Patent Grant
11788417
The present invention relates to a turbine blade such as a rotor blade and a stator vane applied to a gas turbine, and a gas turbine provided with the turbine blade.
A gas turbine includes a compressor, a combustor, and a turbine. The compressor compresses air taken in through an air intake port to obtain high-temperature and high-pressure compressed air. The combustor obtains a high-temperature and high-pressure combustion gas by supplying fuel to the compressed air and performing combustion. The turbine is driven by the combustion gas and drives a coaxially connected generator.
A technique is known in which a cooling passage is provided in a turbine blade such as a rotor blade and a stator vane in a gas turbine and a cooling fluid is caused to flow through the cooling passage such that the turbine blade exposed to a high-temperature gas stream is cooled. For example, in PTL 1 below, a technique is described in which a cooling air passage is provided in a rotor blade and cooling air is blown out through a hole on a trailing edge side after passing through the cooling air passage. In addition, a technique is also described in which a fillet portion having an oval shape is provided at a connecting portion between a blade base end portion and a platform in the rotor blade to reduce a thermal stress.
In the related art, as described above, a thermal stress is likely to be generated at a connecting portion between a blade base end portion and a platform in a turbine blade such as a rotor blade. Therefore, for the purpose of alleviating the thermal stress at the connecting portion between the blade base end portion and the platform, a fillet portion is formed at the connecting portion. With the fillet portion formed at the connecting portion, the thermal stress can be reduced. On the other hand, since a turbine blade receives a high-temperature gas stream, there is a demand for aerodynamically reducing the size of the fillet portion at the connecting portion between the blade base end portion and the platform.
The present invention has been made to solve the above-described problem, and an object thereof is to provide a turbine blade and a gas turbine that reduce a thermal stress at a fillet portion while suppressing a decrease in aerodynamic performance.
In order to achieve the object described above, an aspect of the present invention provides a turbine blade including an airfoil portion that internally includes a cooling air passage, a blade base end portion that is provided at an end portion of the airfoil portion in a blade height direction, and a fillet portion that is provided around an entire periphery of a connecting portion between the airfoil portion and the blade base end portion. The fillet portion includes a first fillet portion that is provided closer to a trailing edge than a position at which a distance between a suction side blade surface of the airfoil portion and a suction side end portion of the blade base end portion is smallest while being on a suction side of the airfoil portion and of which a fillet width is larger than a fillet width of other regions of the fillet portion.
Therefore, a portion of the fillet portion that is on the trailing edge side while being on the suction side of the airfoil portion is likely to receive a thermal stress. Since the first fillet portion, of which the fillet width is larger than the fillet width at the other regions of the fillet portion, is provided in this portion, a thermal stress in the fillet portion can be reduced.
In the turbine blade according to the aspect of the present invention, the first fillet portion is provided closer to the trailing edge than a throat portion between the airfoil portions adjacent to each other.
Therefore, there is less influence on a decrease in aerodynamic performance while a thermal stress at the fillet portion can be reduced.
In the turbine blade according to the aspect of the present invention, an aspect ratio, which is a ratio of a fillet height to the fillet width, of the first fillet portion is smaller than an aspect ratio of the other regions of the fillet portion.
Therefore, the fillet width of the first fillet portion is larger than the fillet width of the other fillet portions, and thus it is possible to reduce generation of a thermal stress caused due to thermal elongation at the fillet portion.
In the turbine blade according to the aspect of the present invention, the first fillet portion includes a region at which the aspect ratio is constant along a circumferential direction of the fillet portion.
Therefore, it is possible to reduce a thermal stress in a predetermined region along the circumferential direction of the fillet portion.
In the turbine blade according to the aspect of the present invention, the aspect ratio of the first fillet portion is 1.0.
Therefore, a thermal stress at the first fillet portion can be reduced.
In the turbine blade according to the aspect of the present invention, the first fillet portion includes a first end portion that is provided on a leading edge side of the airfoil portion along a blade surface of the fillet portion and a second end portion that is provided on the trailing edge side of the airfoil portion along the blade surface of the fillet portion, and the first end portion and the second end portion are connected to fillet change portions, at which a fillet width or a fillet height changes along the blade surface of the fillet portion.
Therefore, since the first fillet portion and the other fillet portions are connected to each other via the fillet change portions at which the fillet width or the fillet height changes, the fillet portion that is smoothly connected to a connecting portion between the airfoil portion and the blade base end portion is provided, and thus it is possible to suppress a decrease in aerodynamic performance and to suppress a sudden change in thermal stress.
In the turbine blade according to the aspect of the present invention, the airfoil portion includes a plurality of cooling holes that are arranged in a trailing edge portion at predetermined intervals in the blade height direction and each of which has one end communicating with the cooling air passage and has the other end open at a trailing edge end surface of the trailing edge portion and the fillet portion includes a second fillet portion that is provided on the trailing edge end surface while being close to the cooling holes and adjacent to an inner side in the blade height direction and of which a fillet height is smaller than a fillet height of other regions of the fillet portion.
Therefore, since the fillet height of the second fillet portion is smaller than the fillet height of the other fillet portions, the positions of the cooling holes in the blade height direction are closer to an upper surface of a platform than the other regions. Accordingly, the upper surface of the platform can be efficiently cooled by means of cooling air flowing through the cooling holes, and a thermal stress on the trailing edge portion side of the platform can be reduced.
