US20120251307A1 - Rotor of rotary machine and rotary machine - Google Patents

Rotor of rotary machine and rotary machine Download PDF

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Publication number
US20120251307A1
US20120251307A1 US13/357,876 US201213357876A US2012251307A1 US 20120251307 A1 US20120251307 A1 US 20120251307A1 US 201213357876 A US201213357876 A US 201213357876A US 2012251307 A1 US2012251307 A1 US 2012251307A1
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US
United States
Prior art keywords
rotor
rotary machine
less
stator
axial direction
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/357,876
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English (en)
Inventor
Shin Nishimoto
Yoshinori Tanaka
Takashi Nakano
Kenji Kawasaki
Ryuichi Yamamoto
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KAWASAKI, KENJI, NAKANO, TAKASHI, NISHIMOTO, SHIN, TANAKA, YOSHINORI, YAMAMOTO, RYUICHI
Publication of US20120251307A1 publication Critical patent/US20120251307A1/en
Priority to US14/592,057 priority Critical patent/US9657574B2/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/177—Ni - Si alloys

Definitions

  • the present invention relates to a rotor of a rotary machine and a rotary machine.
  • 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.
  • Ni-based alloy nickel base alloy
  • the main components may not be easily made in large sizes and the cost may increase.
  • 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.
  • 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.
  • 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.
  • the invention adopts the following means.
  • 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.
  • 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.
  • 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.
  • 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 1 ⁇ 2.
  • 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.
  • the inner diameters of a plurality of portions in the axial direction may be different from each other in the first rotor member.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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 CO 2 or further improvements in thermal efficiency may be sufficiently handled.
  • 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.
  • FIG. 1 is a cross-sectional view illustrating a schematic configuration of a high and intermediate pressure turbine T 1 according to a first embodiment of the invention, and a meridian cross-sectional view including the axis P of the high and intermediate pressure turbine T 1 .
  • FIG. 2 is an enlarged cross-sectional view illustrating a shaft body 11 according to an embodiment of the invention.
  • FIG. 3 is an enlarged cross-sectional view illustrating a shaft body 11 A in a high and intermediate pressure turbine T 2 according to a second embodiment of the invention.
  • FIG. 4 is an enlarged cross-sectional view illustrating a shaft body 11 B in a high and intermediate pressure turbine T 3 according to a third embodiment of the invention.
  • FIG. 5 is an enlarged cross-sectional view illustrating a shaft body 11 C in a high and intermediate pressure turbine T 4 according to a fourth embodiment of the invention.
  • FIG. 1 is a cross-sectional view illustrating a schematic configuration of a high and intermediate pressure turbine (a rotary machine) T 1 according to a first embodiment of the invention, and a meridian cross-sectional view including the axis P of the high and intermediate pressure turbine T 1 .
  • the extension direction of the axis P is referred to as the turbine axial direction (the axial direction)
  • the circumferential direction of the axis P is referred to as the turbine circumferential direction
  • the radial direction of the axis P is referred to as the turbine radial direction.
  • a high pressure turbine (a rotary machine) 1 A is installed at one side of the turbine axial direction
  • an intermediate pressure turbine (a rotary machine) 1 B is installed at the other side of the turbine axial direction.
  • the high and intermediate pressure turbine T 1 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 ( 12 A and 12 B) 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 .
  • bearing units 91 and 92 which are disposed outside the stator 50 .
  • the plurality of rotor vane rows 12 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 12 A is arranged in the high pressure turbine 1 A, and the plurality of rotor vane rows 12 B is arranged in the intermediate pressure turbine 1 B.
  • the stator 50 includes an external casing 60 , an internal casing 70 ( 70 A and 70 B), and a stator vane row 52 ( 52 A and 52 B).
  • the external casing 60 includes an interior wall 60 a which defines an internal space 61 at the outside and a partition wall 60 b which divides the internal space 61 into two parts in the turbine axial direction.
  • the partition wall 60 b 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 61 A which is disposed at one side in the turbine axial direction and an intermediate pressure turbine chamber 61 B which is disposed at the other side in the turbine axial direction.
  • the interior wall 60 a of the external casing 60 is provided with a plurality of injection nozzles 63 A which is formed at the other side in the turbine axial direction and a discharging nozzle 64 A which is formed at one side in the turbine axial direction.
