Patent Grant
12091988
The present disclosure relates to a gas turbine blade.
This application claims the right of priority based on Japanese Patent Application No. 2020-174743 filed with the Japan Patent Office on Oct. 16, 2020, the content of which is incorporated herein by reference.
A gas turbine blade has a plate-like platform part and a blade main body part extending from an upper surface of the platform part. A cooling passage through which compressed air as a cooling medium flows is formed inside the platform part. An end portion of the cooling passage is open on the upper surface or a side end surface of the platform part or on a surface of the blade main body part.
As a specific example of such a cooling passage, the technique described in Japanese Unexamined Patent Application Publication No. 2012-102726 (hereinafter, JP '726) is known. In the gas turbine blade according to JP '726, opening end portions of the cooling passages are uniformly formed on a pressure surface (pressure surface) side of a blade main body part.
Here, in a partial region of a platform away from the blade main body part (specifically, a part of a region outside a blade chord connecting a leading edge and a trailing edge of the blade main body part) in the upper surface of the platform, the thickness thereof is thin as compared to a region in the vicinity of the blade main body part, so that thermal stress due to a high-temperature combustion gas easily occurs. There is a concern that forming many opening end portions of the cooling passages in such a region may lead to a decrease in the fatigue strength of the platform. That is, there is still room for improvement in the technique described in JP '726.
The present disclosure has been made to solve the above problem, and has an object to provide a gas turbine blade having further improved fatigue strength.
In order to solve the above problem, a gas turbine blade according to the present disclosure includes: a platform part having a cooling passage formed inside; and a blade main body part protruding from an upper surface of the platform part, wherein a plurality of first ejection ports that eject a gas supplied from the cooling passage are formed in a chord inside region of the upper surface, which is located on a blade main body part side with respect to a blade chord connecting a leading edge and a trailing edge of the blade main body part, a plurality of second ejection ports that eject the gas supplied from the cooling passage are formed in a chord outside region of the upper surface, which is located on a side opposite the chord inside region with the blade chord as a reference, the chord outside region has a chord outside leading edge region that is located on a leading edge side, and a chord outside trailing edge region that is located on a trailing edge side, and the plurality of second ejection ports are formed more on the chord outside leading edge region than on the chord outside trailing edge region.
According to the present disclosure, it is possible to provide a gas turbine blade having further improved fatigue strength.
(Configuration of Gas Turbine)
Hereinafter, a gas turbine 10 and a gas turbine blade (a rotor blade 50) according to an embodiment of the present disclosure will be described with reference to
The gas turbine 10 of the present embodiment includes a compressor 20 that compresses air, a combustor 30 that burns fuel F in the air compressed by the compressor 20 to generate a combustion gas G, and a turbine 40 that is driven by the combustion gas G.
The compressor 20 has a compressor rotor 21 that rotates with an axis Ar as the center, a compressor casing 25 that rotatably covers the compressor rotor 21, and a plurality of stator blade stages 26. The turbine 40 has a turbine rotor 41 that rotates with the axis Ar as the center, a turbine casing 45 that rotatably covers the turbine rotor 41, and a plurality of stator blade stages 46.
The compressor rotor 21 and the turbine rotor 41 are located on the same axis Ar and are connected to each other to form a gas turbine rotor 11. For example, a rotor of a generator is connected to the gas turbine rotor 11. Further, the compressor casing 25 and the turbine casing 45 are connected to each other with an intermediate casing 16 interposed therebetween to form a gas turbine casing 15. The combustor 30 is disposed in the intermediate casing 16. Hereinafter, a direction in which the axis Ar extends is referred to as an axial direction Da, a circumferential direction around the axis Ar is simply referred to as a circumferential direction Dc, and a direction perpendicular to the axis Ar is referred to as a radial direction Dr. Further, a compressor 20 side with respect to the turbine 40 in the axial direction Da is referred to as an upstream side, and a side opposite thereto is referred to as a downstream side.
