooling passage increases as it moves away from the adjacent end face of the first body part in the circumferential direction.

[0116] According to the seal member described in the above (4), the angle of the cooling passage of one of the second angle of the first end portion cooling passage and the third angle of the second end portion cooling passage is made larger as it is farther from the end surface of the first main body portion, so the cooling area of the cooling passage of the end portion becomes smaller, and the cooling air amount is reduced.

[0117] (5) The seal member of the fifth aspect is based on the seal member of (4), and the second angle of the first end portion cooling passage is made larger as it is farther in the circumferential direction from the first end surface of the first main body portion, and the third angle of the second end portion cooling passage is made larger as it is farther in the circumferential direction from the second end surface of the first main body portion.

[0118] According to the seal member described in the above (5), the second angle of the first end portion cooling passage and the third angle of the second end portion cooling passage are made larger as they are farther from the end surface of the first main body portion, so the cooling area of the cooling passage of the first end portion and the second end portion becomes smaller, and the cooling air amount is further reduced.

[0119] (6) The seal member of the sixth aspect is based on the seal member of (2), and the cooling passage of at least one of the first end portion cooling passage and the second end portion cooling passage is made larger in opening density as it is toward the axial downstream side.

[0120] According to the seal member described in the above (6), the end portion cooling passage of at least one of the first end portion or the second end portion, which is allowed to have a higher metal temperature than the intermediate portion, can be made larger in opening density as it is toward the axial downstream side, so the metal temperature at the axial downstream end of the end portion can be restrained within the allowable value. In addition, the opening density in the axial direction of the cooling passage is changed, so the cooling area becomes smaller compared to the intermediate portion, and the cooling air amount can be reduced.

[0121] (7) The seal member of the seventh aspect is based on the seal member of (2) or (6), and the first end portion cooling passage is made smaller in opening density as it is toward the axial downstream side, and the second end portion cooling passage is made larger in opening density as it is toward the axial downstream side.

[0122] According to the seal member described in the above (7), the first end portion and the second end portion can be allowed to have a higher metal temperature than the intermediate portion. In addition, the first end portion cooling passage and the second end portion cooling passage are changed in opening density as they are toward the axial downstream side, so the cooling area becomes smaller compared to the intermediate portion, and the cooling air amount can be reduced. Furthermore, the second end portion cooling passage is made larger in opening density as it is toward the axial downstream side, so the metal temperature at the axial downstream end of the second end portion can be restrained within the allowable value.

[0123] (8) The seal member of the eighth aspect, wherein the density of openings of the cooling passage at the axial middle position of at least one of the first end portion cooling passage and the second end portion cooling passage decreases as it is farther away in the circumferential direction from the adjacent end surface of the first main body portion.

[0124] According to the seal member described in the above (8), the density of openings of the cooling passage at the axial middle position of at least one of the first end portion cooling passage and the second end portion cooling passage decreases as it is farther away from the adjacent end surface of the first main body portion, so the amount of cooling air decreases.

[0125] (9) The seal member of the ninth aspect, wherein the density of openings of the cooling passage at the axial middle position of the first end portion cooling passage decreases as it is farther away in the circumferential direction from the adjacent first end surface of the first main body portion, and the density of openings of the cooling passage at the axial middle position of the second end portion cooling passage decreases as it is farther away in the circumferential direction from the adjacent second end surface of the first main body portion.

[0126] According to the seal member described in the above (9), the density of openings of the cooling passage at the axial middle position of the first end portion cooling passage and the second end portion cooling passage decreases as it is farther away from the adjacent first end surface and the second end surface of the first main body portion, so the amount of cooling air further decreases.

[0127] (10) The seal member of the tenth aspect, wherein the density of openings in the circumferential direction at the axial middle position of the middle portion cooling passage is greater than the density of openings in the circumferential direction at the same axial middle position of the first end portion cooling passage, and the density of openings in the circumferential direction at the same axial middle position of the first end portion cooling passage is greater than the density of openings in the circumferential direction at the same axial middle position of the second end portion cooling passage, based on the seal member of any one of (2) to (9).