  • the interior wall 60 a is provided with a plurality of injection nozzles 63 B which is formed at one side in the turbine axial direction and a discharging nozzle 64 B 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 60 a in the turbine axial direction.
  • the gaps which are formed between the interior wall 60 a and both ends of the rotor 10 are sealed by sealing units 93 A and 93 B. Further, the gaps which are formed between the partition wall 60 b and the center of the rotor 10 are sealed by sealing members 94 A and 94 B.
  • the internal casing 70 ( 70 A and 70 B) 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 ( 52 A and 52 B) in the inner peripheral portion.
  • the internal casing 70 A is disposed in the high pressure turbine 1 A, and the internal casing 70 B is disposed in the intermediate pressure turbine 1 B.
  • the internal casings 70 A and 70 B are restrained by the inner wall of the interior wall 60 a and the partition wall 60 b of the external casing 60 .
  • the internal casings 70 A and 70 B are inserted through the rotor 10 so as to surround the outer periphery 10 a of the rotor 10 , and an annular passageway (a passageway) 3 ( 3 A and 3 B) extends in the turbine axial direction between the outer periphery 10 a of the rotor 10 and the stator vane holding ring 71 .
  • the other end opening portion of the internal casing 70 A defines a manifold (a hydraulic fluid injection portion) 3 a which extends in the turbine circumferential direction and communicates with the annular passageway 3 between the sealing member 94 A and the outer periphery of the shaft body 11 .
  • the manifold 3 a communicates with a connecting pipe 80 A which is inserted into each injection nozzle 63 A and is air-tightly connected to the internal casing 70 A, and high pressure steam (hydraulic fluid) S 1 (about 700° C.) is supplied from a boiler B through the connecting pipe 80 A.
  • the manifold 3 a introduces the high pressure steam S 1 into the annular passageway 3 and the high pressure steam S 1 supplied to the high pressure turbine 1 A first contacts the rotor 10 in the manifold 3 a. That is, in the running high pressure turbine 1 A, the portion where the manifold 3 a is exposed is the hottest among the portions of the rotor 10 .
  • one end opening portion of the internal casing 70 A is opened toward one side in the turbine axial direction.
  • a flange portion 70 a 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 70 B in the turbine axial direction, and the flange portion 70 a is connected to the inner wall of the interior wall 60 a, so that a manifold 3 b is defined around the one end opening portion.
  • Intermediate pressure steam (hydraulic fluid) S 2 (about 700° C.) is supplied from the boiler B to the manifold 3 b through a connecting pipe 80 B which is inserted to each injection nozzle 63 B.
  • the sealing member 94 B On the other hand, in the internal casing 70 B, one side of the shaft body 11 in the turbine axial direction is covered by the sealing member 94 B. That is, the intermediate pressure steam S 2 which is supplied to the manifold 3 b is introduced into the annular passageway 3 B along the sealing member 94 B, and the exposure portion (the hydraulic fluid injection portion) 3 c from the sealing member 94 B in the rotor 10 becomes a portion where the intermediate pressure steam S 2 first contacts. That is, in the running intermediate pressure turbine 1 B, the exposure portion 3 c from the sealing member 94 B becomes the hottest among the portions of the rotor 10 .
  • the plurality of stator vane rows 52 is formed in a manner such that the stator vanes restrained in the stator vane holding ring 71 of the internal casing 70 ( 70 A and 70 B) are arranged in the turbine circumferential direction.
  • stator vane row 52 A and the rotor vane row 12 A are alternately arranged from the other side in the turbine axial direction toward one side in the annular passageway 3 A of the high pressure turbine 1 A.
  • the stator vane row 52 B and the rotor vane row 12 B are alternately arranged from one side in the turbine axial direction toward the other side in the annular passageway 3 B of the intermediate pressure turbine 1 B.
  • FIG. 2 is an enlarged cross-sectional view illustrating the shaft body 11 .
  • the shaft body 11 is formed by joining the rotor members 20 , 30 , and 40 to each other in the turbine axial direction. More specifically, the rotor members 20 , 30 , and 40 are joined to each other in the above-described order while each axis overlaps the axis P so as to be formed in a shaft shape as a whole.
  • 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.
  • one end portion 20 a at one side in the turbine axial direction is depressed in a dish shape, and the other end portion 20 b is connected to, for example, the end portion of the rotor R L of the low pressure turbine (see FIG. 1 ).
  • 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.
  • the other end portion 40 b at the other side of the rotor member 40 in the turbine axial direction is depressed in a dish shape, and one end portion 40 a is connected to, for example, the end portion of the rotor R VH of the ultra high pressure turbine (see FIG. 1 ).
  • the rotor members 20 and 40 are formed of, for example, high Cr-steel and are formed by, for example, forging.
  • high Cr-steel for example, the compositions of 1-1 and 1-2 shown in Table 1 below may be preferably used.
  • 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.
  • % in Table 1 indicates the weight %.
