Patent Application
20150125280
The present invention relates to a rotor of a rotary machine and a rotary machine.
Priority is claimed on Japanese Patent Application No. 2011-74206, filed Mar. 30, 2011, the content of which is incorporated herein by reference.
Recently, in steam-power generation using a steam turbine, electricity is usually generated at 600° C. or less. In many cases, main components such as a turbine rotor and a rotor vane constituting the steam turbine and used under these conditions are formed of, for example, high Cr-steel (high-chrome steel and ferritic heat resistant steel) such as 12Cr steel.
Incidentally, in recent years, there has been a demand for generating electricity at conditions in which the steam is 700° C. or more in order to meet requirements for a reduction in the discharge of CO2 and further improvements in thermal efficiency. However, due to the insufficient high-temperature strength of the main components, it is not desirable to use ferritic heat resistant steel under these conditions.
Therefore, in order to ensure a higher high-temperature strength, a Ni-based alloy (nickel base alloy) is used for the main components. However, when the Ni-based alloy is used, there are disadvantages in that the main components may not be easily made in large sizes and the cost may increase.
In Patent Document 1 below, in order to both allow an increase in size and suppress cost of the turbine rotor, a turbine rotor is formed by joining a first member formed of a Ni-based alloy to a second member formed of high Cr-steel by welding. Then, the strength of the joint portion is ensured by using a Ni-based alloy with a specific composition.
Incidentally, the Ni-based alloy generally has a low thermal conductivity and a large linear expansion coefficient. For this reason, during the start-up of the steam turbine, the outside of the turbine rotor (the Ni-based alloy) increases in temperature and thermally expands so as to be larger than the inside thereof, thereby causing a problem in that excessive stress is generated inside the turbine rotor.
On the other hand, when the turbine rotor is warmed up slowly so that the temperature thereof gradually increases as a whole, the generation of thermal stress may be suppressed. However, there is a problem in that rapid start-up of the steam turbine is inhibited.
The invention is made in view of such circumstances, and it is an object of the invention to allow rapid start-up of the rotary machine and to suppress the thermal stress generated in the rotor.
In order to accomplish the above-described object, the invention adopts the following means.
That is, according to the invention, there is provided a rotor of a rotary machine of which an outer peripheral portion extending along an axis is surrounded by a stator and in which a hydraulic fluid circulates in a passageway defined between the stator and the outer peripheral portion, the rotor including: a plurality of rotor members that are joined to each other in the axial direction in which the axis extends, wherein a first rotor member which is included in the plurality of rotor members and which is located in a hydraulic fluid injection portion of the passageway is formed of an Ni-based alloy, and the inside of the first rotor member is hollow throughout the entire length in the axial direction.
In this way, since the inside of the first rotor member which is formed of the Ni-based alloy is hollow throughout its entire length in the axial direction, the thermal capacity of the first rotor member becomes smaller than that of the case where the inside is solid. Accordingly, when the rotary machine is rapidly started up, a difference in the temperature which is generated between the outside and the inside of the inner portion of the first rotor member is suppressed, so that the temperature of the first rotor member increases as a whole. Accordingly, it is possible to suppress the thermal stress which is generated inside the first rotor member. Thus, the rotary machine may be rapidly started up and the thermal stress generated in the rotor may be suppressed.
Further, the plurality of rotor members may include a second rotor member that is adjacent to the first rotor member in the axial direction and is formed of high Cr-steel.
In this way, since the plurality of rotor members include the second rotor member which is adjacent to the first rotor member in the axial direction and is formed of high Cr-steel, it is possible to suppress an increase in the cost of the rotor compared to the case where the entire rotor is formed of the Ni-based alloy. Furthermore, since part of the rotor is formed of high Cr-steel which is more easily molded than Ni-based alloy, the rotor may be easily manufactured.
Further, the first rotor member may be formed so that the thickness of the center portion in the axial direction is greater than or equal to the thickness of the end portion in the axial direction and the value of the ratio between the inner diameter and the outer diameter at the center portion in the axial direction is greater than or equal to ½.
In this way, it is possible to further suppress a difference in the temperature which is generated between the outside and the inside of the inner portion of the first rotor member, and further suppress the thermal stress generated inside the first rotor member. Further, it is possible to ensure the strength necessary for the first rotor member.