[0128] According to the seal member described in the above (10), the density of openings of the middle portion cooling passage is made greater than the density of openings of the first end portion cooling passage, and the density of openings of the first end portion cooling passage is made greater than the density of openings of the second end portion cooling passage, so the cooling capacity of the first end portion cooling passage and the second end portion cooling passage is reduced as compared with the middle portion, which has the greatest cooling capacity. Therefore, the amount of cooling air decreases as a whole of the seal member. Further, the density of openings of the first end portion cooling passage is made greater than the density of openings of the second end portion cooling passage, so the metal temperature of the first end portion is suppressed within an allowable value.

[0129] (11) The seal member of the eleventh aspect, wherein the arrangement pitch of the cooling passage at the axial middle position of at least one of the first end portion cooling passage and the second end portion cooling passage increases as it is farther away in the circumferential direction from the adjacent end surface of the first main body portion, based on the seal member of (3).

[0130] According to the seal member described in the above (11), the arrangement pitch of the cooling passage at the axial middle position of at least one of the first end portion cooling passage and the second end portion cooling passage decreases as it is farther from the end surface of the first main body portion, and thus the cooling area increases and the cooling air amount decreases.

[0131] (12) The seal member of the 12th aspect is based on the seal member of (3) or (11), and for the first end portion cooling passage, the arrangement pitch of the cooling passage increases from the upstream side in the axial direction toward the downstream side, and for the second end portion cooling passage, the arrangement pitch of the cooling passage decreases from the upstream side in the axial direction toward the downstream side.

[0132] According to the seal member described in the above (12), the first end portion cooling passage increases the arrangement pitch as it goes toward the downstream side in the axial direction, and the second end portion cooling passage decreases the arrangement pitch as it goes toward the downstream side in the axial direction, and thus the metal temperature at the downstream end in the axial direction is suppressed to be below the allowable value, and a decrease in the cooling air amount can be achieved.

[0133] (13) The seal member of the 13th aspect is based on the seal member of (3) or (11) or (12), and the arrangement pitch of the cooling passage at the axial middle position of the middle portion cooling passage is smaller than the arrangement pitch at the same axial middle position of the first end portion cooling passage and the second end portion cooling passage.

[0134] According to the seal member described in the above (13), the arrangement pitch of the middle portion cooling passage is made smaller than that of the other regions, and the cooling area is increased, and thus heat damage at the downstream end in the axial direction of the middle portion can be prevented.

[0135] (14) The seal member of the 14th aspect is based on the seal member of (3) or (11) to (13), and for the middle portion cooling passage, the arrangement pitch of the cooling passage at the upstream end in the axial direction is the same as the arrangement pitch at the downstream end in the axial direction, for the first end portion cooling passage, the arrangement pitch of the cooling passage at the upstream end in the axial direction is made smaller than the arrangement pitch at the upstream end in the axial direction of the middle portion cooling passage, and the arrangement pitch at the downstream end in the axial direction is made larger than the arrangement pitch at the downstream end in the axial direction of the middle portion cooling passage, and for the second end portion cooling passage, the arrangement pitch of the cooling passage at the upstream end in the axial direction is made larger than the arrangement pitch at the upstream end in the axial direction of the middle portion cooling passage, and the arrangement pitch at the downstream end in the axial direction is the same as the arrangement pitch at the downstream end in the axial direction of the middle portion cooling passage.

[0136] According to the seal member described in the above (14), the metal temperature at the downstream end in the axial direction of the first main body portion is suppressed to be within the allowable value, and the cooling air amount of the entire seal member is decreased.

[0137] (15) The seal member of the 15th aspect, wherein the circumferential width of the axial upstream end of the intermediate portion in which the intermediate portion cooling passage is formed is the same as the circumferential width of the axial downstream end, the circumferential width of the axial upstream end of the first end portion in which the first end portion cooling passage is formed is larger than the circumferential width of the axial downstream end, and the circumferential width of the axial upstream end of the second end portion in which the second end portion cooling passage is formed is smaller than the circumferential width of the axial downstream end.

[0138] According to the seal member described in the above (15), the first end portion in which the first end portion cooling passage is formed and the second end portion in which the second end portion cooling passage is formed have a smaller passage surface area per unit area of the cooling passage and a smaller cooling area than the intermediate portion in which the intermediate portion cooling passage is formed. Therefore, the amount of cooling air at the first end portion and the second end portion is reduced compared to the intermediate portion, and the amount of cooling air is reduced for the entire seal member.

