Patent Grant
11834957
The present disclosure relates to a strut cover for a gas turbine, an exhaust casing including the strut cover, and a gas turbine.
The gas turbine is equipped with a combustor for generating high-temperature and high-pressure combustion gas using compressed air and fuel, a turbine rotationally driven by the combustion gas to generate rotational power, and an exhaust casing to which the combustion gas that has rotationally driven the turbine is supplied (see Patent Document 1, for example). The combustion gas that has rotationally driven the turbine is converted to static pressure in the diffuser passage of the exhaust casing. The diffuser passage is defined by a cylindrical outer diffuser and a cylindrical inner diffuser disposed inside the outer diffuser.
In Patent Document 1, a strut is connected to a casing wall forming the outer shape of the exhaust casing and to a bearing casing internally accommodating a bearing portion that supports the rotor. The casing wall is disposed outside the outer diffuser, and the bearing casing is disposed inside the inner diffuser. Accordingly, the strut is arranged so as to traverse the diffuser passage.
In Patent Document 1, a strut cover covers the strut and forms a flow passage for cooling air between the strut cover and the strut. The strut cover is connected at the outer end to the outer diffuser and at the inner end to the inner diffuser. The outer end and the inner end of the strut cover have a flare shape with a large bulge in the outer shape. Further, the components of the exhaust casing such as the strut cover are manufactured by sheet metal welding.
Patent Document 1: JP2013-57302A
The outer diffuser and the inner diffuser vibrate when the combustion gas flows through the diffuser passage, and stress (vibration stress) is generated by the vibration in the strut cover connecting the outer diffuser and the inner diffuser. Further, stress (impact stress) is generated by the impingement of the combustion gas on the strut cover.
In recent years, as the output power of the gas turbine has increased, the temperature of the combustion gas flowing through the diffuser passage tends to increase. The outer diffuser, the inner diffuser, and the strut cover may become hot due to the heat transferred from the combustion gas. In such a high temperature environment, the risk of break or damage to the strut cover increases due to high cycle fatigue caused by the stress generated in the strut cover.
Since the strut cover described in Patent Document 1 has a uniform thickness from the outer end to the inner end, the stress is concentrated on the flare portion, and the strut cover may break or be damaged due to high cycle fatigue caused by the stress.
In view of the above, an object of at least one embodiment of the present disclosure is to provide a strut cover for a gas turbine that can improve the high cycle fatigue strength.
A strut cover for a gas turbine according to the present disclosure comprises: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.
An exhaust casing of a gas turbine according to the present disclosure comprises: a cylindrical casing wall; a cylindrical outer diffuser disposed on a radially inner side of the casing wall; an inner diffuser disposed on a radially inner side of the outer diffuser and forming a diffuser passage between the inner diffuser and the outer diffuser; and the above-described strut cover. The flare member of the strut cover includes: an outer flare member connected to the outer diffuser; and an inner flare member connected to the inner diffuser.
A gas turbine according to the present disclosure comprises the above-described exhaust casing.
At least one embodiment of the present disclosure provides a strut cover for a gas turbine that can improve the high cycle fatigue strength.
Embodiments of the present disclosure will be described below with reference to the accompanying drawings. It is intended, however, that unless particularly identified, dimensions, materials, shapes, relative positions, and the like of components described in the embodiments shall be interpreted as illustrative only and not intended to limit the scope of the present disclosure.
For instance, an expression of relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “centered”, “concentric” and “coaxial” shall not be construed as indicating only the arrangement in a strict literal sense, but also includes a state where the arrangement is relatively displaced by a tolerance, or by an angle or a distance whereby it is possible to achieve the same function.
For instance, an expression of an equal state such as “same” “equal” and “uniform” shall not be construed as indicating only the state in which the feature is strictly equal, but also includes a state in which there is a tolerance or a difference that can still achieve the same function.
Further, for instance, an expression of a shape such as a rectangular shape or a cylindrical shape shall not be construed as only the geometrically strict shape, but also includes a shape with unevenness or chamfered corners within the range in which the same effect can be achieved.
On the other hand, an expression such as “comprise”, “include”, “have”, “contain” and “constitute” are not intended to be exclusive of other components.