Further, a plurality of the hydraulic fluid injection portions may be formed, and the inner diameters of at least two or more of the plurality of hydraulic fluid injection portions may be different from each other in the first rotor member.
In this way, it is possible to adjust the temperature distribution for each hydraulic fluid injection portion.
Further, the inner diameters of a plurality of portions in the axial direction may be different from each other in the first rotor member.
In this way, it is possible to adjust the temperature distribution in a plurality of portions in the axial direction.
Further, in at least part of the first rotor member in the axial direction, a hole may be formed in a tapered shaped so that the inner diameter gradually decreases toward one end side of the rotor member from the other end side.
In this way, it is possible to adjust the temperature of the first rotor member in the axial direction.
Further, the Ni-based alloy may include 0.15 wt % or less of C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 15 wt % of Cr, 17 to 25 wt % of including one or two or more of Mo, W, and Re; Mo+(W+Re)/2, 0.2 to 2 wt % of Al, 0.5 to 4.5 wt % of Ti, 10 wt % or less of Fe, including one or two of 0.02 wt % or less of B and 0.2 wt % or less of Zr, 2.5 to 7.0 at % of Al+Ti, and the remainder of Ni and inevitable impurities.
Further, the Ni-based alloy may include 0.15 wt % or less of C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 17 to 26 wt % of Mo, 17 to 27 wt % of Mo+(W+Re)/2, 0.1 to 2 wt % of Al, 0.1 to 2 wt % of Ti, 10 wt % or less of Fe, 0.02 wt % or less of B, 0.2 wt % or less of Zr, 1 to 5.5 at % of Al+Ti, and the remainder of Ni and inevitable impurities.
Further, the Ni-based alloy may include 0.15 wt % or less of C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 17 to 27 wt % of including one or two or more of Mo, W, and Re; Mo+(W+Re)/2, 0.1 to 2 wt % of Al, 0.1 to 2 wt % of Ti, 10 wt % or less of Fe, 0.001 to 0.02 wt % of B, 0.001 to 0.2 wt % of Zr, 1.5 wt % or less of Nb+Ta/2, 5 wt % or less of Co, and the remainder of Ni and inevitable impurities.
Further, the Ni-based alloy may include 0.15 wt % or less of C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 10 wt % or less of W, 5 to 20 wt % of including one or two or more of Mo, W, and Re; Mo+(W+Re)/2, 0.1 to 2.5 wt % of Al, 0.10 to 0.95 wt % of Ti, 4 wt % or less of Fe, 0.001 to 0.02 wt % of B, 0.001 to 0.2 wt % of Zr, 1.5 wt % or less of Nb+Ta/2, 2.0 to 6.5 at % of Al+Ti+Nb+Ta, and the remainder of Ni and inevitable impurities.
Further, the Ni-based alloy may include 0.005 to 0.1 wt % of C, 8 to 15 wt % of Cr, 5 to 20 wt % of W, 1 to 7 wt % of Mo, 0.5 to 1.0 wt % of Al, 1.0 to 2.5 wt % of Ti, and the remainder of Ni and inevitable impurities.
Further, the Ni-based alloy may include 0.005 to 0.15 wt % of C, 8 to 22 wt % of Cr, 5 to 30 wt % of Co, 5 to 20 wt % of W, 1 to 9 wt % of Mo, 0.1 to 2.0 wt % of Al, 0.3 to 2.5 wt % of Ti, 0.015 wt % or less of B, 0.01 wt % or less of Mg, and the remainder of Ni and inevitable impurities.
That is, when the first rotor member is formed of the Ni-based alloy with the abovementioned compositions, it is possible to ensure the strength of the joint portion with the second rotor member formed of the high Cr-steel.
Furthermore, according to the invention, there is provided a rotary machine including: a rotor of one of the above-described rotary machines and a stator which surrounds the rotor and in which a hydraulic fluid is injected into a passageway defined between the stator and the rotor.