[0139] (16) The seal member of the 16th aspect, wherein the circumferential width of the axial upstream end between the end surfaces on both sides of the circumferential direction of the first main portion is at least the same as or larger than the circumferential width of the first main portion at the axial downstream end.

[0140] (17) The seal member of the 17th aspect, wherein the intermediate portion cooling passage includes a plurality of cooling passages that are inclined toward the inner side in the radial direction as they go toward the axial downstream side and that open onto the inner surface on the radially inner side of the first main portion.

[0141] According to the seal member described in the above (17), the combustion gas that has entered the recess is immediately purged toward the combustion gas flow path by the cooling air that is discharged from the cooling passage, and thus heat damage to the seal member is suppressed.

[0142] (18) The seal member of the 18th aspect, wherein the intermediate portion cooling passage is composed of a first intermediate portion cooling passage that opens onto the axial downstream end of the first main portion and a second intermediate portion cooling passage that opens onto the inner surface on the radially inner side of the first main portion, and the first intermediate portion cooling passage and the second intermediate portion cooling passage are alternately arranged in the circumferential direction of the first main portion.

[0143] According to the seal member described in the above (18), the first intermediate portion cooling passage and the second intermediate portion cooling passage that constitute the cooling passage are alternately arranged in the circumferential direction, and thus the intermediate portion of the first main portion, which has a large heat load, is uniformly cooled.

[0144] (19) The seal member of the 19th aspect, on the basis of the seal members of (1) to (18), is configured to seal between a tail pipe that discharges combustion gas and a stator vane that is configured on the downstream side in the axial direction of the tail pipe, the seal member having: a first body portion; and a second body portion that is connected to the upstream end in the axial direction of the first body portion, extends in a direction away from the radial direction of the first body portion, and engages with the tail pipe, the second body portion including a supply passage that extends in the radial direction inside, a plurality of the supply passages being arranged in the circumferential direction, one end of the supply passage communicating with the cooling passage, and the other end of the supply passage communicating with a space surrounded by the casing via an opening formed in the other end that is a terminal end of the second body portion.

[0145] (20) The gas turbine of the 20th aspect has: the seal member of (1) to (19); a combustor that is connected to the upstream side in the axial direction of the seal member; and a turbine that is driven by combustion gas generated by the combustor.

[0146] Explanation of Reference Signs:

[0147] 1... gas turbine;

[0148] 2... compressor;

[0149] 4... combustor;

[0150] 6... turbine;

[0151] 8... rotor;

[0152] 10... compressor chamber;

[0153] 12... intake chamber;

[0154] 14... inlet guide vane;

[0155] 16... compressor stator vane;

[0156] 18... compressor rotor vane;

[0157] 20... casing;

[0158] 21... space;

[0159] 22... turbine chamber;

[0160] 24... turbine stator vane;

[0161] 25... shroud;

[0162] 25a... protruding portion;

[0163] 26... turbine rotor vane;

[0164] 28... exhaust chamber;

[0165] 29 exhaust chamber

[0166] 30 combustion nozzle

[0167] 32 combustion cylinder

[0168] 33 inner cylinder

[0169] 34 tail cylinder

[0170] 35 flange

[0171] 37 combustion gas flow path

[0172] 40 seal member

[0173] 40a inner side seal member

[0174] 40b outer side seal member

[0175] 42 first body portion

[0176] 42a outer surface

[0177] 42b opening

[0178] 42c first end surface

[0179] 42d second end surface

[0180] 42e axially upstream end

[0181] 42f axially downstream end

[0182] 42h connection point

[0183] 42i inner surface

[0184] 43 intermediate portion

[0185] 44 first end portion

[0186] 45 second end portion

[0187] 46 second body portion

[0188] 46a end portion

[0189] 46b opening

[0190] 47 third body portion

[0191] 48 fitting portion

[0192] 49... stationary seal;

[0193] 50, 52a, 52b, 53a, 53b, 54a, 54n, 56a, 56n... cooling passage;

[0194] 50a... central axis;

[0195] 52... intermediate portion cooling passage;