The compressor rotor 21 has a rotor shaft 22 extending in the axial direction Da along the axis Ar, and a plurality of rotor blade stages 23 mounted to the rotor shaft 22. The plurality of rotor blade stages 23 are arranged in the axial direction Da. Each of the rotor blade stages 23 is composed of a plurality of rotor blades 24 arranged in the circumferential direction Dc. The stator blade stage 26 is disposed on the downstream side of each of the plurality of rotor blade stages 23. Each stator blade stage 26 is provided inside the compressor casing 25. Each of the stator blade stages 26 is composed of a plurality of stator blades 27 arranged in the circumferential direction Dc.
The turbine rotor 41 has a rotor shaft 42 extending in the axial direction Da along the axis Ar, and a plurality of rotor blade stages 43 mounted to the rotor shaft 42. The plurality of rotor blade stages 43 are arranged in the axial direction Da. Each of the rotor blade stages 43 is composed of a plurality of rotor blades 50 arranged in the circumferential direction Dc. The stator blade stage 46 is disposed on the upstream side of each of the plurality of rotor blade stages 43. Each stator blade stage 46 is provided inside the turbine casing 45. Each of the stator blade stages 46 is composed of a plurality of stator blades 47 arranged in the circumferential direction Dc. An annular space in a region between an outer periphery side of the rotor shaft 42 and an inner periphery side of the turbine casing 45 and in which the stator blade 47 and the rotor blade 50 are disposed in the axial direction Da forms a combustion gas flow path through which the combustion gas G from the combustor 30 flows.
(Composition of Rotor Blade)
As shown in
The blade body 51 has a leading edge 52 that is an end portion on the upstream side in the axial direction, and a trailing edge 53 that is an end portion on the downstream side in the axial direction. The blade body 51 has a smooth convex shape toward one side in the circumferential direction Dc. A convex surface of surfaces facing the circumferential direction Dc in a surface of the blade body 51 forms a suction side surface (=suction surface) 55, and a concave surface forms a pressure side surface (=pressure surface) 54. For the convenience of the following description, a pressure side (=pressure surface side) of the blade body 51 in the circumferential direction Dc is defined as a pressure side in the circumferential direction, and a suction side (=suction surface side) of the blade body 51 is defined as a suction side in the circumferential direction. Further, the upstream side in the axial direction Da may be called a front side, and the downstream side in the axial direction Da may be called a rear side.
The blade root 59 has a Christmas tree shape in which a wide width portion and a narrow width portion are alternately repeated toward an inner side in the radial direction in a cross-sectional shape perpendicular to a blade chord of the blade body 51. A blade root groove into which the blade root 59 is fitted is formed in the rotor shaft 42 described above.
The platform 61 is formed with a front end surface 62 that is an end surface on the upstream side in the axial direction, a rear end surface 63 that is an end surface on the downstream side in the axial direction, a pressure side end surface 64 that is an end surface on the pressure side in the circumferential direction, and a suction side end surface 65 that is an end surface on the suction side in the circumferential direction. In a case of being viewed from the radial direction Dr, the platform 61 has a parallelogram shape, as shown in
(Composition of Blade Air Passage)
As shown in
The blade body 51 is formed with a blade front end passage 56 which extends from a first blade air passage 71a on a most upstream side among the plurality of blade air passages 71 to the upstream side and is open at the leading edge 52 of the blade body 51. Some of the cooling air that has flowed into the first blade air passage 71a flows out from the plurality of blade front end passages 56 of the blade body 51 into the combustion gas flow path. Further, some of the cooling air flows out from a seventh blade air passage 71b on a most downstream side of the blade air passages 71 into the combustion gas flow path. The leading edge 52 and trailing edge 53 of the blade body 51 are cooled by the cooling air.
(Configurations of Pressure Surface-Side Passage and First Ejection Port)
As shown in
Here, in the gas pass surface 66, a region on a blade body 51 side with respect to a blade chord Ch with a line (the blade chord Ch) connecting the leading edge 52 and the trailing edge 53 of the blade body 51 as a reference is defined as a chord inside region A. Further, in the gas pass surface 66, a region that is located on a side opposite the chord inside region A with the blade chord Ch as a reference is defined as a chord outside region B. At this time, all the first ejection ports 75a described above are located within the chord inside region A. That is, all the first ejection ports 75a are disposed closer to the blade body 51 than the blade chord Ch is.