In this way, even when the Ni-based alloy is used under conditions in which the hydraulic fluid is comparatively hot, the rotary machine may be rapidly started up and the thermal stress generated in the rotor may be suppressed. Accordingly, satisfactory running performance may be obtained and damage to the rotor may be prevented. Then, since the hydraulic fluid is set to a comparatively high temperature, requirements for a reduction in the discharge of CO2 or further improvements in thermal efficiency may be sufficiently handled.
According to the rotor of the rotary machine of the invention, it is possible to rapidly start up the rotary machine and suppress the thermal stress generated in the rotor.
Further, according to the rotary machine of the invention, it is possible to obtain a satisfactory running performance and prevent damage to the rotor.
Hereinafter, embodiments of the invention will be described by referring to the drawings.
As shown in
The high and intermediate pressure turbine T1 includes a rotor 10 and a stator 50.
The rotor 10 includes a shaft body 11 which is rotatably supported and a plurality of rotor vane rows 12 (12A and 12B) which are formed in the shaft body 11.
The shaft body 11 penetrates the stator 50 in the turbine axial direction, and both ends in the turbine axial direction are supported by bearing units 91 and 92 which are disposed outside the stator 50. The other configurations of the shaft body 11 will be described in detail.
The plurality of rotor vane rows 12 (12A and 12B) are formed in a manner such that a plurality of rotor vanes restrained in the outer periphery of the shaft body 11 is arranged in the turbine circumferential direction. The plurality of rotor vane rows 12A is arranged in the high pressure turbine 1A, and the plurality of rotor vane rows 12B is arranged in the intermediate pressure turbine 1B.
The stator 50 includes an external casing 60, an internal casing 70 (70A and 70B), and a stator vane row 52 (52A and 52B).
The external casing 60 includes an interior wall 60a which defines an internal space 61 at the outside and a partition wall 60b which divides the internal space 61 into two parts in the turbine axial direction. The partition wall 60b is disposed substantially at the center of the internal space 61 in the turbine axial direction, and divides the internal space 61 into a high pressure turbine chamber 61A which is disposed at one side in the turbine axial direction and an intermediate pressure turbine chamber 61B which is disposed at the other side in the turbine axial direction.
In the high pressure turbine 1A, the interior wall 60a of the external casing 60 is provided with a plurality of injection nozzles 63A which is formed at the other side in the turbine axial direction and a discharging nozzle 64A which is formed at one side in the turbine axial direction. Further, in the intermediate pressure turbine 1B, the interior wall 60a is provided with a plurality of injection nozzles 63B which is formed at one side in the turbine axial direction and a discharging nozzle 64B which is formed at the other side in the turbine axial direction.
A rotor 10 is inserted through the external casing 60, and both ends of the rotor 10 (the shaft body 11) protrude from both ends of the interior wall 60a in the turbine axial direction.
Furthermore, the gaps which are formed between the interior wall 60a and both ends of the rotor 10 are sealed by sealing units 93A and 93B. Further, the gaps which are formed between the partition wall 60b and the center of the rotor 10 are sealed by sealing members 94A and 94B.
The internal casing 70 (70A and 70B) is a cylindrical member of which both ends are opened, and which includes a stator vane holding ring 71 which holds the stator vane row 52 (52A and 52B) in the inner peripheral portion.
The internal casing 70A is disposed in the high pressure turbine 1A, and the internal casing 70B is disposed in the intermediate pressure turbine 1B. The internal casings 70A and 70B are restrained by the inner wall of the interior wall 60a and the partition wall 60b of the external casing 60. The internal casings 70A and 70B are inserted through the rotor 10 so as to surround the outer periphery 10a of the rotor 10, and an annular passageway (a passageway) 3 (3A and 3B) extends in the turbine axial direction between the outer periphery 10a of the rotor 10 and the stator vane holding ring 71.
The other end opening portion at the other side of the internal casing 70A in the turbine axial direction abuts on the partition wall 60b so as to be blocked and the gap between the other end opening portion and the rotor 10 is sealed by the seal member 94A.