In the turbine blade according to the aspect of the present invention, the fillet portion includes a third fillet portion that is connected to the first fillet portion via the fillet change portion along the suction side blade surface and is connected to the second fillet portion via the fillet change portion along a pressure side blade surface with a leading edge of the airfoil portion interposed therebetween.
Therefore, since the third fillet portion is provided over an area from the suction side blade surface to the pressure side blade surface with the leading edge of the airfoil portion interposed therebetween in addition to a first fillet and the second fillet portion, a fillet having an appropriate shape can be provided around the entire periphery between the airfoil portion and the blade base end portion. In addition, since the fillet change portions are provided, a decrease in aerodynamic performance can be suppressed.
In the turbine blade according to the aspect of the present invention, the third fillet portion includes a region at which an aspect ratio of a fillet height to a fillet width is constant along the blade surface of the fillet portion.
Therefore, it is possible to reduce a thermal stress in a predetermined region along the circumferential direction of the fillet portion.
In the turbine blade according to the aspect of the present invention, the fillet change portions include a first fillet change portion provided between the first end portion and a third end portion, and a fillet width of the first fillet change portion becomes smaller toward the third end portion from the first end portion while a fillet height of the first fillet change portion is maintained constant.
Therefore, the first fillet portion and the third fillet portion can be smoothly connected to each other by means of the first fillet change portion, and it is possible to suppress a decrease in aerodynamic performance and to suppress a sudden change in thermal stress.
In the turbine blade according to the aspect of the present invention, the first fillet change portion includes a fillet having an oval shape, of which an aspect ratio of a fillet height to a fillet width exceeds 1.0.
Therefore, the first fillet portion and the third fillet portion can be smoothly connected by means of the first fillet change portion.
In the turbine blade according to the aspect of the present invention, the fillet change portions include a second fillet change portion provided between the second end portion and the second fillet portion, and a fillet width and a fillet height of the second fillet change portion become smaller toward the second fillet portion from the second end portion.
Therefore, the first fillet portion and the second fillet portion can be smoothly connected to each other by means of the second fillet change portion, and it is possible to suppress a decrease in aerodynamic performance and to suppress a sudden change in thermal stress.
In the turbine blade according to the aspect of the present invention, the second fillet change portion includes a fillet having an oval shape, of which an aspect ratio of a fillet height to a fillet width exceeds 1.0.
Therefore, the first fillet portion and the second fillet portion can be smoothly connected by means of the second fillet change portion.
In the turbine blade according to the aspect of the present invention, the fillet change portions include a third fillet change portion provided between the fourth end portion and the second fillet portion, and a fillet height of the third fillet change portion becomes smaller toward the second fillet portion from the fourth end portion while a fillet width of the third fillet change portion is maintained constant.
Therefore, the second fillet portion and the third fillet portion can be smoothly connected to each other by means of the third fillet change portion, and it is possible to suppress a decrease in performance.
In the turbine blade according to the aspect of the present invention, the third fillet change portion includes a fillet having an oval shape, of which an aspect ratio of a fillet height to a fillet width exceeds 1.0.
Therefore, the second fillet portion and the third fillet portion can be smoothly connected by means of the third fillet change portion.
In the turbine blade according to the aspect of the present invention, the plurality of cooling holes include end portion cooling holes, of which an opening density is higher than an opening density of a plurality of other cooling holes, at positions adjacent to the second fillet portion on the blade base end portion side of the airfoil portion, and the end portion cooling holes are disposed to be adjacent to the airfoil portion side of the second fillet portion in the blade height direction.
Therefore, the cooling ability with respect to the vicinity of the second fillet portion is enhanced since the cooling holes of which the opening density is high are disposed close to the second fillet portion, and the cooling performance with respect to the second fillet portion can be improved.
In the turbine blade according to the aspect of the present invention, the first fillet portion is provided along a blade wall of a final passage on a most downstream side in a cooling air flow direction in the cooling air passage.
Therefore, the first fillet portion can be effectively cooled by means of cooling air flowing through the final passage in the cooling air passage.
In the turbine blade according to the aspect of the present invention, the cooling air passage includes a meandering passage provided in the airfoil portion, the first fillet portion is provided along the final passage on the most downstream side in the cooling air flow direction in the meandering passage, and a length of a region of the first fillet portion falls within a range of a length of the final passage in a chord direction.
Therefore, since the length of the final passage in the chord direction is larger than the length of the region of the first fillet portion, the first fillet portion can be appropriately cooled by means of cooling air flowing through the final passage.
In the turbine blade according to the aspect of the present invention, the blade base end portion includes a platform that extends in a direction orthogonal to the blade height direction of the airfoil portion, the platform includes a recessed groove portion that is formed at a trailing edge portion end surface of the platform and is recessed toward a leading edge side from the trailing edge portion end surface, the recessed groove portion extends from a pressure side end portion to a suction side end portion of the platform, and a leading edge side end portion of the recessed groove portion is provided to become closer to the trailing edge portion end surface of the platform toward the suction side end portion from the pressure side end portion of the platform.
Therefore, since the leading edge side end portion of the recessed groove portion is provided to become closer to the trailing edge portion of the platform toward the suction side from a pressure side of the airfoil portion, the rigidity of the platform 42 is decreased at a portion where the recessed groove portion is provided, and thus a stress at the blade trailing edge portion of the airfoil portion can be reduced.
In the turbine blade according to the aspect of the present invention, the end portion of the recessed groove portion that is on the leading edge side of the platform is positioned between a final passage on a most downstream side in a cooling air flow direction in the cooling air passage and the trailing edge end surface of the airfoil portion as seen in a plan view of the platform.