The same features can be indicated by the same reference numerals and not described in detail.
(Gas Turbine)
As shown in
The compressor 11 includes a plurality of stator blades 15 fixed to a compressor casing 14 and a plurality of rotor blades 17 implanted on a rotor 16 so as to be arranged alternately with the stator blades 15.
To the compressor 11, air sucked in from an air inlet 18 is supplied. The air supplied to the compressor 11 flows through the plurality of stator blades 15 and the plurality of rotor blades 17 and is compressed into compressed air having a high temperature and a high pressure.
The combustor 12 is supplied with fuel and the compressed air produced in the compressor 11. The combustor 12 combusts the fuel to produce combustion gas that serves as a working fluid of the turbine 13. In the embodiment shown in
The turbine 13 has a combustion gas passage 22 formed by a turbine casing 21 and includes a plurality of stator blades 23 and a plurality of rotor blades 24 disposed in the combustion gas passage 22. The stator blades 23 and the rotor blades 24 of the turbine 13 are disposed downstream of the combustors 12 in the flow direction of the combustion gas.
The stator blades 23 are fixed to the turbine casing 21, and a set of the stator blades 23 arranged along the circumferential direction of the rotor 16 forms a stator blade array. Further, the rotor blades 24 are implanted on the rotor 16, and a set of the rotor blades 24 arranged along the circumferential direction of the rotor 16 forms a rotor blade array. The stator blade arrays and the rotor blade arrays are arranged alternately in the axial direction of the rotor 16.
In the turbine 13, as the combustion gas introduced from the combustor 12 into the combustion gas passage 22 passes through the plurality of stator blades 23 and the plurality of rotor blades 24, the rotor 16 is rotationally driven. Thereby, the generator connected to the rotor 16 is driven to generate power. The combustion gas having driven the turbine 13 is discharged outside via the exhaust casing 3.
(Exhaust Casing)
As shown in
As shown in
The exhaust casing 3 further includes a cylindrical outer diffuser 33 disposed on the radially inner side of the casing wall 31, a cylindrical inner diffuser 35 disposed on the radially inner side of the outer diffuser 33 and forming a diffuser passage 34 between the inner diffuser 35 and the outer diffuser 33, and a partition wall 36 disposed between the inner diffuser 35 and the bearing casing 32. The outer diffuser 33, the inner diffuser 35, and the partition wall 36 each extend along the axial direction of the rotor 16. The strut cover 5 connects the outer diffuser 33 and the inner diffuser 35.
In the illustrated embodiment, each of the casing wall 31 and the bearing casing 32 is formed in a cylindrical shape centered on the center axis CA. The casing wall 31 has an outer wall surface 311 that forms the outer shape of the exhaust casing 3. The bearing casing 32 accommodates a bearing portion 37 and supports the bearing portion 37 in a non-rotatable manner. The bearing portion 37 supports the rotor 16 in a rotatable manner.
The diffuser passage 34 is configured to be supplied with combustion gas that has passed through the final stage rotor blade 24A of the turbine 13, and is formed in an annular shape in which the cross-sectional area gradually expands toward the downstream side. When the combustion gas is supplied to the diffuser passage 34, the speed of the gas decreases, and kinetic energy of the gas is converted to pressure (static pressure recovery).
In the illustrated embodiment, each of the outer diffuser 33 and the inner diffuser 35 is formed in a cylindrical shape centered on the center axis CA. The outer diffuser 33 has an inner wall surface 331 with a distance from the center axis CA gradually increasing toward the downstream side. The inner diffuser 35 has an outer wall surface 351 with a uniform distance from the center axis CA. The diffuser passage 34 is formed by the inner wall surface 331 of the outer diffuser 33 and the outer wall surface 351 of the inner diffuser 35, and has a shape that gradually expands outward in the radial direction as it extends downstream.
As shown in
In the illustrated embodiment, as shown in
In the illustrated embodiment, the at least one strut 4 includes a plurality of (six in the figure) struts 4 spaced from each other in the circumferential direction. Further, the at least one strut cover 5 includes a plurality of (six in the figure) strut covers 5 spaced from each other in the circumferential direction.