The other end opening portion of the internal casing 70A defines a manifold (a hydraulic fluid injection portion) 3a which extends in the turbine circumferential direction and communicates with the annular passageway 3 between the sealing member 94A and the outer periphery of the shaft body 11. The manifold 3a communicates with a connecting pipe 80A which is inserted into each injection nozzle 63A and is air-tightly connected to the internal casing 70A, and high pressure steam (hydraulic fluid) S1 (about 700° C.) is supplied from a boiler B through the connecting pipe 80A. The manifold 3a introduces the high pressure steam S1 into the annular passageway 3 and the high pressure steam S1 supplied to the high pressure turbine 1A first contacts the rotor 10 in the manifold 3a. That is, in the running high pressure turbine 1A, the portion where the manifold 3a is exposed is the hottest among the portions of the rotor 10.
Furthermore, one end opening portion of the internal casing 70A is opened toward one side in the turbine axial direction.
The opening portions of both ends of the internal casing 70B are each opened in the turbine axial direction. A flange portion 70a, which extends in a flange shape from the outer peripheral portion of the internal casing 70, is formed at one side of the internal casing 70B in the turbine axial direction, and the flange portion 70a is connected to the inner wall of the interior wall 60a, so that a manifold 3b is defined around the one end opening portion. Intermediate pressure steam (hydraulic fluid) S2 (about 700° C.) is supplied from the boiler B to the manifold 3b through a connecting pipe 80B which is inserted to each injection nozzle 63B.
On the other hand, in the internal casing 70B, one side of the shaft body 11 in the turbine axial direction is covered by the sealing member 94B. That is, the intermediate pressure steam S2 which is supplied to the manifold 3b is introduced into the annular passageway 3B along the sealing member 94B, and the exposure portion (the hydraulic fluid injection portion) 3c from the sealing member 94B in the rotor 10 becomes a portion where the intermediate pressure steam S2 first contacts. That is, in the running intermediate pressure turbine 1B, the exposure portion 3c from the sealing member 94B becomes the hottest among the portions of the rotor 10.
The plurality of stator vane rows 52 (52A and 52B) is formed in a manner such that the stator vanes restrained in the stator vane holding ring 71 of the internal casing 70 (70A and 70B) are arranged in the turbine circumferential direction.
The stator vane row 52A and the rotor vane row 12A are alternately arranged from the other side in the turbine axial direction toward one side in the annular passageway 3A of the high pressure turbine 1A. The stator vane row 52B and the rotor vane row 12B are alternately arranged from one side in the turbine axial direction toward the other side in the annular passageway 3B of the intermediate pressure turbine 1B.
As shown in
The rotor member (the second rotor member) 20 includes a small diameter portion 21 which is formed with a relatively small diameter and a large diameter portion 22 which is formed with a relatively large diameter.
In the large diameter portion 22, one end portion 20a at one side in the turbine axial direction is depressed in a dish shape, and the other end portion 20b is connected to, for example, the end portion of the rotor RL of the low pressure turbine (see
The rotor member (the second rotor member) 40 includes a small diameter portion 41 which is formed with a relatively small diameter and a large diameter portion 42 which is formed with a relatively large diameter.
In the rotor member 40, the other end portion 40b at the other side of the rotor member 40 in the turbine axial direction is depressed in a dish shape, and one end portion 40a is connected to, for example, the end portion of the rotor RVH of the ultra high pressure turbine (see
The rotor members 20 and 40 are formed of, for example, high Cr-steel and are formed by, for example, forging. As the high Cr-steel, for example, the compositions of 1-1 and 1-2 shown in Table 1 below may be preferably used. In the high Cr-steel with such a composition, the average linear expansion coefficient from room temperature to 700° C. is approximately from 11.2×10−6/° C. to 12.4×10−6° C.
Furthermore, high Cr-steel with a composition other than that in Table 1 may also be used.
10~12.5%
In the rotor member (the first rotor member) 30, both end portions (the joint end portion) 30a and 30b in the turbine axial direction are depressed in a dish shape.
The rotor member 30 is formed of a Ni-based alloy, and has comparatively low thermal conductivity and a high linear expansion coefficient. As the Ni-based alloy, for example, the compositions of 2-1, 2-2, 2-3, 2-4, 2-5, and 2-6 shown in Table 2 below may be preferably used. In the Ni-based alloys with such compositions, the average linear expansion coefficient from room temperature to 700° C. is approximately from 12.4×10−6/° C. to 14.5×106° C., and is suppressed so as to be lower than that of Ni-based alloys with other compositions.