Therefore, with the recessed groove portion being close to the final passage in the cooling air passage, the recessed groove portion can be formed to have a sufficient depth in the vicinity of the connecting portion between the blade trailing edge portion of the airfoil portion and the platform.
In the turbine blade according to the aspect of the present invention, the end portion of the recessed groove portion that is on the leading edge side of the platform is linearly formed toward the suction side end portion from the pressure side end portion of the platform.
Therefore, since the end portion of the recessed groove portion is linear, the workability can be improved.
In the turbine blade according to the aspect of the present invention, the platform includes a first cooling passage that extends from the leading edge to the trailing edge along the suction side end portion of the airfoil portion platform and a second cooling passage that extends from the leading edge to the trailing edge along the pressure side end portion of the platform, and the first cooling passage and the second cooling passage communicate with the cooling air passage of the airfoil portion on an upstream side in a cooling air flow direction and are open to a combustion gas at the trailing edge portion end surface on a downstream side in the cooling air flow direction.
Therefore, since the cooling passages are provided in the platform and the cooling passages communicate with the cooling air passage, it is possible to efficiently cool the platform by supplying cooling air cooling the airfoil portion to the platform.
In the turbine blade according to the aspect of the present invention, the turbine blade is a rotor blade.
Therefore, it is possible to suppress a decrease in performance of the rotor blade and to reduce a thermal stress at the fillet portion.
In addition, a gas turbine according to the present invention includes a compressor that compresses air, a combustor that mixes compressed air compressed by the compressor and fuel with each other and that performs combustion, and a turbine that includes the turbine blade and that obtains rotational power by means of a combustion gas generated by the combustor.
Therefore, it is possible to suppress a decrease in performance of the turbine and to reduce a thermal stress at the fillet portion.
According to the turbine blade and the gas turbine of the present invention, it is possible to suppress a decrease in aerodynamic performance and to reduce a thermal stress at a fillet portion.
Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the drawings. Note that the present invention is not limited by the embodiments, and in a case where there are a plurality of embodiments, the present invention encompasses combinations of the embodiments.
In the first embodiment, a gas turbine 10 includes a compressor 11, a combustor 12, and a turbine 13 as shown in
The compressor 11 includes an air intake port 20 through which air is taken in, an inlet guide vane (IGV) 22 is provided in a compressor casing 21, a plurality of stator vanes 23 and a plurality of rotor blades 24 are alternately provided in the axial direction Da, and an air bleeding chamber 25 is provided on the outside thereof. The combustor 12 can perform combustion by supplying fuel with respect to compressed air compressed by the compressor 11 and burning the mixture thereof. In the turbine 13, a plurality of stator vanes 27 and a plurality of rotor blades 28 are alternately provided in the axial direction Da in a turbine casing 26. An exhaust chamber 30 is provided downstream of the turbine casing 26 with an exhaust casing 29 interposed therebetween, and the exhaust chamber 30 includes an exhaust diffuser 31 that is aligned with the turbine 13.
In addition, a rotor 32 is positioned such that the rotor 32 penetrates the central portions of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 30. An end portion of the rotor 32 that is on the compressor 11 side is rotatably supported by a bearing portion 33, and an end portion that is on the exhaust chamber 30 side is rotatably supported by a bearing portion 34. A plurality of disks, onto which the rotor blades 24 are respectively mounted, are laid on and fixed to the rotor 32 at the compressor 11, a plurality of disks, onto which the rotor blades 28 are respectively mounted, are laid on and fixed to the rotor 32 at the turbine 13, and a drive shaft of the generator (not shown) is connected to the end portion on the compressor 11 side.
Regarding the gas turbine 10, the compressor casing 21 of the compressor 11 is supported by a leg portion 35, the turbine casing 26 of the turbine 13 is supported by a leg portion 36, and the exhaust chamber 30 is supported by a leg portion 37.
Therefore, air taken in through the air intake port 20 of the compressor 11 passes through the inlet guide vane 22, the plurality of stator vanes 23, and the plurality of rotor blades 24 and is compressed to become high-temperature and high-pressure compressed air. In the combustor 12, predetermined fuel is supplied with respect to the compressed air, and combustion is performed. A high-temperature and high-pressure combustion gas, which is a working fluid generated in the combustor 12, passes through the plurality of stator vanes 27 and the plurality of rotor blades 28 constituting the turbine 13 to drive and rotate the rotor 32 and to drive the generator connected to the rotor 32. Meanwhile, the combustion gas that drives the turbine 13 is discharged to the atmosphere as an exhaust gas.
As shown in
The airfoil portion 41 is integrally formed by means of a blade surface 57 and a top plate 59 formed on a blade tip portion 56 side in the blade height direction Dh, the blade surface 57 being composed of a suction side blade surface 53 on a suction surface side that extends in the blade height direction Dh and that has a protruding shape and a pressure side blade surface 54 on a pressure surface side that has a recessed shape. The airfoil portion 41 has a hollow shape, the suction side blade surface 53 and the pressure side blade surface 54 are connected to each other on an upstream side in a flow direction of a combustion gas FG along the axial direction Da such that a leading edge 51 is formed and are connected to each other on a downstream side such that a trailing edge 52 is formed, and a trailing edge end surface 52a is formed at a trailing edge downstream side end surface. The airfoil portion 41 has a tapered shape that becomes narrower toward the blade tip portion 56 from the blade base end portion 55 and is bonded to the top plate 59 on the blade tip portion 56 side in the blade height direction Dh.
