WO2017037804A1 - タービンロータの製造方法、及び、タービンの製造方法 - Google Patents
タービンロータの製造方法、及び、タービンの製造方法 Download PDFInfo
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- WO2017037804A1 WO2017037804A1 PCT/JP2015/074527 JP2015074527W WO2017037804A1 WO 2017037804 A1 WO2017037804 A1 WO 2017037804A1 JP 2015074527 W JP2015074527 W JP 2015074527W WO 2017037804 A1 WO2017037804 A1 WO 2017037804A1
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/18—Hardening; Quenching with or without subsequent tempering
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/56—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering characterised by the quenching agents
- C21D1/58—Oils
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/46—Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
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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
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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
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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
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
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- 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
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- 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
- F05D2230/00—Manufacture
- F05D2230/40—Heat treatment
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- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
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- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
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- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
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- 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
Definitions
- the present invention relates to a method for manufacturing a turbine rotor used in a turbine, and a method for manufacturing a turbine.
- Patent Document 1 discloses such a low alloy heat resistant steel with improved high temperature resistance as a material used for a turbine rotor.
- a large turbine rotor having an outer diameter dimension exceeding 1000 mm is used.
- a so-called gradient quenching (gradient heat treatment) method is used to improve high temperature resistance.
- the region between the region having high temperature resistance required in the high pressure portion of the turbine and the region having high temperature resistance required in the low pressure portion is used.
- a so-called transition region is formed as an intermediate region having neither characteristic.
- the above-described gradient quenching is performed on a turbine rotor used in a small and medium-sized steam turbine, the entire length of the turbine rotor is short, so that the entire turbine rotor becomes a transition region. It has characteristics that cannot satisfy any requirements of the low pressure part. That is, there is a problem that it is very difficult to manufacture a small-sized turbine rotor having high-temperature resistant performance even if gradient quenching is employed as in the conventional large-sized turbine rotor.
- the present invention provides a method of manufacturing a turbine rotor having sufficient high-temperature resistance as a high-low pressure integrated turbine rotor used for a small-to-medium-sized turbine.
- the turbine rotor according to the first aspect of the present invention is, in weight percent, carbon: 0.20% or more and 0.35% or less, silicon 0.35% or less, manganese: 1.00% or less, nickel: 0.50%.
- a quenching step in which oil quenching is performed at a cooling rate of 2.0 ° C./min or more in a range, and a temperature range of 630 ° C. or more after the quenching step, and a formula P T (C + logt) Tempered para And a tempering step of tempering the rotor raw material under the conditions (T is an absolute temperature (K), t is a time (h), and C is a material constant). It is out.
- a turbine rotor having a maximum outer diameter of 1000 mm or less used for a small and medium-sized turbine can have sufficient high temperature resistance. That is, even a turbine rotor of a medium-sized turbine can have sufficient high-temperature creep strength, low-temperature toughness, and SCC resistance (stress corrosion cracking resistance).
- SCC resistance stress corrosion cracking resistance
- the turbine manufacturing method includes a plurality of rotor blade rows arranged on the turbine rotor so as to be aligned in the direction of the rotation axis of the turbine rotor obtained by the turbine rotor manufacturing method according to the first aspect.
- a turbine blade installation step for fixing the turbine rotor a casing installation step for providing a casing for covering the turbine rotor so that the turbine rotor and the blade cascade can be relatively rotated about the rotation axis, and the casing
- the turbine rotor is manufactured by the above-described manufacturing method, so that even a turbine rotor of a small and medium-sized turbine has sufficient high-temperature creep strength, low-temperature toughness, and SCC resistance (anti-resistance Stress corrosion cracking).
- SCC resistance anti-resistance Stress corrosion cracking
- a turbine rotor having sufficient high temperature resistance can be manufactured as a high-low pressure integrated turbine rotor used for a small and medium-sized turbine.
- the steam turbine 1 is provided in a casing 10, an adjustment valve 20 that adjusts the amount and pressure of the steam S flowing into the casing 10, and an inner space inside the casing 10 so as to be freely rotatable.