Furthermore, Ni-based alloy with a composition other those in than Table 2 may also be used.
One end portion 30a of the rotor member 30 is joined to the other end portion 40b of the rotor member 40 by welding in an abutting state. Further, the other end portion 30b of the rotor member 30 is joined to one end portion 20a of the rotor member 20 by welding in an abutting state.
With regard to the joint portions of both end portions 30a and 30b of the rotor member 30 in the turbine axial direction, it is desirable that the thickness d be set as small as possible on the condition that the necessary strength is ensured while maintaining the running state of the high and intermediate pressure turbine T1.
As shown in
The thickness of the rotor member 30 is formed so that the center portion in the turbine axial direction is greater than or equal to each thickness d of both end portions in the turbine axial direction and the value of the ratio of the inner diameter D1 with respect to the outer diameter D2 at the center portion in the turbine axial direction is greater than or equal to ½.
Subsequently, operation of the high and intermediate pressure turbine T1 with the above-described configuration will be described with reference to the drawings.
First, when the high and intermediate pressure turbine T1 is started up, the high pressure steam S1 flows into the high pressure turbine 1A and the intermediate pressure steam S2 flows into the intermediate pressure turbine 1B.
As shown in
On the other hand, for example, in the intermediate pressure turbine 1B, the intermediate pressure steam S2 which is discharged from the high pressure turbine 1A and is reheated by the boiler B is supplied to the manifold 3b through the connecting pipe 80B.
Then, the intermediate pressure steam S2 is introduced from the manifold 3b into the annular passageway 3B along the sealing member 94B, and sequentially flows through the rotor vane row 12B and the stator vane row 52B in the annular passageway 3B, thereby applying rotational force to the rotor 10. The intermediate pressure steam S2 which passes through the annular passageway 3B is discharged from the intermediate pressure turbine 1B through the discharge nozzle 64B and sent to the boiler (not shown).
At this time, since the inside of the rotor member 30 in the rotor 10 is formed so as to be hollow so that the thermal capacity is small, it is difficult for a difference in temperature between the outside and the inside in the inner portion (more specifically, the thick portion) of the rotor member 30 to arise.
In other words, since the rotor member 30 is formed so as to be hollow, the distance of the thermal transmission path from the outer peripheral end of the rotor member 30 to the inner peripheral end thereof is shorter than that of the case where the rotor member 30 is solid, and the heat which is transmitted from the high pressure steam S1 to the outer peripheral end of the rotor member 30 is rapidly conducted (reaches) to the inner peripheral end of the rotor member 30. For this reason, the temperature gradient in the turbine radial direction inside the rotor member 30 is gentle, and the temperatures of the outside and the inside of the inner portion of the rotor member 30 are equal to each other.
A difference in the thermal growth between the outside and the inside of the rotor member 30 decreases in proportion to a difference in the temperature which is generated outside and inside of the inner portion of the rotor member 30. For this reason, it is possible to largely suppress the thermal stress which is generated inside the rotor member 30.
When this state is continued, the temperature of the entire rotor member 30 increases to the running temperature of the high and intermediate pressure turbine T1.
Then, the high and intermediate pressure turbine T1 changes from the start-up state to the normal state. After changing to the normal state, the rotor member 30 rotates after the temperature becomes constant.
As described above, according to the high and intermediate pressure turbine T1, since the inside of the rotor member 30 which is formed of the Ni-based alloy is formed so as to be hollow throughout the entire length in the turbine axial direction, the thermal capacity of the rotor member 30 becomes smaller than that of the case where the inside is solid. Accordingly, when the high and intermediate pressure turbine T1 is rapidly started up, a difference in the temperature which is generated between the outside and the inside of the inner portion of the rotor member 30 is suppressed, and the temperature of the rotor member 30 increases as a whole. Accordingly, it is possible to suppress the thermal stress which is generated inside the rotor member 30. Thus, the high and intermediate pressure turbine T1 may be rapidly started up and the thermal stress generated in the rotor 10 may be suppressed.