Further, the chord outside region B is divided into a chord outside leading edge region B1 that is located on a leading edge 52 side with respect to a dividing line D and a chord outside trailing edge region B2 that is located on a trailing edge 53 side, by the dividing line D perpendicular to the blade chord Ch. The position of the dividing line D is appropriately set within a range of 50% or less from the leading edge 52 in a case where the length of the blade chord Ch is set to 100%. An opening direction of the first ejection port 75a described above is determined so as to eject a gas from the chord inside region A toward the chord outside trailing edge region B2.
(Configurations of Leading Edge-Side Passage, Branch Passage, and Second Ejection Port)
A leading edge-side passage 76 is connected to the first blade air passage 71a that is located closest to the leading edge 52 side, among the blade air passages 71. The leading edge-side passage 76 extends from the first blade air passage 71a toward the chord outside leading edge region B1 described above. Further, a plurality of (as an example, three) branch passages 77 are connected to the middle of the leading edge-side passage 76. The leading edge-side passage 76 and the branch passage 77 serve as a part of the cooling passage.
Each branch passage 77 extends in a direction along the blade chord Ch from the leading edge-side passage 76. One end of the branch passage 77 is a second ejection port 77a that is open on the chord outside leading edge region B1. As an example, the positions of the second ejection ports 77a in the direction of the blade chord Ch are the same and are within a range of 25% or less of the length of the blade chord Ch from the leading edge 52 in the blade chord Ch. An opening direction of each second ejection port 77a is determined so as to eject a gas toward the chord outside trailing edge region B2. In other words, compared to the first ejection port 75a, the second ejection port 77a is open in the direction along the blade chord Ch.
It is possible to adopt a configuration in which the second ejection port 77a is formed in the chord outside trailing edge region B2 as well. However, in this case, a configuration is made such that the number of the second ejection ports 77a that are formed in the chord outside leading edge region B1 is greater than the number of the second ejection ports 77a that are formed in the chord outside trailing edge region B2. That is, it is desirable that the second ejection ports 77a are disposed to be localized on a chord outside leading edge region B1 side. Further, the number of the second ejection ports 77a is smaller than the number of the first ejection ports 75a.
(Configurations of Side Passage and Third Ejection Port)
As shown in
(Operation and Effects)
Here, in a partial region of the platform 61 away from the blade body 51 (specifically, a part of a region outside the blade chord connecting the leading edge and the trailing edge of the blade main body part) in the gas pass surface 66, the thickness thereof is thinner as compared with the region close to the blade body 51, so that thermal stress due to a high-temperature combustion gas easily occurs. There is a concern that forming many opening end portions of the cooling passages in such a region may lead to a decrease in the fatigue strength of the platform 61.
There is also a case where in the vicinity of the pressure side end surface 64 that is in contact with the suction side end surface 65 of the adjacent platform 61, the vicinity of the end surface is partially thickened in order to enhance the sealing performance between the platforms 61. However, since a part of the region outside the blade chord Ch is thin as compared to the region in the vicinity of the blade body 51, if many opening end portions of the cooling passages are formed in the chord outside region, it leads to a decrease in the fatigue strength of the platform 61.
In the present embodiment, by forming the first ejection port 75a in the region close to the blade body 51, it is possible to minimize the influence on the strength. Further, in the chord outside region B, the number of the second ejection ports 77a is greater in the chord outside leading edge region B1 than in the chord outside trailing edge region B2. In other words, in the chord outside region B, the second ejection ports 77a are disposed to be localized on the leading edge 52 side as compared with the first ejection port 75a in the chord inside region A. In this way, it is possible to minimize the influence on the structural strength as compared with, for example, a case where the second ejection ports 77a are evenly formed in the chord outside region B.
Further, according to the above configuration, the number of the second ejection ports 77a in the chord outside region B is smaller than the number of the first ejection ports 75a in the chord inside region A. Since the chord outside region B is thinner than the region close to the blade body 51, by reducing the number of the second ejection ports 77a, it is possible to further minimize the influence on the structural strength.
In addition, according to the above configuration, the second ejection port 77a formed in the chord outside leading edge region B1 ejects a gas toward the chord outside trailing edge region B2. In this way, it is possible to efficiently cool the surface of the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small.