[0196] 53a... first intermediate portion cooling passage;

[0197] 53b... second intermediate portion cooling passage;

[0198] 53c... opening;

[0199] 54... first end portion cooling passage;

[0200] 56... second end portion cooling passage;

[0201] 58... supply passage;

[0202] 60... plate;

[0203] 60a... axially upstream end;

[0204] 60b... axially downstream end;

[0205] 61, 63... heated region;

[0206] 62... heated increased region;

[0207] 62a... first increased region;

[0208] 62b... second increased region;

[0209] L1, L2... passage length;

[0210] DL... difference;

[0211] a, a0... inclination angle;

[0212] a1... inclination angle (first angle);

[0213] a2... inclination angle (second angle);

[0214] a3... inclination angle (third angle);

[0215] LP, LP0, LP1... arrangement pitch.

Claims

1. A sealing member that forms a combustion gas flow path in a gas turbine, wherein, The sealing member includes a first main body extending axially and circumferentially and having internal cooling passages. The first main body portion is composed of a first end portion forming one end portion in the circumferential direction, a second end portion forming the other end portion in the opposite direction in the circumferential direction, and an intermediate portion formed between the first end portion and the second end portion. The cooling path includes: A central cooling passage is disposed in the central portion, inclined at a first angle relative to the axial direction, extends along the axial direction, and is provided in multiple ways in the circumferential direction; A first end cooling passage, disposed at the first end, inclined at a second angle relative to the axial direction, extending along the axial direction, and having a plurality of such passages arranged in the circumferential direction; and A second end cooling passage, disposed at the second end, inclined at a third angle relative to the axial direction, extending along the axial direction, and having a plurality of such passages arranged in the circumferential direction. Both the second angle and the third angle are smaller than the first angle.

2. The sealing member according to claim 1, wherein, The angle of at least one of the second angle of the first end cooling passage and the third angle of the second end cooling passage increases as it moves away from the adjacent end face of the first body portion in the circumferential direction.

3. A sealing member that forms a combustion gas flow path in a gas turbine, wherein, The sealing member includes a first main body extending axially and circumferentially and having internal cooling passages. The first main body portion is composed of a first end portion forming one end portion in the circumferential direction, a second end portion forming the other end portion in the opposite direction in the circumferential direction, and an intermediate portion formed between the first end portion and the second end portion. The cooling path includes: A central cooling passage is disposed in the central portion and extends at a certain angle relative to the axial direction, and multiple such passages are arranged in the circumferential direction. A first end cooling passage, disposed at the first end, extending at a predetermined angle relative to the axial direction, and having a plurality of such passages arranged in the circumferential direction; and A second end cooling passage, disposed at the second end, extends at a predetermined angle relative to the axial direction, and is provided in plurality of such passages in the circumferential direction. The opening density of the cooling passage at the axial upstream end of either the first end cooling passage or the second end cooling passage is smaller than the opening density of the cooling passage at the axial downstream end.

4. The sealing member according to claim 3, wherein, The opening density of at least one of the first end cooling passage and the second end cooling passage increases as it moves toward the axial downstream side.

5. The sealing member according to claim 3 or 4, wherein, The opening density of the first end cooling passage decreases as it moves towards the axial downstream side. The opening density of the second end cooling passage increases as it moves toward the axial downstream side.

6. The sealing member according to claim 3 or 4, wherein, The opening density at the axial midpoint of the cooling passage of at least one of the first end cooling passage and the second end cooling passage decreases as it moves circumferentially away from the adjacent end face of the first body portion.

7. The sealing member according to claim 3 or 4, wherein, The circumferential opening density at the axial midpoint of the intermediate cooling passage is greater than the circumferential opening density at the same axial midpoint of the first end cooling passage. The circumferential opening density at the same axial midpoint of the first end cooling passage is greater than the circumferential opening density at the same axial midpoint of the second end cooling passage.