  • both end portions (the joint end portion) 30 a and 30 b 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.
  • 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.
  • the average linear expansion coefficient from room temperature to 700° C. is approximately from 12.4 ⁇ 10 ⁇ 6 /° C. to 14.5 ⁇ 10 ⁇ 6 ° C., and is suppressed so as to be lower than that of Ni-based alloys with other compositions.
  • Ni-based alloy with a composition other those in than Table 2 may also be used.
  • % in Table 2 indicates the weight %.
  • One end portion 30 a of the rotor member 30 is joined to the other end portion 40 b of the rotor member 40 by welding in an abutting state. Further, the other end portion 30 b of the rotor member 30 is joined to one end portion 20 a of the rotor member 20 by welding in an abutting state.
  • 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 T 1 .
  • the inside of the rotor member 30 is formed so as to be hollow. More specifically, a hole 31 with a constant inner diameter D 1 extends in the turbine axial direction on the axis P, and one end portion 30 a and the other end portion 30 b communicate with each other. That is, the thermal capacity of the rotor member 30 becomes smaller than that of the case where the rotor member 30 is solid (i.e., the case where the hole 31 is not formed).
  • 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 D 1 with respect to the outer diameter D 2 at the center portion in the turbine axial direction is greater than or equal to 1 ⁇ 2.
  • the high pressure steam S 1 flows into the high pressure turbine 1 A and the intermediate pressure steam S 2 flows into the intermediate pressure turbine 1 B.
  • the high pressure steam S 1 which passes through the ultra high pressure turbine (not shown) and is reheated by the boiler B is supplied to the manifold 3 a through the connecting pipe 80 A. Then, the high pressure steam S 1 is introduced into the annular passageway 3 A along the rotor member 30 , and sequentially flows through the rotor vane row 12 A and the stator vane row 52 A, thereby applying rotational force to the rotor 10 .
  • the high pressure steam S 1 which passes through the annular passageway 3 A is discharged from the high pressure turbine 1 A through the discharge nozzle 64 A and sent to the boiler B.
  • the intermediate pressure steam S 2 which is discharged from the high pressure turbine 1 A and is reheated by the boiler B is supplied to the manifold 3 b through the connecting pipe 80 B.
  • the intermediate pressure steam S 2 is introduced from the manifold 3 b into the annular passageway 3 B along the sealing member 94 B, and sequentially flows through the rotor vane row 12 B and the stator vane row 52 B in the annular passageway 3 B, thereby applying rotational force to the rotor 10 .
  • the intermediate pressure steam S 2 which passes through the annular passageway 3 B is discharged from the intermediate pressure turbine 1 B through the discharge nozzle 64 B and sent to the boiler (not shown).
  • 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.
  • 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 S 1 to the outer peripheral end of the rotor member 30 is rapidly conducted (reaches) to the inner peripheral end of the rotor member 30 .
  • 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 .
  • the high and intermediate pressure turbine T 1 changes from the start-up state to the normal state.
  • the rotor member 30 rotates after the temperature becomes constant.
  • 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 T 1 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 T 1 may be rapidly started up and the thermal stress generated in the rotor 10 may be suppressed.
  • 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.
  • 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 .
  • 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 .
  • the thickness of the rotor member 30 is formed so as to be greater than or equal to 1 ⁇ 2 of the value of the ratio of the inner diameter D 1 with respect to the outer diameter D 2 at the center portion in the turbine axial direction.
  • the thickness of the rotor member 30 is formed so as to be greater than or equal to 1 ⁇ 2 of the value of the ratio of the inner diameter D 1 with respect to the outer diameter D 2 at the center portion in the turbine axial direction.
  • 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 .
  • the high and intermediate pressure turbine T 1 since the high and intermediate pressure turbine T 1 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 T 1 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 S 1 and the steam S 2 are set to a comparatively high temperature (about 700° C.), a demand for the reduction in the discharge amount of CO 2 or the further improvement in the thermal coefficient may be sufficiently handled.
  • FIG. 3 is an enlarged cross-sectional view illustrating a shaft body 11 A in a high and intermediate pressure turbine (the rotary machine) T 2 according to the second embodiment of the invention.
  • the shaft body 11 A of the high and intermediate pressure turbine T 2 has a configuration in which rotor members (first rotor members) 32 A and 32 B are disposed at a position corresponding to the rotor member 30 .
  • the rotor members 32 A and 32 B are formed of Ni-based alloy as in the case of the rotor member 30 , and both end portions (joint end portions) 32 a, 32 b, 32 c, and 32 d are each depressed in a dish shape in the turbine axial direction.