- a turbine rotor 30 for transmitting power to the machine, a stationary blade row 40 fixed to the casing 10, a moving blade row 50 fixed to the turbine rotor 30, and the turbine rotor 30 are supported so as to be rotatable around the rotation axis O.
- the bearing part 60 is provided.
- the casing 10 is formed so as to hermetically seal the internal space, and defines a flow path for the steam S.
- a plurality of regulating valves 20 are attached to the casing 10 and each include a regulating valve chamber 21 into which steam S flows from a boiler (not shown), a valve body 22, a valve seat 23, and a steam chamber 24.
- the flow path of the steam S is opened when the valve body 22 is separated from the valve seat 23, whereby the steam S flows into the internal space of the casing 10 through the steam chamber 24.
- the turbine rotor 30 includes a rotor body 31 and a plurality of disks 32 extending radially outward from the outer periphery of the rotor body 31.
- the turbine rotor 30 transmits rotational energy to a machine such as a generator (not shown).
- the bearing portion 60 is fixed to the casing 10 and includes a journal bearing device 61 and a thrust bearing device 62, and rotatably supports the turbine rotor 30 inserted into the casing 10.
- a plurality of stationary blade rows 40 are fixed to the casing 10 at intervals in the direction of the rotation axis O.
- Each stationary blade row 40 includes a plurality of stationary blades 41 arranged radially so as to surround the turbine rotor 30 to constitute an annular stationary blade group.
- column 40 converts the pressure energy of the steam
- a plurality of moving blade rows 50 are fixed to the outer periphery of the disk 32 in the turbine rotor 30 and extend radially outward from the turbine rotor 30.
- Each of the blade rows 50 includes a plurality of blades 51 arranged radially on the disk 32 to form an annular blade group, and is alternately arranged on the downstream side of each stationary blade row 40.
- step ST1 carbon: 0.20% or more and 0.35% or less, silicon 0.35% or less, manganese: 1.00% or less, nickel: 0.50% or more and 1.50% or less, chromium in weight% : 2.00% to 2.50%, Molybdenum: 0.90% to 1.50%, vanadium: 0.20% to 0.30%, balance iron and impurities
- a rotor coarse material 30A having a maximum outer diameter of 1000 mm or less is formed by forging from a low-alloy steel containing no).
- the maximum outer diameter dimension of the rotor coarse material 30A indicates the outer diameter dimension d (see FIG. 1) of the disk 32 having the largest outer diameter among the plurality of disks 32.
- Carbon 0.20% or more and 0.35% or less It is an indispensable element for increasing the hardenability of steel. In order to give the turbine rotor 30 the necessary strength and toughness, 0.20% or more of carbon is required. However, if too much carbon is not obtained, sufficient toughness cannot be obtained and workability is lowered. .35% or less.
- Silicon and manganese are elements necessary for promoting the deoxidizing action of steel. If the silicon content is too large, the toughness and workability deteriorate, so the content was made 0.35% or less. Manganese increases the hardenability and mechanical strength, but if the content is too large, the toughness decreases, so the content was made 1.00% or less.
- Nickel 0.50% or more and 1.50% or less It is an effective element for improving the hardenability and improving the mechanical strength and toughness at a low temperature. In order to promote temper brittleness, the content was made 0.50% or more and 1.50% or less.
- Chromium 2.00% or more and 2.50% or less An element effective for improving strength and toughness at high temperatures. Moreover, since the bainite hardenability is increased, the content is set to 2.00% or more and 2.50% or less from the viewpoint of mass effect.
- Molybdenum 0.90% or more and 1.50% or less
- carbon and chromium there is an effect of increasing strength at high temperature and relaxing temper brittleness. Further, in order to increase the bainite hardenability, it is effective to improve the toughness if appropriate heat treatment is performed. However, even if the content is too large, the above effect is only saturated, so 0.90% or more and 1.50% or less.
- Vanadium 0.20% or more and 0.30% or less It is the most effective element for increasing the strength at high temperature. Even if the content is too large, the toughness deteriorates, so the content was made 0.20% or more and 0.30% or less.
- quenching process ST2 is performed. That is, in the quenching step ST2, the rotor rough material 30A is heated in a temperature range of 940 ° C. or more and 960 ° C. or less, and then at least a cooling rate of 2.0 ° C./min or more in a temperature range of 500 ° C. or less and 250 ° C. Apply oil quenching.