In the airfoil portion 41, a cooling air passage 60 is provided. The cooling air passage 60 includes a first cooling air passage 61, a second cooling air passage 62, a first supply passage 61a, and a second supply passage 62a. The first cooling air passage 61 is provided along the blade height direction Dh on the leading edge 51 side of the airfoil portion 41, is connected to the first supply passage 61a on the blade base end portion 55 side, and is open at the top plate 59 on the blade tip portion 56 side. The first supply passage 61a and the second supply passage 62a are formed in the blade root portion 43 and take in cooling air from the outside. In the first cooling air passage 61, cooling air supplied from the first supply passage 61a flows along the leading edge 51 in one direction in the blade height direction Dh, and the cooling air is discharged into the combustion gas FG on the outside via an opening formed in the top plate 59 on the blade tip portion 56 side. The second cooling air passage 62 is connected to the second supply passage 62a on the blade base end portion 55 side, and cooling air is supplied thereto from the second supply passage 62a. The second cooling air passage 62 is formed as a meandering passage (serpentine passage) inside the airfoil portion 41 and is provided on the trailing edge 52 side while being adjacent to the first cooling air passage 61. The second cooling air passage 62 includes a first passage 63, a first turn-back passage 64, a second passage 65, a second turn-back passage 66, and a third passage 67. The first passage 63, the second passage 65, and the third passage 67 are provided along the blade height direction Dh, and the third passage 67 is connected to the opening formed in the top plate 59 on the blade tip portion 56 side. In the second cooling air passage 62, cooling air supplied from the second supply passage 62a flows through the first passage 63, the first turn-back passage 64, the second passage 65, the second turn-back passage 66, and the third passage 67 in this other, and the cooling air is discharged to the outside via an opening formed in the top plate 59 of the blade tip portion 56. An inner wall of the airfoil portion 41 is convection-cooled with cooling air flowing through the first cooling air passage 61 and the second cooling air passage 62.
In addition, regarding the airfoil portion 41, a plurality of cooling holes 68 are provided in a blade trailing edge portion 52b on the trailing edge 52 side. The plurality of cooling holes 68 are arranged at predetermined intervals in the blade height direction Dh. Each of the plurality of cooling holes 68 communicates with the third passage 67 at one end 102 (refer to
The platform 42 is provided with a first cooling passage 72 that is on the suction side blade surface 53 side of the airfoil portion 41 and a second cooling passage 73 that is on the pressure side blade surface 54 side. In the axial direction Da, the first cooling passage 72 and the second cooling passage 73 extend from a leading edge portion 74 to a trailing edge portion 75 of the platform 42 along the upper surface 71 of the platform 42. An upstream end of the first cooling passage 72 in the cooling air flow direction communicates with the second cooling air passage 62 of the airfoil portion 41, and a downstream end thereof in the cooling air flow direction is open at a trailing edge portion end surface 75a. An upstream end of the second cooling passage 73 in the cooling air flow direction communicates with the first cooling air passage 61 of the airfoil portion 41, and a downstream end thereof in the cooling air flow direction is open at the trailing edge portion end surface 75a. The first cooling passage 72 and the second cooling passage 73 take in a portion of cooling air from the first cooling air passage 61 and the second cooling air passage 62 of the airfoil portion 41 so that a suction side end portion 44 and a pressure side end portion 45 of the platform 42 are convection-cooled. An upstream end to which the first cooling passage 72 is connected may be the first cooling air passage 61, and an upstream end to which the second cooling passage 73 is connected may be the second cooling air passage 62.
As shown in
In addition, as shown in
The first fillet portion 81 is provided closer to the trailing edge portion 75 of the platform 42 than a position X, at which a distance and a width between the suction side blade surface 53 of the airfoil portion 41 and the suction side end portion 44 of the platform 42 are smallest, while being on the suction side blade surface 53 side of the airfoil portion 41. The first fillet portion 81 is provided closer to the trailing edge portion 75 than a throat portion 110, which is formed between the airfoil portions 41 of the rotor blades 28 that are adjacent to each other in the circumferential direction Dc and which will be described later. A fillet width W1 of the first fillet portion 81 is set to be larger than a fillet width W of other regions of the fillet portion 80 excluding the first fillet portion 81. Here, the throat portion refers to a position where a minimum flow path width in a flow direction of the combustion gas FG between the rotor blades 28 that are adjacent to each other in the circumferential direction Dc is determined. Note that a tip of the fillet portion 80 in a direction along the fillet width W of the fillet portion 80, which is formed on the upper surface 71 of the platform 42, forms a lower outer edge 80b, and a tip of the fillet portion 80 which is formed in the blade height direction Dh along the blade surface 57 forms an upper outer edge 80a. Here, the fillet width W is a length or distance between the connecting portion 76, at which the airfoil portion 41 and the upper surface 71 of the platform 42 are bonded to each other, and the lower outer edge 80b of the fillet portion 80. A fillet height H is a length or height between the connecting portion 76, at which the airfoil portion 41 and the upper surface 71 of the platform 42 are bonded to each other, and the upper outer edge 80a of the fillet portion 80.
Here, a positional relationship between the throat portion 110 and the first fillet portion 81 will be described with reference to
The second fillet portion 82 is provided closer to the trailing edge 52 than the first fillet portion 81. The second fillet portion 82 is formed on the trailing edge end surface 52a of the airfoil portion 41, is formed on the blade base end portion 55 side to be adjacent to the plurality of cooling holes 68 (refer to
The third fillet portion 83 is provided to extend from the leading edge 51 to the first fillet portion 81 on the suction side blade surface 53 side and is provided to extend from the leading edge 51 to a third fillet change portion 86, which will be described later, along the pressure side blade surface 54 with the leading edge 51 of the airfoil portion 41 being interposed.