The strut 4 is disposed so as to penetrate the outer diffuser 33 and the inner diffuser 35 and traverse the diffuser passage 34. The outer diffuser 33 is formed with a communication hole 332 that connects the inside and the outside in the radial direction, and the strut 4 is inserted through the communication hole 332. The inner diffuser 35 is formed with a communication hole 352 that connects the inside and the outside in the radial direction, and the strut 4 is inserted through the communication hole 352.
In the illustrated embodiment, components (e.g., outer diffuser 33, inner diffuser 35, strut 4 and strut cover 5) disposed inside the exhaust casing 3 are cooled by flowing cooling air inside the exhaust casing 3.
In the embodiment shown in
The first cooling passage 38A communicates with the intake port 312 and is configured to pass cooling air introduced from the intake port 312. The second cooling passage 38B communicates with the first cooling passage 38A through the communication hole 332 and is configured to pass the cooling air. The third cooling passage 38C communicates with the second cooling passage 38B through the communication hole 352 and is configured to pass the cooling air.
The cooling air introduced from the intake port 312 into the exhaust casing 3 flows through the first cooling passage 38A, the second cooling passage 38B, and the third cooling passage 38C in this order, and cools the components (e.g., outer diffuser 33, inner diffuser 35, strut 4, and strut cover 5) facing these cooling passages 38A, 38B, and 38C to suppress the temperature rise of the components.
In the illustrated embodiment, the inner diffuser 35 has a discharge port 353 for discharging the cooling air to the diffuser passage 34. The discharge port 353 penetrates the inside and outside of the inner diffuser 35 in the radial direction, and connects an upstream diffuser inlet portion 34A of the diffuser passage 34 and the third cooling passage 38C. Since the diffuser inlet portion 34A is adjust to the final stage rotor blade 24A of the turbine 13, the pressure of the combustion gas in the diffuser inlet portion 34A is negative pressure compared to the static pressure. Due to the pressure difference between the air outside the exhaust casing 3 and the negative pressure, the outside air is introduced through the intake port 312 as the cooling air, and after passing through the cooling passages 38A, 38B, and 38C, is discharged through the discharge port 353.
(Strut Cover)
The strut cover 5 according to some embodiments includes, for example as shown in
The cylindrical sheet metal member 6 is formed in a cylindrical shape extending along the axial direction of the cylindrical sheet metal member 6, and is shaped by sheet metal processing. That is, the cylindrical sheet metal member 6 is a sheet metal part. Since the cylindrical sheet metal member 6 is formed by sheet metal processing, the thickness can be reduced. The hollow portion 61 of the cylindrical sheet metal member 6 is defined by the inner surface 65 of the cylindrical sheet metal member 6.
In the illustrated embodiment, for example as shown in
In the illustrated embodiment, for example as shown in
In the illustrated embodiment, for example as shown in
In the illustrated embodiment, for example as shown in
The strut 4 is inserted into the hollow portion 61 of the cylindrical sheet metal member 6 and the hollow portion 76 of the flare member 7, and the second cooling passage 38B is formed between the hollow portion 61 and the inserted strut 4.
The strut cover 5 according to some embodiments includes, for example as shown in
In the embodiment shown in
In the embodiment shown in
According to the above configuration, the strut cover 5 includes the cylindrical sheet metal member 6 having the hollow portion 61 and the flare member 7. The flare member 7 has a thickness larger than the minimum thickness TC of the cylindrical sheet metal member 6 at least in the curved portion 71. In this case, since the curved portion 71 of the flare member 7 is thick, the stress generated in the curved portion 71 can be reduced. By reducing the stress generated in the curved portion 71, it is possible to improve the high cycle fatigue strength of the strut cover 5.
Further, according to the above configuration, the wall thickness of the cylindrical sheet metal member 6 can be reduced compared to a casting part formed by casting. By reducing the wall thickness of the cylindrical sheet metal member 6, the outer surface 66 (see
In some embodiments, as shown in
According to the above configuration, since the inner surface 712 of the curved portion 71 of the flare member 7 protrudes toward the center axis CB with respect to the inner surface 65 of the cylindrical sheet metal member 6, the thickness of the curved portion 71 can be increased while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage 34 due to an increase in distance of the outer surface 711 of the curved portion 71 from the center axis CB.