Further, according to the above configuration, the first ejection port 75a ejects a gas toward the chord outside trailing edge region B2. In this way, it is possible to efficiently cool the surface of the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small.
Further, according to the above configuration, the second ejection port 77a is open in the direction along the blade chord Ch as compared with the first ejection port 75a. Therefore, it is possible to actively perform film cooling on the chord outside trailing edge region B2 by means of the gas that is supplied from the second ejection port 77a.
Furthermore, according to the above configuration, the plurality of first ejection ports 75a are arranged along the shape of the pressure side surface 54 of the blade main body part. That is, the first ejection ports 75a are arranged along the shape of the portion where the platform 61 and the blade body 51 are in contact with each other. Since such a portion has a higher strength than the region close to the blade chord, it is possible to further minimize the influence of the formation of the first ejection port 75a on the strength.
Further, according to the above configuration, the side passages 72 communicating with the third ejection ports 72a are formed more on the chord outside trailing edge region B2 side than on the chord outside leading edge region B1 side. Therefore, the convective cooling effect of the side passages 72 passing through the inside can be applied to the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small and the cooling effect is difficult to achieve. As a result, it becomes possible to more efficiently cool the chord outside trailing edge region B2.
The embodiment of the present disclosure has been described above. Various changes and modifications can be made to the above configuration within a scope which does not depart from the gist of the present disclosure. For example, the number or shape of the blade air passages 71 described in the above embodiment is an example, and can be appropriately changed according to design or specifications. Further, it is also possible to form other cooling passages communicating with the blade air passages 71.
The gas turbine blade (the rotor blade 50) described in each embodiment is understood as follows, for example.
(1) A gas turbine blade (the rotor blade 50) according to a first aspect includes: the platform part (the platform 61) having the cooling passage (the blade air passage 71) formed inside; and the blade main body part (the blade body 51) protruding from the upper surface (the gas pass surface 66) of the platform part, in which the plurality of first ejection ports 75a that eject the gas supplied from the cooling passage are formed in the chord inside region A of the upper surface, which is located on the blade main body part side with respect to the blade chord Ch connecting the leading edge 52 and the trailing edge 53 of the blade main body part, the plurality of second ejection ports 77a that eject the gas supplied from the cooling passage are formed in the chord outside region B of the upper surface, which is located on the side opposite the chord inside region A with the blade chord Ch as a reference, the chord outside region B has the chord outside leading edge region B1 that is located on the leading edge 52 side, and the chord outside trailing edge region B2 that is located on the trailing edge 53 side, and the plurality of second ejection ports 77a are formed more on the chord outside leading edge region B1 than on the chord outside trailing edge region B2.
Here, the chord inside region A, which is located closer to the blade main body side than the blade chord Ch is, is thicker than the chord outside region B, so that the chord inside region A has relatively high strength and is less affected by thermal stress. The first ejection port 75a is formed in such a region, so that it is possible to minimize the influence on the strength. Further, in the chord outside region B, the number of the second ejection ports 77a is greater in the chord outside leading edge region B1 than in the chord outside trailing edge region B2. In other words, in the chord outside region B, the second ejection ports 77a are disposed to be localized on the leading edge 52 side as compared with the first ejection port 75a in the chord inside region A. In this way, it is possible to minimize the influence on the structural strength as compared with, for example, a case where the second ejection ports 77a are evenly formed in the chord outside region B.
(2) In a gas turbine blade according to a second aspect, the number of the second ejection ports 77a may be smaller than the number of the first ejection ports 75a.
According to the above configuration, the number of the second ejection ports 77a in the chord outside region B is smaller than the number of the first ejection ports 75a in the chord inside region A. Since the chord outside region B is thinner than the region close to the blade body 51, by reducing the number of the second ejection ports 77a, it is possible to further minimize the influence on the structural strength.
(3) In a gas turbine blade according to a third aspect, the position of the second ejection port 77a may be within a range of 25% or less of the length of the blade chord Ch with the leading edge 52 in a direction along the blade chord Ch as a reference in the chord outside leading edge region B1.