As shown in
As shown in
As shown in
As shown in
In addition, as shown in
As shown in
The fillet change portions 87 include the first fillet change portion 84, the second fillet change portion 85, and the third fillet change portion 86. The first fillet change portion 84 is formed between the first end portion 81a and the third end portion 83a disposed closer to the leading edge 51 than the first end portion 81a and is provided in a region A11 along the suction side blade surface 53. At the first fillet change portion 84, the fillet width W becomes smaller toward the third end portion 83a from the first end portion 81a, and the fillet height H is maintained constant. That is, in a region extending from the first fillet portion 81 to the third end portion 83a of the third fillet portion 83 with the first fillet change portion 84 interposed therebetween, the fillet width W becomes smaller, but the fillet height H is maintained constant.
The second fillet change portion 85 is formed between the second end portion 81b and the second fillet portion 82 and is provided in a region A12 along the suction side blade surface 53. At the second fillet change portion 85, the fillet width W and the fillet height H become smaller toward the second fillet portion 82 from the second end portion 81b. The third fillet change portion 86 is formed between the fourth end portion 83b and the second fillet portion 82 and is provided in a region A13 along the pressure side blade surface 54. At the third fillet change portion 86, the fillet height H becomes smaller toward the second fillet portion 82 from the fourth end portion 83b, and the fillet width W is maintained constant.
In addition, as shown in
Here, the reason why the shape of the fillet portion 80 depends on the position of the fillet portion 80 along the blade surface 57 of the airfoil portion 41 described above will be described below.
First, a cooling structure on the trailing edge 52 side of the airfoil portion 41, which influences the shape of the fillet portion 80, will be described. As described above, the second cooling air passage 62 formed in the airfoil portion 41 forms a meandering passage composed of the first passage 63, the first turn-back passage 64, the second passage 65, the second turn-back passage 66, and the third passage 67. Therefore, the cooling air flowing through the second cooling air passage 62 is overheated when flowing in the cooling air passage 60, and the temperature of the cooling air flowing through the final passage 70 becomes high. Accordingly, the metal temperature of the blade wall 58 on the trailing edge 52 side, which forms the final passage 70, tends to become high. Meanwhile, a stress caused by a centrifugal force or the like is generated at the fillet portion 80 at which the airfoil portion 41 and the platform 42 are connected to each other. Therefore, a high thermal stress tends to be generated at the fillet portion 80 on the trailing edge 52 side, and some cooling means or thermal stress suppressing means needs to be provided in some cases.
The first fillet portion 81 is formed on the suction side blade surface 53 side of the airfoil portion 41. In a suction side region of the trailing edge portion 75 of the platform 42, which is surrounded by the suction side blade surface 53 of the airfoil portion 41, the suction side end portion 44 of the platform 42, and the trailing edge portion end surface 75a and is on the downstream side in the axial direction, the first cooling passage 72 described above is arranged merely from the leading edge 51 to the trailing edge 52 along the suction side end portion 44. Therefore, the suction side region of the trailing edge portion 75 of the platform 42 which is on the downstream side in the axial direction is in a state of not being cooled except for a region in which the first cooling passage 72 is disposed.
As described above, regarding the final passage 70 (third passage 67) of the second cooling air passage 62 of the airfoil portion 41, generation of a thermal stress generated on the blade base end portion 55 side of the airfoil portion 41 due to interaction between overheating caused by cooling air and a centrifugal force or the like and generation of a thermal stress caused by a thermal elongation difference due to the presence of a non-cooling region of the platform 42 overlap with each other, and thus a higher thermal stress than the other regions of the fillet portion 80 tends to be generated at the first fillet portion 81, which is in the vicinity of a region that is on the suction side blade surface 53 side of the airfoil portion 41 and is on the downstream side in the axial direction, along the upper surface 71 of the platform 42.
As shown in
As shown in
The third fillet portion 83 is formed on the suction side blade surface 53 side and on the pressure side blade surface 54 with the leading edge 51 of the airfoil portion 41 interposed therebetween. As shown in
Note that at all of the region A1 of the first fillet portion 81, the region A2 of the second fillet portion 82, and the region A3 of the third fillet portion 83, there is no change in fillet height H and fillet width W and the fillet height H and the fillet width W are maintained constant. However, the fillet change portions 87 that connect each fillet portion 80 and are disposed at intermediate positions are formed to smoothly connect each fillet portion 80 with the fillet height H or the fillet width W being gradually changed. A sudden change in fillet shape at each connection point (first end portion 81a, second end portion 81b, third end portion 83a, and fourth end portion 83b) is not desirable from the viewpoint of aerodynamic performance and stress concentration.
Note that the turbine blade of the present invention is not limited to the rotor blade 28 configured as described above.