In some embodiments, as shown in
According to the above configuration, since the inner surface 741 of the thick-walled portion 74 of the flare member 7 curves convexly, the thick-walled portion 74 is prevented from becoming excessively thick. By preventing the thick-walled portion 74 from becoming excessively thick, the thermal stress caused by the temperature difference between the inner surface 741 facing the second cooling passage 38B of the thick-walled portion 74 and the outer surface 711 disposed on the opposite side from the inner surface 741 in the thickness direction can be reduced. By reducing the thermal stress generated in the flare member 7, it is possible to improve the high cycle fatigue strength of the strut cover 5.
Further, according to the above configuration, since the inner surface 741 of the thick-walled portion 74 of the flare member 7 curves convexly, the shape change of the inner surface 741 is gradual, and the stress concentration in the flare member 7 can be relaxed. By relaxing the stress concentration in the flare member 7, it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, as shown in
In some embodiments, as shown in
According to the above configuration, in a cross-section along the center axis CB, since the flare member 7 bulges on the opposite side of the tangential line TL from the cylindrical sheet metal member 6, the thickness of the portion including the bulge portion 75 of the flare member 7 can be increased while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage 34 due to an increase in distance of the outer surface of the curved portion 71 (outer surface 711 of curved portion 71 or outer surface 733 of flange portion 73) from the tangential line TL.
In some embodiments, as shown in
According to the above configuration, since the inner surface 751 of the bulge portion 75 of the flare member 7 curves convexly, the bulge portion 75 is prevented from becoming excessively thick. By preventing the bulge portion 75 from becoming excessively thick, the thermal stress caused by the temperature difference between the inner surface 751 facing the cooling passage of the bulge portion 75 (e.g., first cooling passage 38A) and the outer surface (e.g., outer surface 711, 733) disposed on the opposite side from the inner surface 751 in the thickness direction can be reduced. By reducing the thermal stress generated in the flare member 7, it is possible to improve the high cycle fatigue strength of the strut cover 5.
Further, according to the above configuration, since the inner surface 751 of the bulge portion 75 of the flare member 7 curves convexly, the shape change of the inner surface 751 is gradual, and the stress concentration in the flare member 7 can be relaxed. By relaxing the stress concentration in the flare member 7, it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, for example as shown in
As shown in
The region AR3 and the region AR4 of the flare member 7 face each other in the direction along the major axis LA of the hollow portion 61 (in the right-left direction in
The region AR5 and the region AR6 of the flare member 7 face each other in the direction along the minor axis MA of the hollow portion 61 (in the up-down direction in
Hereinafter, for example as shown in
In the illustrated embodiment, as shown in
As shown in
In the illustrated embodiment, as shown in
As shown in
According to the above configuration, the angle between the tangential direction to the outer surface 733 of the flange portion 73 and the center axis CB is larger in the second region AR2 than in the first region AR1. Therefore, the curved portion 71 (71B) in the second region AR2 is gently curved as compared to the curved portion 71 (71A) in the first region AR1, and the stress generated in the curved portion 71 is small in the second region AR2, so that the thickness of the curved portion 71 can be reduced. Thus, when the thickness of the curved portion 71 fluctuates according to the angle (first angle α and second angle β) in the first region AR1 and the second region AR2, the thickness of the curved portion 71 in each of the first region AR1 and the second region AR2 can be made appropriate while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage 34. By making the thickness of the curved portion 71 appropriate, the stress (vibration stress and thermal stress) generated in the curved portion 71 can be reduced. Thus, it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, as shown in
According to the above configuration, the first region AR1 (region AR3) of the flare member 7 is disposed on one side in the direction along the major axis LA, and the second region AR2 (region AR4) is disposed on the other side in the direction along the major axis LA. That is, since the angle between the tangential direction to the outer surface 733 of the flange portion 73 and the center axis CB is larger in the region AR4 disposed on the other side in the direction along the major axis LA than in the region AR3 disposed on one side in the direction along the major axis LA, the stress generated in the curved portion 71B in the region AR4 is small, and thus the thickness of the curved portion 71B in the region AR4 can be reduced. Thus, according to the above configuration, the thickness of the curved portion 71 can be made appropriate in each of the region AR3 disposed on one side in the direction along the major axis LA and the region AR4 disposed on the other side in the direction along the major axis LA.