- tempering process ST3 is performed. That is, in the tempering step ST3, the rotor raw material 30A after the quenching is performed in a temperature range of 630 ° C. or higher and a tempering parameter P of 19700 or higher and 19900 or lower. Temper 30A.
- the tempering parameter P is a numerical value defined by the following equation (1).
- P T (C + logt) (1)
- T is an absolute temperature (K)
- t time (h)
- C is a material constant.
- the tempering step ST3 is performed so as to have the predetermined 0.2% yield strength, tensile strength, elongation, drawing, impact value, and 50% FATT shown in Table 5 below. Execute.
- the turbine rotor 30 is manufactured through the above steps. Further, the moving blade row installation step ST4 for installing the moving blade row 50 on the turbine rotor 30 is executed.
- the moving blades 51 are fixed to the disk 32 at intervals in the circumferential direction.
- the moving blade rows 50 are provided in the direction of the rotation axis O so as to be spaced from each other so that the rotor blade rows 50 are arranged in the direction of the rotation axis O.
- a casing installation step ST5 for supporting the turbine rotor 30 by the bearing portion 60 and fixing the bearing portion 60 and the turbine rotor 30 to the casing 10 is performed.
- the casing 10 covers the turbine rotor 30 from the outer peripheral side, and the turbine rotor 30 and the moving blade row 50 can rotate relative to the casing 10 about the rotation axis O.
- a plurality of stationary blade rows 40 are fixed inside the casing 10 so as to be alternately arranged with the moving blade rows 50 in the direction of the rotation axis O by executing the stationary blade row installation step ST6.
- the moving blades 51 are fixed at intervals in the circumferential direction.
- the casing installation step ST5 and the stationary blade row installation step ST6 for example, the lower portion of the anti-cracked casing 10 is first installed, and then the stationary blade row 40 is fixed to the lower portion of the casing 10.
- the turbine rotor 30 provided with the moving blade row 50 is incorporated in the lower part of the casing 10.
- the stationary blade row 40 is fixed to the upper part of the anti-cracked casing 10, and the upper part of the casing 10 is installed in the lower part of the casing 10 in which the turbine rotor 30 is incorporated.
- the turbine rotor 30 having a maximum outer diameter of 1000 mm or less used in the small and medium-sized steam turbine 1 can have sufficient high temperature resistance. That is, even the turbine rotor 30 of the small and medium-sized steam turbine 1 can have sufficient high-temperature creep strength, low-temperature toughness, and SCC resistance (stress corrosion cracking resistance) by the manufacturing method of the present embodiment.
- the disk 32 of the turbine rotor 30 can be thinned at the high-pressure portion of the steam turbine 1 (the portion on the front stage side: the portion on the left side as viewed in FIG. 1), and the number of moving blade rows can be increased. Can do. Further, since the weight of the turbine rotor 30 is reduced by reducing the thickness of the disk 32 and the rotational load of the turbine rotor 30 is reduced, the reliability is improved.
- the turbine rotor 30 having sufficient high temperature resistance as a high-low pressure integrated turbine rotor used in the small and medium-sized steam turbine 1.
- Example ⁇ A material test for confirming the high temperature resistance of the turbine rotor 30 was performed as follows. (Test material) As a test material, a test material block of 30 [mm] ⁇ 30 [mm] ⁇ 150 [mm] was prepared from the same material as the rotor coarse material 30A.
- Heat treatment simulation A heat treatment simulation was performed on the above test material assuming a rotor coarse material 30A having outer diameters of ⁇ 500 [mm], ⁇ 1000 [mm], and ⁇ 1500 [mm].
- heat treatment simulating preliminary heat treatment and temper heat treatment of the actual rotor material was performed.
- solution treatment was first performed. This solution treatment is performed for the purpose of eliminating the influence of the heat treatment performed on the test piece. That is, after heating to 1200 ° C. and holding for 1 hr, air cooling is performed. Thereafter, normalizing and tempering treatment corresponding to preliminary heat treatment of the actual rotor was performed.