As shown in
In the airfoil portion 41, a cooling air passage 90 is provided. The cooling air passage 90 includes a first cooling air passage 91 and a second cooling air passage 92. The first cooling air passage 91 is provided along the blade height direction Dh on the leading edge 51 side of the airfoil portion 41 and is open at the top plate 59 on the blade tip portion 56 side. In the first cooling air passage 91, cooling air supplied to the blade root portion 43 side flows along the leading edge 51 in one direction, and the cooling air is discharged into the combustion gas FG on the outside via an opening formed in the top plate 59 on the blade tip portion 56 side. Similarly to the rotor blade 28 described in the first embodiment, the second cooling air passage 92 is formed as a meandering passage (serpentine passage) inside the airfoil portion 41 and is provided on the trailing edge 52 side while being adjacent to the first cooling air passage 91. The second cooling air passage 92 includes a first passage 93, a first turn-back passage (not shown), a second passage 94, a second turn-back passage (not shown), a third passage 95, a third turn-back passage (not shown), a fourth passage 96, a fourth turn-back passage (not shown), and a fifth passage 97. The first passage 93, the second passage 94, the third passage 95, the fourth passage 96, and the fifth passage 97 are provided along the blade height direction Dh, and a portion of the fifth passage 97 that is on the blade tip portion 56 side is connected to the opening formed in the top plate 59. In the second cooling air passage 92, cooling air supplied to the blade root portion 43 side flows through the first passage 93, the first turn-back passage, the second passage 94, the second turn-back passage, the third passage 95, the third turn-back passage, the fourth passage 96, the fourth turn-back passage, and the fifth passage 97 in this order, and the cooling air is discharged to the outside via an opening formed in the top plate 59 of the blade tip portion 56. The fifth passage 97 also functions as the final passage 70 of the second cooling air passage 92.
In addition, regarding the rotor blade 28A, the fillet portion 80 is provided around the entire periphery of the blade surface 57 of the airfoil portion 41 so that stress concentration on the connecting portion 76 between the airfoil portion 41 and the platform 42 is prevented. Similarly to the rotor blade 28 described in the first embodiment, the fillet portion 80 includes the first fillet portion 81, the second fillet portion 82, and the third fillet portion 83. In addition, as fillet change portions, the first fillet change portion 84, the second fillet change portion 85, and the third fillet change portion 86 are provided. Since the configurations of the fillet portion 80 and the fillet change portions 87 are the same as the configurations in the first embodiment described above, the description thereof will be omitted.
As described above, the turbine blade of the first embodiment includes the airfoil portion 41 that internally includes the cooling air passage 60, the platform (blade base end portion) 42 that is provided at the blade base end portion 55 of the airfoil portion 41 in the blade height direction Dh, and the fillet portion 80 that is provided around the entire periphery of the blade surface 57 at the connecting portion 76 between the airfoil portion 41 and the platform 42. The fillet portion 80 includes the first fillet portion 81 that is provided closer to the trailing edge 52 than the position X, at which a distance and an interval between the suction side blade surface 53 of the airfoil portion 41 and the suction side end portion 44 of the platform 42 are smallest, while being on the suction side blade surface 53 side of the airfoil portion 41 and of which the fillet width W is larger than the fillet width W of other regions of the fillet portion 80.
Therefore, at a region on the fillet portion 80 that is on the downstream side in the axial direction Da while being on the trailing edge 52 side and on the suction side blade surface 53 side of the platform 42, a thermal stress higher than other regions is likely to be generated. Since the first fillet portion 81 which is larger than the fillet portion 80 in fillet width W is provided at the region, a thermal stress at the fillet portion 80 can be reduced. In addition, the first fillet portion 81 which is on the trailing edge 52 side while being on the suction side blade surface 53 side of the platform 42 is disposed downstream of the throat portion 110 in the axial direction Da in comparison with the third fillet portion 83 on the leading edge 51 side, and thus the influence of the fillet shape on the aerodynamic performance is small. Therefore, for the first fillet portion 81, a fillet larger than the third fillet portion 83 in fillet width W can be selected.
As described above, in the case of the turbine blade of the first embodiment, the first fillet portion 81 is provided to be closer to the trailing edge 52 than the throat portion 110 which is formed between the airfoil portions 41 that are adjacent to each other. As a result, it is possible to suppress a decrease in aerodynamic performance even if the fillet width W is large, while reducing a thermal stress at the fillet portion 80.
In the case of the turbine blade of the first embodiment, the aspect ratio of the fillet height H to the fillet width W of the first fillet portion 81 is smaller than the aspect ratios of the other fillet portions. Therefore, the fillet width W of the first fillet portion 81 is larger than those of the other fillet portions, and thus it is possible to reduce generation of a thermal stress caused due to a thermal elongation difference at the fillet portion 80.
In the case of the turbine blade of the first embodiment, the first fillet portion 81 is a region at which the aspect ratio is maintained constant along the blade surface 57 of the fillet portion 80. Therefore, it is possible to reduce a thermal stress in a predetermined region (region A1) along the blade surface 57 of the fillet portion 80.
In the case of the turbine blade of the first embodiment, the aspect ratio of the first fillet portion 81 is 1.0. Therefore, a thermal stress at the first fillet portion 81 can be reduced.
In the case of the turbine blade of the first embodiment, the first fillet portion 81 includes the first end portion 81a that is provided on the leading edge 51 side of the airfoil portion 41 along the blade surface 57 of the fillet portion 80 and the second end portion 81b that is provided on the trailing edge 52 side of the airfoil portion 41 along the blade surface 57 of the fillet portion 80. The first end portion 81a and the second end portion 81b of the first fillet portion 81 are connected to the fillet change portions 84 and 85 at which the fillet width W or the fillet height H changes along the blade surface 57 of the fillet portion 80 in the other regions. Therefore, since the first fillet portion 81 and the other fillet portions 80 (second fillet portion 82 and third fillet portion 83) are connected to each other via the fillet change portions 84 and 85 at which the fillet width W or the fillet height H changes, the fillet portion 80 that is smoothly connected to a connecting portion between the airfoil portion 41 and the platform 42 is provided, and thus it is possible to suppress a decrease in aerodynamic performance and to suppress stress concentration.