In some embodiments, for example as shown in
In some embodiments, as shown in
According to the above configuration, the first region AR1 (region AR5) of the flare member 7 is disposed on one side in the direction along the minor axis MA, and the second region AR2 (region AR6) is disposed on the other side in the direction along the minor axis MA. That is, since the angle between the tangential direction to the outer surface 733 of the flange portion 73 and the center axis CB is larger in the region AR6 disposed on the other side in the direction along the minor axis MA than in the region AR5 disposed on one side in the direction along the minor axis MA, the stress generated in the curved portion 71B in the region AR6 is small, and thus the thickness of the curved portion 71B in the region AR6 can be reduced. Thus, according to the above configuration, the thickness of the curved portion 71 can be made appropriate in each of the region AR5 disposed on one side in the direction along the minor axis MA and the region AR6 disposed on the other side in the direction along the minor axis MA.
Further, according to the above configuration, as shown in
In some embodiments, the flare member 7 includes the curved portion 71, the connection end 70 connected to the cylindrical sheet metal member 6, and the cylindrical portion 72 extending along the center axis CB between the curved portion 71 and the connection end 70. As shown in
According to the above configuration, the combustion gas flowing through the diffuser passage 34 has not only a velocity component along the axial direction of the exhaust casing 3 (the axial direction of the rotor 16) but also a velocity component that swirls along the circumferential direction. Therefore, when the combustion gas impinges on the strut cover 5, the impingement force acts to twist the strut cover 5. Thus, a larger force acts on the major axis end of the flare member 7, that is, the third region BR1, than on the minor axis end of the flare member 7, that is, the fourth region BR2. By making the thickness TT1 of the cylindrical portion 72 in the third region BR1 larger than the thickness TT2 of the cylindrical portion 72 in the fourth region BR2, the stress generated in the third region BR1 can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, for example as shown in
In some embodiments, the flare member 7 is a casting part formed by casting. Here, the flare member 7 which is a sheet metal part formed by sheet metal processing, for example as shown in
According to the above configuration, since the flare member 7 is a casting part, the wall thickness can be easily increased compared to a sheet metal part formed by sheet metal processing. Further, the flare member 7 which is a casting part allows the curvature radius of the outer surface of the curved portion to be reduced compared to a sheet metal part, the reduction in the flow-passage cross-sectional area of the diffuser passage can be effectively suppressed. Either one of the outer flare member 7A or the inner flare member 7B may be a casting part, and the other may be a sheet metal part.
As shown in
According to the above configuration, the flare member 7 of the strut cover 5 includes the outer flare member 7A connected to the outer diffuser 33 and the inner flare member 7B connected to the inner diffuser 35. Since each of the outer flare member 7A and the inner flare member 7B has a thickness larger than the minimum thickness of the cylindrical sheet metal member 6 at least in the curved portion 71, the stress generated in the curved portion 71 can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, as shown in
According to the above configuration, the diffuser passage 34 is hotter and the flow velocity of the combustion gas is higher on the outer peripheral side (the radially outer side) of the exhaust casing 3 where the outer flare member 7A is located than on the inner peripheral side (the radially inner side) where the inner flare member 7B is located. Thus, a larger force acts on the outer flare member 7A than on the inner flare member 7B. By making the thickness of the curved portion 71 upstream of the center axis CB in the diffuser passage 34 in the outer flare member 7A than in the inner flare member 7B, the stress generated in the curved portion 71 can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover 5.
In some embodiments, at least one of the outer diffuser 33 or the inner diffuser 35 is a sheet metal part.
According to the above configuration, since at least one of the outer diffuser 33 or the inner diffuser 35 is a sheet metal part, the thickness of the diffuser can be reduced, so that the reduction in the flow-passage cross-sectional area of the diffuser passage 34 can be suppressed. Further, since at least one of the outer diffuser 33 or the inner diffuser 35 is a sheet metal part, it vibrates greatly due to the combustion gas flowing through the diffuser passage 34, and vibration stress is generated in the flare member 7 of the strut cover 5. By increasing the thickness of the curved portion 71 of the flare member 7, the vibration stress generated in the curved portion 71 can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover 5.