8. A sealing member that forms a combustion gas flow path for a gas turbine, wherein, The sealing member includes a first main body extending axially and circumferentially and having internal cooling passages. The first main body portion is composed of a first end portion forming one end portion in the circumferential direction, a second end portion forming the other end portion in the opposite direction in the circumferential direction, and an intermediate portion formed between the first end portion and the second end portion. The cooling path includes: A central cooling passage is disposed in the central portion and extends at a certain angle relative to the axial direction, and multiple such passages are arranged in the circumferential direction. A first end cooling passage, disposed at the first end, extending at a predetermined angle relative to the axial direction, and having a plurality of such passages arranged in the circumferential direction; and A second end cooling passage, disposed at the second end, extends at a predetermined angle relative to the axial direction, and is provided in plurality of such passages in the circumferential direction. The spacing between the cooling passages at the upstream end of either the first end cooling passage or the second end cooling passage is greater than the spacing between the cooling passages at the downstream end.

9. The sealing member according to claim 8, wherein, The spacing between the cooling passages at the axial midpoint of at least one of the first and second end cooling passages increases as it moves circumferentially away from the adjacent end face of the first body portion.

10. The sealing member according to claim 8 or 9, wherein, For the first end cooling passage, the spacing between the cooling passages increases from the axial upward flow side towards the axial downstream side. For the second end cooling passage, the spacing of the cooling passages decreases from the axial upward flow side toward the axial downstream side.

11. The sealing member according to claim 8 or 9, wherein, The spacing between the cooling passages at the axial midpoint of the intermediate cooling passage is smaller than the spacing between the cooling passages at the same axial midpoint of the first and second end cooling passages.

12. The sealing member according to claim 8 or 9, wherein, For the intermediate cooling passage, the arrangement spacing at the upstream end of the cooling passage is the same as the arrangement spacing at the downstream end of the cooling passage. For the first end cooling passage, the arrangement spacing at the axial upstream end of the cooling passage is smaller than the arrangement spacing at the axial upstream end of the middle cooling passage, and the arrangement spacing at the axial downstream end is larger than the arrangement spacing at the axial downstream end of the middle cooling passage. For the second end cooling passage, the arrangement spacing at the axial upstream end of the cooling passage is larger than the arrangement spacing at the axial upstream end of the middle cooling passage, and the arrangement spacing at the axial downstream end is the same as the arrangement spacing at the axial downstream end of the middle cooling passage.

13. The sealing member according to any one of claims 1, 3, and 8, wherein, The circumferential width of the upstream end of the intermediate portion where the intermediate cooling passage is formed is the same as the circumferential width of the downstream end. The circumferential width of the upstream end of the first end having the first end cooling passage is smaller than the circumferential width of the downstream end. The circumferential width of the upstream end of the second end of the second end where the second end cooling passage is formed is larger than the circumferential width of the downstream end.

14. The sealing member according to any one of claims 1, 3, and 8, wherein, The circumferential width at the upstream end between the two circumferential end faces of the first main body is at least the same as or greater than the circumferential width of the first main body at the downstream end.

15. The sealing member according to any one of claims 1, 3, and 8, wherein, The intermediate cooling passage includes a plurality of cooling passages that are inclined radially inward toward the axial downstream side and open on the inner surface of the radially inner side of the first main body.

16. The sealing member according to claim 15, wherein, The intermediate cooling passage is composed of a first intermediate cooling passage that opens at the axial downstream end of the first main body and a second intermediate cooling passage that opens on the inner surface of the radially inner side of the first main body. The first intermediate cooling passage and the second intermediate cooling passage are alternately arranged in the circumferential direction of the first main body.

17. The sealing member according to any one of claims 1, 3, and 8, wherein, The sealing member is disposed between the tailstock that discharges combustion gases and a stationary vane disposed on the axial downstream side of the tailstock, thereby sealing the area between the tailstock and the stationary vane. The sealing member comprises: The first main body section; as well as The second main body is connected to the axial upstream end of the first main body, extends in a direction away from the outer surface of the first main body, and its outer end engages with the tail cylinder. The second main body includes a supply passage extending radially inside. The supply passages are arranged in a plurality of circumferential directions, one end of which is connected to the cooling passage, and the other end of which is formed at the end of the second main body and is connected to the space surrounded by the shell.

18. A gas turbine, wherein, The gas turbine includes: The sealing member according to any one of claims 1 to 17; A burner, which is connected to the axially upward flow side of the sealing member; and A turbine, which is driven by combustion gases produced by the burner.

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