In the case of the turbine blade of the first embodiment, the plurality of cooling holes 68 arranged at predetermined intervals in the blade height direction Dh of the blade trailing edge portion 52b on the trailing edge 52 side are disposed in the airfoil portion 41. One end of each cooling hole 68 communicates with the cooling air passage 60, and the other end thereof is open at the trailing edge end surface 52a of the trailing edge 52. The fillet portion 80 includes the second fillet portion 82 of which the fillet height H is set to be smaller than the fillet height H of the other fillet portion 80. The second fillet portion 82 is provided on the trailing edge end surface 52a to be closer to the platform 42 and more adjacent to the platform 42 in the blade height direction Dh than the cooling holes 68. Therefore, since the fillet height H of the second fillet portion 82 is smaller than the fillet height H of the other fillet portion 80, the fillet portion 80 of the blade trailing edge portion 52b including the second fillet portion 82 and a region of the platform 42 that is on the downstream side in the axial direction while being on the trailing edge 52 side can be efficiently cooled by means of cooling air flowing through the cooling holes 68, and a thermal stress at the fillet portion 80 of the blade trailing edge portion 52b including the second fillet portion 82 can be reduced.
In the case of the turbine blade of the first embodiment, regarding the fillet portion 80, the suction side blade surface 53 side extends from the leading edge 51 of the airfoil portion 41 to the second fillet portion 82 via the third fillet portion 83, the first fillet change portion 84, the first fillet portion 81, and the second fillet change portion 85. The pressure side blade surface 54 side extends to the second fillet portion 82 via the third fillet portion 83 and the third fillet change portion 86. Therefore, the fillet portion 80 having an appropriate shape can be provided around the entire periphery of the connecting portion between the airfoil portion 41 and the platform 42.
In the case of the turbine blade of the first embodiment, the aspect ratio of the fillet height H to the fillet width W of the third fillet portion 83 is maintained constant along the blade surface 57 of the fillet portion 80. Therefore, it is possible to reduce a thermal stress in a predetermined region in the blade surface 57 of the fillet portion 80 while suppressing a decrease in aerodynamic performance.
In the case of the turbine blade of the first embodiment, the first fillet change portion 84 is provided between the first end portion 81a and the third end portion 83a. At the first fillet change portion 84, the fillet width W becomes smaller toward the third end portion 83a from the first end portion 81a, and the fillet height H is maintained constant. In this case, the shape of the first fillet change portion 84 is an oval shape of which the aspect ratio exceeds 1.0. Therefore, since the first fillet portion 81 and the third fillet portion 83 can be smoothly connected to each other by means of the first fillet change portion 84 and the fillet width W can be made smaller than that of the first fillet portion 81, it is possible to suppress a decrease in aerodynamic performance and to suppress stress concentration.
In the case of the turbine blade of the first embodiment, the second fillet change portion 85 is provided between the second end portion 81b and the second fillet portion 82. At the second fillet change portion 85, the fillet width W and the fillet height H become smaller toward the second fillet portion 82 from the second end portion 81b. Note that at the second fillet change portion 85, a rate at which the fillet width W is changed is larger than a rate at which the fillet height H is changed. In this case, the shape of the second fillet change portion 85 is an oval shape of which the aspect ratio exceeds 1.0. Therefore, since the first fillet portion 81 and the second fillet portion 82 can be smoothly connected to each other by means of the second fillet change portion 85 and the fillet width W can be made smaller than that of the first fillet portion 81, it is possible to suppress a decrease in aerodynamic performance and to suppress stress concentration.
In the case of the turbine blade of the first embodiment, the third fillet change portion 86 is provided between the fourth end portion 83b and the second fillet portion 82. At the third fillet change portion 86, the fillet height H becomes smaller toward the second fillet portion 82 from the fourth end portion 83b, and the fillet width W is maintained constant. In this case, the shape of the third fillet change portion 86 is an oval shape of which the aspect ratio exceeds 1.0. Therefore, the second fillet portion 82 and the third fillet portion 83 can be smoothly connected to each other by means of the third fillet change portion 86, and it is possible to suppress a decrease in aerodynamic performance and to suppress stress concentration by making the fillet height H small and making the positions of the cooling holes 68 close to the upper surface 71 of the platform 42.
In the case of the turbine blade of the first embodiment, the first fillet portion 81 is provided in the blade height direction Dh along the blade wall 58 of the third passage 67, which is the final passage 70 on a most downstream side in the cooling air flow direction in the cooling air passage 60. Therefore, the first fillet portion 81 can be effectively cooled by means of cooling air flowing through the third passage 67 in the cooling air passage 60.
In the case of the turbine blade of the first embodiment, the second cooling air passage 62 as a meandering passage is provided in the airfoil portion, the first fillet portion 81 is provided along the passage cross-section of the third passage 67 that extends in the chord direction, and the length of the region A1 of the first fillet portion 81 falls within the range of the length of the third passage 67 in the chord direction, the third passage 67 being the final passage 70 on the most downstream side in the cooling air flow direction in the second cooling air passage 62. Therefore, since the length of the third passage 67 in the chord direction is larger than the length of the region A1 of the first fillet portion 81, convection cooling is performed by means of cooling air flowing through the third passage 67, and the first fillet portion 81 can be appropriately cooled.