The gas turbine 1 according to some embodiments includes the above-described exhaust casing 3, as shown in
The present disclosure is not limited to the embodiments described above, but includes modifications to the embodiments described above, and embodiments composed of combinations of those embodiments.
The contents described in the above embodiments would be understood as follows, for instance.
1) A strut cover (5) for a gas turbine (1) according to at least one embodiment of the present disclosure comprises: a cylindrical sheet metal member (6) having a hollow portion (61); and a flare member (7) that is connected to one end of the cylindrical sheet metal member (6) in an axial direction of the cylindrical sheet metal member (6) and includes a curved portion (71) having an outer surface (711) such that a distance from a center axis (CB) of the cylindrical sheet metal member (6) to the outer surface (711) increases with increasing a distance from the cylindrical sheet metal member (6) in the axial direction. The flare member (7) has a thickness larger than a minimum thickness (TC) of the cylindrical sheet metal member (6) at least in the curved portion (71).
According to the above configuration 1), the strut cover includes the cylindrical sheet metal member having the hollow portion and the flare member. The flare member has a thickness larger than the minimum thickness of the cylindrical sheet metal member at least in the curved portion. In this case, since the curved portion of the flare member is thick, the stress generated in the curved portion can be reduced. By reducing the stress generated in the curved portion, it is possible to improve the high cycle fatigue strength of the strut cover.
Further, according to the above configuration 1), the wall thickness of the cylindrical sheet metal member can be reduced compared to a casting part formed by casting. By reducing the wall thickness of the cylindrical sheet metal member, the outer surface of the cylindrical sheet metal member can be brought closer to the center axis of the cylindrical sheet metal member, and thus the reduction in the flow-passage cross-sectional area of the diffuser passage (34) can be suppressed. By suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage, it is possible to suppress the reduction in performance of the gas turbine.
2) In some embodiments, in the strut cover (5) described in 1), an inner surface (712) of the curved portion (71) of the flare member (7) protrudes toward the center axis (CB) with respect to an inner surface (65) of the cylindrical sheet metal member (6).
According to the above configuration 2), since the inner surface of the curved portion of the flare member protrudes toward the center axis with respect to the inner surface of the cylindrical sheet metal member, the thickness of the curved portion can be increased while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage (34) due to an increase in distance of the outer surface (711) of the curved portion from the center axis.
3) In some embodiments, in the strut cover (5) described in 1) or 2), the flare member (7) includes: a connection end (70) connected to the cylindrical sheet metal member (6); and a flange portion (73) disposed on an opposite side of the curved portion (71) from the connection end (70). In a cross-section along the center axis (CB), the flare member (7) bulges on an opposite side of a tangential line (TL) to an inner surface (732) of the flange portion (73) in an outer peripheral region (731) of the flange portion (73) from the cylindrical sheet metal member (6).
According to the above configuration 3), in a cross-section along the center axis, since the flare member bulges on the opposite side of the tangential line from the cylindrical sheet metal member, the thickness of the portion including the bulge portion (75) of the flare member can be increased while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage (34) due to an increase in distance of the outer surface of the curved portion (outer surface 711 of curved portion 71 or outer surface 733 of flange portion 73) from the tangential line.
4) In some embodiments, in the strut cover (5) described in 3), in a cross-section along the center axis (CB), an inner surface (751) of the bulge portion (75) of the flare member (7) that bulges on the opposite side of the tangential line (TL) from the cylindrical sheet metal member (6) curves convexly.
According to the above configuration 4), since the inner surface of the bulge portion of the flare member curves convexly, the bulge portion is prevented from becoming excessively thick. By preventing the bulge portion from becoming excessively thick, the thermal stress caused by the temperature difference between the inner surface facing the cooling passage (e.g., first cooling passage 38A) of the bulge portion and the outer surface (e.g., outer surface 711, 733) disposed on the opposite side from the inner surface in the thickness direction can be reduced. By reducing the thermal stress generated in the flare member, it is possible to improve the high cycle fatigue strength of the strut cover.
Further, according to the above configuration, since the inner surface of the bulge portion of the flare member curves convexly, the shape change of the inner surface is gradual, and the stress concentration in the flare member can be relaxed. By relaxing the stress concentration in the flare member, it is possible to improve the high cycle fatigue strength of the strut cover.