Further, since the shaft body 11 is adjacent to the rotor member 30 in the turbine axial direction and the rotor members 20 and 40 which are formed of high Cr-steel are provided, it is possible to suppress the cost of the rotor 10 compared to the case where the entire shaft body 11 is formed of Ni-based alloy. Furthermore, since part of the shaft body 11 is formed of high Cr-steel which is more easily molded than the Ni-based alloy, the rotor 10 may be easily manufactured.
Further, since the rotor member 30 is formed of Ni-based alloy with the composition shown in Table 2, the average linear expansion coefficient from room temperature to 700° C. becomes smaller than that of Ni-based alloy with other compositions. Accordingly, since thermal growth hardly occurs in the rotor member 30 compared to Ni-based alloys with other compositions, it is possible to further suppress the thermal stress which is generated inside the rotor member 30.
Further, since the rotor members 20 and 40 are formed of high Cr-steel with the composition shown in Table 1 and the rotor member 30 is formed of Ni-based alloy with the composition shown in Table 2, a difference in the linear expansion coefficient is decreased. Accordingly, it is possible to ensure the strength of the joint portions of the rotor members 20 and 40 and the rotor member 30.
Further, the thickness of the rotor member 30 is formed so as to be greater than or equal to ½ of the value of the ratio of the inner diameter D1 with respect to the outer diameter D2 at the center portion in the turbine axial direction. Thus, it is possible to further suppress a difference in the temperature which is generated between the outside and the inside of the inner portion of the rotor member 30, and further suppress the thermal stress which is generated inside the rotor member 30. Further, the thickness of the rotor member 30 is formed so as to be greater than or equal to ½ of the value of the ratio of the inner diameter D1 with respect to the outer diameter D2 at the center portion in the turbine axial direction. Thus, it is possible to further suppress a difference in the temperature which is generated between the outside and the inside of the inner portion of the rotor member 30, and further suppress the thermal stress which is generated inside the rotor member 30. Further, the thickness of the rotor member 30 is formed so as to be greater than or equal to thickness d of both end portions in the turbine axial direction at the center portion in the turbine axial direction. Thus, it is possible to ensure the strength which is necessary for the rotor member 30.
Furthermore, since the high and intermediate pressure turbine T1 according to the invention includes the rotor 10, even when Ni-based alloy is used at steam conditions of 700° C. or more, the high and intermediate pressure turbine T1 may be rapidly started up and the thermal stress generated in the rotor 10 is suppressed. Accordingly, satisfactory running performance may be obtained, and the breakage of the rotor 10 may be prevented. Then, since the steam S1 and the steam S2 are set to a comparatively high temperature (about 700° C.), a demand for the reduction in the discharge amount of CO2 or the further improvement in the thermal coefficient may be sufficiently handled.
Hereinafter, a second embodiment of the invention will be described by referring to the drawings. Furthermore, in the following description and the drawings used for the description, the same reference numerals will be given to the same components as the components described above, and the repetitive descriptions thereof will not be repeated.
Compared to the configuration in which the shaft body 11 of the first embodiment includes the rotor member 30 which is integrally formed with the shaft body, as shown in
The rotor members 32A and 32B are formed of Ni-based alloy as in the case of the rotor member 30, and both end portions (joint end portions) 32a, 32b, 32c, and 32d are each depressed in a dish shape in the turbine axial direction. The inside of each of the rotor members 32A and 32B is formed so as to be hollow.
One end portion 32a of the rotor member 32A is joined to the other end portion 40b of the rotor member 40 (added since it is not shown) by welding in an abutting state.
One end portion 32d of the rotor member 32B is joined to one end portion 20a of the rotor member 20 (added since it is not shown) by welding in an abutting state.
Further, the other end portion 32b of the rotor member 32A and the other end portion 32c of the rotor member 32B are joined to each other by welding (common welding) in an abutting state.
In the rotor member 32A, a hole 31A with a constant inner diameter D1 extends in the turbine axial direction on the axis P. In the rotor member 32B, a hole 31B with a constant inner diameter D3 (≠the inner diameter D1) extends in the turbine axial direction on the axis P.
That is, the rotor members 32A and 32B are formed so as to have different inner diameters.