  • the inside of each of the rotor members 32 A and 32 B is formed so as to be hollow.
  • One end portion 32 a of the rotor member 32 A is joined to the other end portion 40 b of the rotor member 40 (added since it is not shown) by welding in an abutting state.
  • One end portion 32 d of the rotor member 32 B is joined to one end portion 20 a of the rotor member 20 (added since it is not shown) by welding in an abutting state.
  • a hole 31 A with a constant inner diameter D 1 extends in the turbine axial direction on the axis P.
  • a hole 31 B with a constant inner diameter D 3 ( ⁇ the inner diameter D 1 ) extends in the turbine axial direction on the axis P.
  • the rotor members 32 A and 32 B are formed so as to have different inner diameters.
  • the high and intermediate pressure turbine T 2 it is possible to obtain the main advantage of the first embodiment. Further, since the inner diameters (D 1 ⁇ D 3 ) are different from each other in the manifold 3 a and the exposure portion 3 c shown in FIG. 1 , it is possible to adjust each temperature distribution of the manifold 3 a and the exposure portion 3 c (the high pressure turbine 1 A and the intermediate pressure turbine 1 B).
  • FIG. 4 is an enlarged cross-sectional view illustrating a shaft body 11 B in a high and intermediate pressure turbine (the rotary machine) T 3 according to the third embodiment of the invention.
  • a shaft body 11 B of the high and intermediate pressure turbine T 3 includes a solid rotor member 33 instead of the rotor member 32 B.
  • the rotor member 33 is formed of an Ni-based alloy, where one end portion (the joint end portion) 33 a is joined to the other end portion 32 b of the rotor member 32 A by welding in an abutting state and the other end portion 33 b is joined to one end portion 20 a of the rotor member 20 (added since it is not shown in the drawings) by welding in an abutting state.
  • the high and intermediate pressure turbine T 3 it is possible to obtain the main advantages of the first embodiment and the second embodiment in the rotor member 32 A. 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 1 B.
  • the inside of the rotor member 33 may be hollow (as in the case of the rotor member 32 B), and the inside of the rotor member 32 A may be formed so as to be solid.
  • FIG. 5 is an enlarged cross-sectional view illustrating a shaft body 11 C in a high and intermediate pressure turbine (the rotary machine) T 4 according to the fourth embodiment of the invention.
  • a shaft body 11 C of the high and intermediate pressure turbine T 4 includes rotor members (first rotor members) 34 A and 34 B in which the inner diameters of the holes 35 A and 35 B respectively formed therein are different at each portion in the turbine axial direction.
  • the hole 35 A of the rotor member 34 A is formed in, for example, a tapered shape in which the inner diameter gradually decreases toward one end side of the rotor member 34 A from the other end side in the turbine axial direction.
  • the hole 35 B of the rotor member 34 B 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.
  • the high and intermediate pressure turbine T 4 it is possible to obtain the main advantages of the first embodiment and the second embodiment. Further, since the inner diameters (the holes 35 A and 35 B) of the rotor members 34 A and 34 B are different at each portion in the turbine axial direction, it is possible to adjust the temperatures of the rotor members 34 A and 34 B (the high pressure turbine 1 A and the intermediate pressure turbine 1 B) in the turbine axial direction.
  • the hole 35 A is formed in a tapered shape in which the inner diameter gradually decreases from one end side of the rotor member 34 A 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 34 A from the other end side in the turbine axial direction. Further, a part of the hole 35 A may have a portion with a constant inner diameter. Further, a portion may be formed in which the inner diameter of the hole 35 A increases and then decreases in the turbine axial direction. The same applies to the hole 35 B.
  • each hole of the first embodiment to the third embodiment may be changed in the turbine axial direction.
  • each end portion of the rotor members 20 , 30 , 40 , 32 A, 32 B, 33 , 34 A, and 34 B 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.
  • the invention is applied to the high and intermediate pressure turbines T 1 to T 4 , 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.
  • 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.
  • T 1 , T 2 , T 3 , T 4 high and intermediate pressure turbine (rotary machine)

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/357,876 2011-03-30 2012-01-25 Rotor of rotary machine and rotary machine Abandoned US20120251307A1 (en)

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JP2011074206A JP2012207594A (ja) 2011-03-30 2011-03-30 回転機械のロータ及び回転機械

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WO2012132526A1 (fr) 2012-10-04
EP2910734A1 (fr) 2015-08-26
US20150125280A1 (en) 2015-05-07
CN104791017A (zh) 2015-07-22
EP2692985A4 (fr) 2014-11-05
KR101557616B1 (ko) 2015-10-19
US9657574B2 (en) 2017-05-23
KR101557562B1 (ko) 2015-10-06
EP2910734B1 (fr) 2019-06-19
EP2692985A1 (fr) 2014-02-05
KR20130122665A (ko) 2013-11-07
KR20150065916A (ko) 2015-06-15
JP2012207594A (ja) 2012-10-25
CN103459773A (zh) 2013-12-18

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