5) In some embodiments, in the strut cover (5) described in any one of 1) to 4), the flare member (7) includes: a connection end (70) connected to the cylindrical sheet metal member (6); and a flange portion (73) disposed on an opposite side of the curved portion (71) from the connection end (70). The flare member (7) includes: a first region (AR1, for example AR3 in
According to the above configuration 5), the angle between the tangential direction to the outer surface of the flange portion and the center axis is larger in the second region than in the first region. Therefore, the curved portion (71B) in the second region is gently curved as compared to the curved portion (71A) in the first region, and the stress generated in the curved portion (71B) is small in the second region, so that the thickness of the curved portion (71B) can be reduced. Thus, when the thickness of the curved portion fluctuates according to the angle (first angle α and second angle β) in the first region and the second region, the thickness of the curved portion in each of the first region and the second region can be made appropriate while suppressing the reduction in the flow-passage cross-sectional area of the diffuser passage (34). By making the thickness of the curved portion appropriate, the vibration stress and thermal stress generated in the curved portion can be reduced. Thus, it is possible to improve the high cycle fatigue strength of the strut cover.
6) In some embodiments, in the strut cover (5) described in 5), in a cross-section perpendicular to the center axis (CB), the hollow portion (61) has a minor axis (MA) and a major axis (LA) larger than the minor axis (MA). The first region (region AR3) and the second region (region AR4) of the flare member (7) face each other in a direction along the major axis (LA) of the hollow portion (61), with the center axis (CB) therebetween.
According to the above configuration 6), the first region of the flare member is disposed on one side in the direction along the major axis, and the second region is disposed on the other side in the direction along the major axis. That is, since the angle between the tangential direction to the outer surface (733) of the flange portion (73) and the center axis is larger in the region (second region) disposed on the other side in the direction along the major axis than in the region (first region) disposed on one side in the direction along the major axis, the stress generated in the curved portion (71B) in the region is small, and thus the thickness of the curved portion in the region can be reduced. Thus, according to the above configuration, the thickness of the curved portion (71) can be made appropriate in each of the region (first region) disposed on one side in the direction along the major axis and the region (second region) disposed on the other side in the direction along the major axis.
7) In some embodiments, in the strut cover (5) described in 5), in a cross-section perpendicular to the center axis (CB), the hollow portion (61) has a minor axis (MA) and a major axis (LA) larger than the minor axis (MA). The first region (region AR5) and the second region (region AR6) of the flare member (7) face each other in a direction along the minor axis (MA) of the hollow portion (61), with the center axis (CB) therebetween.
According to the above configuration 7), the first region of the flare member is disposed on one side in the direction along the minor axis, and the second region is disposed on the other side in the direction along the minor axis. That is, since the angle between the tangential direction to the outer surface (733) of the flange portion (73) and the center axis is larger in the region (second region) disposed on the other side in the direction along the minor axis than in the region (first region) disposed on one side in the direction along the minor axis, the stress generated in the curved portion (71B) in the region is small, and thus the thickness of the curved portion in the region can be reduced. Thus, according to the above configuration, the thickness of the curved portion (71) can be made appropriate in each of the region (first region) disposed on one side in the direction along the minor axis and the region (second region) disposed on the other side in the direction along the minor axis.
8) In some embodiments, in the strut cover (5) described in any one of 1) to 4), the flare member (7) includes: a connection end (70) connected to the cylindrical sheet metal member (6); and a cylindrical portion (72) extending along the center axis (CB) between the curved portion (71) and the connection end (70). In a cross-section perpendicular to the center axis (CB), the hollow portion (61) has a minor axis (MA) and a major axis (LA) larger than the minor axis (MA). The flare member (7) includes: a third region (BR1) intersecting a straight line (LA1) extending from the center axis (CB) in a direction along the major axis (LA) in a cross-section perpendicular to the center axis (CB); and a fourth region (BR2) intersecting a straight line (MA1) extending from the center axis (CB) in a direction along the minor axis (MA) in a cross-section perpendicular to the center axis (CB). The cylindrical portion (72) has a thinner thickness in the fourth region (BR2) than in the third region (BR1).