In the case of the turbine blade of the first embodiment, the first cooling passage 72 and the second cooling passage 73 extending from the leading edge portion 74 to the trailing edge portion 75 of the platform 42 are provided on the pressure side blade surface 54 side and the suction side blade surface 53 side of the airfoil portion 41, and portions of the first cooling passage 72 and the second cooling passage 73 on an upstream side in the cooling air flow direction communicate with the cooling air passage 60. Therefore, it is possible to efficiently cool the platform 42 by supplying a portion of cooling air supplied to the airfoil portion 41 to the first cooling passage 72 and the second cooling passage 73 disposed in the platform 42 and convection-cooling the platform 42.
In the case of the turbine blade of the first embodiment, the turbine blade is applied to the rotor blade 28. Therefore, it is possible to suppress a decrease in performance of the rotor blade 28 and to reduce a thermal stress at the fillet portion 80.
In addition, the gas turbine of the first embodiment includes the compressor 11, the combustor 12 that mixes compressed air compressed by the compressor 11 and fuel with each other and that performs combustion, and the turbine 13 that includes the rotor blades 28 as turbine blades and that obtains rotational power by means of the combustion gas FG generated by the combustor 12. Therefore, it is possible to suppress a decrease in performance of the turbine 13 and to reduce a thermal stress at the fillet portion 80.
In the second embodiment, similarly to the rotor blade 28 in the first embodiment described above, a rotor blade 28B includes the airfoil portion 41, the platform 42, and the blade root portion 43 (refer to
In addition, regarding the rotor blade 28B, the fillet portion 80 is provided around the entire periphery of the blade surface 57 of the airfoil portion 41 so that stress concentration on the connecting portion 76 between the airfoil portion 41 and the platform 42 is prevented. Similarly to the rotor blade 28 described in the first embodiment, the fillet portion 80 includes the first fillet portion 81, the second fillet portion 82, and the third fillet portion 83. In addition, as fillet change portions, the first fillet change portion 84, the second fillet change portion 85, and the third fillet change portion 86 are provided. Since the configurations of the fillet portion 80 and the fillet change portions are the same as the configurations in the first embodiment described above, the description thereof will be omitted.
Regarding the airfoil portion 41, the plurality of cooling holes 68 are provided in the blade trailing edge portion 52b on the trailing edge 52 side. The plurality of cooling holes 68 are arranged at predetermined intervals in the blade height direction Dh, one end of each cooling hole 68 communicates with the third passage 67 in the second cooling air passage 62, and the other end of each cooling hole 68 is open at the trailing edge end surface 52a of the trailing edge 52. In addition, at positions on the trailing edge end surface 52a of the airfoil portion 41 that are close to the platform 42 side, the cooling holes 68 are disposed at positions on an outer side in the blade height direction Dh that are adjacent to the upper outer edge 80a of the second fillet portion 82. As will be described later, the plurality of cooling holes 68 include a plurality of end portion cooling holes 101 of which the opening density is higher than the opening density of the plurality of other cooling holes 68.
As shown in
The opening density of the end portion cooling holes 101 in the blade height direction Dh is higher than that of the cooling holes 68 which are positioned closer to the blade tip portion 56 (refer to
As shown in
The recessed groove portion 111 extends to the suction side end portion 44 side from the pressure side end portion 45 side of the platform 42. The leading edge side end portion 112 of the recessed groove portion 111 is formed from the pressure side end portion 45 side to the suction side end portion 44 side of the platform 42 and is formed to be close to the trailing edge portion end surface 75a of the platform 42. That is, the leading edge side end portion 112 of the recessed groove portion 111, which is on the leading edge 51 side of the platform 42, is positioned between an end portion (one end 102) on the trailing edge 52 side of the final passage 70 (that is, third passage 67), which is on the most downstream side in the cooling air flow direction in the second cooling air passage 62 of the airfoil portion 41, and the trailing edge end surface 52a of the airfoil portion 41 as seen in a plan view (
Providing the recessed groove portion 111 at the trailing edge portion 75 of the platform 42 results in a decrease in rigidity of the trailing edge portion 75 of the platform, which has significance for reducing rigidity. It is possible to reduce a thermal stress at the trailing edge portion 75 of the platform and the fillet portion 80 by reducing the rigidity of the trailing edge portion 75 of the platform.
In the vicinity of the position of the trailing edge portion 75 in a width direction (circumferential direction Dc) of the platform 42, the leading edge side end portion 112 of the recessed groove portion 111 is provided to be inclined with respect to the width direction (circumferential direction Dc) of the platform 42 such that the leading edge side end portion 112 becomes closer to the leading edge 51 side toward the pressure side end portion 45 side from the suction side end portion 44 side. Therefore, the recessed groove portion 111 can be formed to have a sufficient depth in a direction to the leading edge 51 side in the vicinity of the connecting portion 76 (second fillet portion 82) between the trailing edge end surface 52a of the airfoil portion 41 where stress reduction is highly necessary and the platform 42, and thus it is possible to reduce a thermal stress at the fillet portion 80 including the second fillet portion 82 and the trailing edge portion 75 of the platform 42.
Note that in the embodiments described above, the description has been made with the turbine blade of the present invention applied to the rotor blade 28. However, the turbine blade may also be applied to the stator vane 27.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2019-053739 | Mar 2019 | JP | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2020/008670 | 3/2/2020 | WO |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2020/189237 | 9/24/2020 | WO | A |
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| Number | Date | Country | |
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| 20220154581 A1 | May 2022 | US |