According to the high and intermediate pressure turbine T2, it is possible to obtain the main advantage of the first embodiment. Further, since the inner diameters (D1≠D3) are different from each other in the manifold 3a and the exposure portion 3c shown in
Furthermore, it is possible to obtain the main advantage of the first embodiment even when the rotor members 32A and 32B have the same inner diameter.
Hereinafter, a third embodiment of the invention will be described by referring to the drawings. Furthermore, in the following description and the drawings used for the description, the same reference numerals will be given to the same components as the components described above, and the repetitive descriptions thereof will not be repeated.
Compared to the configuration in which the shaft body 11A of the second embodiment includes the rotor member 32B with the hole 31B, as shown in
The rotor member 33 is formed of an Ni-based alloy, where one end portion (the joint end portion) 33a is joined to the other end portion 32b of the rotor member 32A by welding in an abutting state and the other end portion 33b is joined to one end portion 20a of the rotor member 20 (added since it is not shown in the drawings) by welding in an abutting state.
According to the high and intermediate pressure turbine T3, it is possible to obtain the main advantages of the first embodiment and the second embodiment in the rotor member 32A. Further, since the inside of the rotor member 33 is solid, it is possible to improve the rigidity of the rotor member 33 in the intermediate pressure turbine 1B.
Furthermore, the inside of the rotor member 33 may be hollow (as in the case of the rotor member 32B), and the inside of the rotor member 32A may be formed so as to be solid.
Hereinafter, a fourth embodiment of the invention will be described by referring to the drawings. Furthermore, in the following description and the drawings used for the description, the same reference numerals will be given to the same components as the components described above, and the repetitive descriptions thereof will not be repeated.
Compared to the configuration in which the shaft body 11A of the second embodiment includes the rotor members 32A and 32B having the holes 31A and 31B with constant inner diameters D1 and D3, as shown in
The hole 35A of the rotor member 34A is formed in, for example, a tapered shape in which the inner diameter gradually decreases toward one end side of the rotor member 34A from the other end side in the turbine axial direction.
The hole 35B of the rotor member 34B is formed in, for example, a tapered shape in which the inner diameter gradually decreases from one end side of the rotor member toward the other end side in the turbine axial direction.
According to the high and intermediate pressure turbine T4, it is possible to obtain the main advantages of the first embodiment and the second embodiment. Further, since the inner diameters (the holes 35A and 35B) of the rotor members 34A and 34B are different at each portion in the turbine axial direction, it is possible to adjust the temperatures of the rotor members 34A and 34B (the high pressure turbine 1A and the intermediate pressure turbine 1B) in the turbine axial direction.
Furthermore, in the embodiment, the hole 35A is formed in a tapered shape in which the inner diameter gradually decreases from one end side of the rotor member 34A toward the other end side in the turbine axial direction, but may be formed so that the inner diameter gradually decreases toward one end side of the rotor member 34A from the other end side in the turbine axial direction. Further, a part of the hole 35A may have a portion with a constant inner diameter. Further, a portion may be formed in which the inner diameter of the hole 35A increases and then decreases in the turbine axial direction. The same applies to the hole 35B.
Further, as in this embodiment, the inner diameter of each hole of the first embodiment to the third embodiment may be changed in the turbine axial direction.
Furthermore, the operation sequences or all shapes, combinations, and the like of the components shown in the above-described embodiments are examples, and may be modified into various forms based on the design requirements and the like in the scope without departing from the spirit of the invention.
For example, in the above-described embodiments, each end portion of the rotor members 20, 30, 40, 32A, 32B, 33, 34A, and 34B in the turbine axial direction is formed in a dish shape, but may be depressed in other shapes in the turbine axial direction. Further, the end portion may be formed in a flat shape without being depressed in the turbine axial direction.
Further, in the above-described embodiments, a case has been described in which the invention is applied to the high and intermediate pressure turbines T1 to T4, but the invention may be applied to the turbine of another pressure range. Further, the invention may be applied to a rotary machine other than a turbine.
According to the rotor of the rotary machine of the invention, it is possible to rapidly start-up the rotary machine and suppress the thermal stress generated in the rotor.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2011-074206 | Mar 2011 | JP | national |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 13357876 | Jan 2012 | US |
| Child | 14592057 | US |