According to the above configuration 8), the combustion gas flowing through the diffuser passage has not only a velocity component along the axial direction of the exhaust casing but also a velocity component that swirls along the circumferential direction. Therefore, when the combustion gas impinges on the strut cover, the impingement force acts to twist the strut cover. Thus, a larger force acts on the major axis end of the flare member, that is, the third region, than on the minor axis end of the flare member, that is, the fourth region. By making the thickness (TT1) of the cylindrical portion in the third region larger than the thickness (TT2) of the cylindrical portion in the fourth region, the stress generated in the third region can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover.
9) In some embodiments, in the strut cover (5) described in any one of 1) to 8), the flare member (7) is a casting part formed by casting.
According to the above configuration 9), since the flare member is a casting part, the wall thickness can be easily increased compared to a sheet metal part formed by sheet metal processing. Further, the flare member which is a casting part allows the curvature radius of the outer surface of the curved portion to be reduced compared to a sheet metal part, the reduction in the flow-passage cross-sectional area of the diffuser passage (34) can be effectively suppressed.
10) An exhaust casing (3) of a gas turbine (1) according to at least one embodiment of the present disclosure comprises: a cylindrical casing wall (31); a cylindrical outer diffuser (33) disposed on a radially inner side of the casing wall (31); an inner diffuser (35) disposed on a radially inner side of the outer diffuser (33) and forming a diffuser passage (34) between the inner diffuser (35) and the outer diffuser (33); and the strut cover (5) described in any one of 1) to 9). The flare member (7) of the strut cover (5) includes: an outer flare member (7A) connected to the outer diffuser (33); and an inner flare member (7B) connected to the inner diffuser (35).
According to the above configuration 10), the flare member of the strut cover includes the outer flare member connected to the outer diffuser and the inner flare member connected to the inner diffuser. Since each of the outer flare member and the inner flare member has a thickness larger than the minimum thickness of the cylindrical sheet metal member at least in the curved portion, the stress generated in the curved portion can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover.
11) In some embodiments, in the exhaust casing (3) described in 10), in a cross-section along an axis (EA) of the exhaust casing (3), a thickness of the curved portion (71) upstream of at least the center axis (CB) in the diffuser passage (34) is thicker in the outer flare member (7A) than in the inner flare member (7B).
According to the above configuration 11), the diffuser passage is hotter on the outer peripheral side of the exhaust casing where the outer flare member is located than on the inner peripheral side where the inner flare member is located, and a larger force acts on the outer flare member than on the inner flare member. By making the thickness of the curved portion upstream of the center axis in the diffuser passage in the outer flare member than in the inner flare member, the stress generated in the curved portion can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover.
12) In some embodiments, in the exhaust casing (3) described in 10) or 11), at least one of the outer diffuser (33) or the inner diffuser (35) is a sheet metal part.
According to the above configuration 12), since at least one of the outer diffuser or the inner diffuser is a sheet metal part, the thickness of the diffuser can be reduced, so that the reduction in the flow-passage cross-sectional area of the diffuser passage can be suppressed. Further, since at least one of the outer diffuser or the inner diffuser is a sheet metal part, it vibrates greatly due to the combustion gas flowing through the diffuser passage, and vibration stress is generated in the flare member of the strut cover. By increasing the thickness of the curved portion of the flare member, the vibration stress generated in the curved portion can be reduced, so that it is possible to improve the high cycle fatigue strength of the strut cover.
13) A gas turbine (1) according to at least one embodiment of the present disclosure comprises the exhaust casing (3) described in any one of (10) to (12).
According to the above configuration 13), the exhaust casing of the gas turbine includes the above-described strut cover (5). In this case, since the reduction in the flow-passage cross-sectional area of the diffuser passage (34) is suppressed, it is possible to suppress the reduction in performance of the gas turbine. Further, since the high cycle fatigue strength of the strut cover is improved, it is possible to improve the reliability of the gas turbine for long-term operation.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2019-165806 | Sep 2019 | JP | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2020/034097 | 9/9/2020 | WO |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2021/049523 | 3/18/2021 | WO | A |
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| Number | Date | Country | |
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| 20220325635 A1 | Oct 2022 | US |