According to the above configuration, the position of the second ejection port 77a is provided within the range of 25% or less of the length of the blade chord with the leading edge 52 as a reference with respect to the direction of the blade chord Ch in the chord outside leading edge region B1. In this way, it is possible to further minimize the influence on the structural strength.
(4) In a gas turbine blade according to a fourth aspect, the second ejection port 77a formed in the chord outside leading edge region B1 among the plurality of second ejection ports 77a may be configured to eject the gas toward the chord outside trailing edge region B2.
According to the above configuration, the second ejection ports 77a formed in the chord outside leading edge region B1 eject the gas toward the chord outside trailing edge region B2. In this way, it is possible to efficiently cool the surface of the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small.
(5) In a gas turbine blade according to a fifth aspect, the plurality of first ejection ports 75a may be configured to eject the gas toward the chord outside trailing edge region B2.
According to the above configuration, the first ejection ports 75a eject the gas toward the chord outside trailing edge region B2. In this way, it is possible to efficiently cool the surface of the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small.
(6) In a gas turbine blade according to a sixth aspect, compared to the first ejection port 75a, the second ejection port 77a may be open in a direction along the blade chord Ch.
According to the above configuration, compared with the first ejection port 75a, the second ejection port 77a is open in the direction along the blade chord Ch. Therefore, it is possible to actively perform film cooling on the chord outside trailing edge region B2 by means of the gas that is supplied from the second ejection port 77a.
(7) In a gas turbine blade according to a seventh aspect, the plurality of first ejection ports 75a may be arranged along the shape of the pressure surface (the pressure side surface 54) of the blade main body part.
According to the above configuration, the plurality of first ejection ports 75a are arranged along the shape of the pressure surface of the blade main body part. That is, the first ejection ports 75a are arranged along the shape of the portion where the platform part and the blade main body part are in contact with each other. Since such a portion has a high strength, it is possible to further minimize the influence of the formation of the first ejection port 75a on the strength.
(8) In a gas turbine blade according to an eighth aspect, the plurality of third ejection ports 72a for ejecting the gas supplied from the cooling passage may be formed in the side end surface (the pressure side end surface 64) of the platform part, and the cooling passages (the side passages 72) communicating with the plurality of third ejection ports 72a may be formed more on the chord outside trailing edge region B2 side than on the chord outside leading edge region B1 side.
According to the above configuration, the cooling passages 72 communicating with the third ejection ports 72a are formed more on the chord outside trailing edge region B2 side than on the chord outside leading edge region B1 side. Therefore, the convective cooling effect of the cooling passages (the side passages 72) passing through the inside can be applied to the chord outside trailing edge region B2 in which the number of the second ejection ports 77a is small and the cooling effect is difficult to achieve. As a result, it becomes possible to more efficiently cool the chord outside trailing edge region B2.
According to the present disclosure, it is possible to provide a gas turbine blade having further improved fatigue strength.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2020-174743 | Oct 2020 | JP | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2021/034568 | 9/21/2021 | WO |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2022/080094 | 4/21/2022 | WO | A |
| Number | Name | Date | Kind |
|---|---|---|---|
| 4946346 | Ito | Aug 1990 | A |
| 6071075 | Tomita | Jun 2000 | A |
| 20090202339 | Torii et al. | Aug 2009 | A1 |
| 20120107135 | Harris, Jr. | May 2012 | A1 |
| 20120263603 | Hada | Oct 2012 | A1 |
| 20160177751 | Otomo et al. | Jun 2016 | A1 |
| Number | Date | Country |
|---|---|---|
| 2610435 | Jul 2013 | EP |
| 2-11801 | Jan 1990 | JP |
| 8-144704 | Jun 1996 | JP |
| 2008-95697 | Apr 2008 | JP |
| 2008-202547 | Sep 2008 | JP |
| 2012-102726 | May 2012 | JP |
| 2016-11616 | Jan 2016 | JP |
| Entry |
|---|
| International Search Report issued Nov. 22, 2021 in International (PCT) Application No. PCT/JP2021/034568, with English translation. |
| International Written Opinion issued Nov. 22, 2021 in International (PCT) Application No. PCT/JP2021/034568, with English translation. |
| Number | Date | Country | |
|---|---|---|---|
| 20230340881 A1 | Oct 2023 | US |