- the sample was heated to 1010 ° C., held for 5 hours, and then cooled to 200 ° C. or less at a cooling rate corresponding to air cooling of the actual rotor. Further, the tempering was heated to 720 ° C. and held for 9 hours, and then cooled to 200 ° C. or lower. Thereafter, a heat treatment corresponding to the tempering heat treatment of the actual rotor was performed. After heating to 950 ° C. and holding for 9 hours, the furnace was cooled to 200 ° C. or less at a cooling rate corresponding to oil cooling of the actual machine. Thereafter, a heat treatment corresponding to the tempering process of the actual machine was performed. That is, after heating to a tempering temperature (T ° C.) and holding for 10 hours, the furnace was cooled to 200 ° C. or lower.
- T ° C. tempering temperature
- the outer diameter of the rotor coarse material 30A is set to ⁇ 1000 [mm] or less and 630 ° C. in the above-described embodiment so that the rotor coarse material 30A satisfies the characteristics shown in Table 5 below. Tempering was performed in the above temperature range.
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Abstract
Description
傾斜焼き入れを行うことで、一本のタービンロータの部位毎に、タービンの高圧部及び低圧部でそれぞれ要求される耐高温性を持ったタービンロータを製造可能である。
はじめに、図1を参照して本発明の実施形態に係るタービンの製造方法で製造される蒸気タービン1について説明する。
そして、各静翼列40は、蒸気Sの圧力エネルギーを速度エネルギーに変換して、回転軸線Oの方向の下流側に隣接する後述する動翼列50側に案内するようになっている。
まずはじめに、タービンロータ30の製造方法について説明する。
即ち、成形工程ST1を実行する。成形工程ST1では、重量%で炭素:0.20%以上0.35%以下、ケイ素0.35%以下、マンガン:1.00%以下、ニッケル:0.50%以上1.50%以下、クロム:2.00%以上2.50%以下、モリブデン:0.90%以上1.50%以下、バナジウム:0.20%以上0.30%以下、残部鉄および不純物(製造工程で混入が避けられないもの)を含有する低合金鋼から、最大外径寸法が1000mm以下のロータ粗材30Aを鍛造により成形する。ここで、ロータ粗材30Aの最大外径寸法は、複数のディスク32のうち、最も外径が大きいディスク32の外径寸法d(図1参照)を示す。
(1)炭素:0.20%以上0.35%以下
鋼の焼き入れ性を増大させるために不可欠な元素である。タービンロータ30に必要な強度及び靱性を出すためには0.20%以上の炭素が必要となるが、多すぎると十分な靱性が得られず加工性が低下するので、0.20%以上0.35%以下とした。
ケイ素及びマンガンは、鋼の脱酸作用を促進させるために必要な元素である。ケイ素の含有量が多すぎると靱性及び加工性が低下するため、0.35%以下とした。マンガンは焼き入れ性及び機械的強度を増大させるが、含有量が多すぎると靱性が低下するので1.00%以下とした。
焼き入れ性を向上させ、低温における機械的強度及び靱性を向上させるために有効な元素であるが、含有量が多すぎると高温における強度が低下し、焼き戻し脆性を助長するため0.50%以上1.50%以下とした。
高温における強度及び靱性の改善に有効な元素である。またベイナイト焼き入れ性を増大させるので、質量効果の点から2.00%以上2.50%以下とした。
炭素及びクロムとの共存下で、高温における強度を増大させ、焼き戻し脆性を緩和する効果がある。また、ベイナイト焼き入れ性を増大させるため、適当な熱処理を施せば靱性の改善にも有効である。しかし、含有量が多すぎても上記の効果は飽和するだけであるため、0.90%以上1.50%以下とした。
高温における強度を上げるのに最も有効な元素である。含有量が多すぎても靱性が低下するため、0.20%以上0.30%以下とした。
P=T(C+logt)・・・(1)
Tは絶対温度(K)、tは時間(h)、Cは材料定数である。また、本実施形態では、材料定数:C=20である。
換言すると、630℃以上の温度範囲で、以下の表5に示す所定の0.2%耐力、引張強さ、伸び、絞り、衝撃値、及び50%FATTを有するように、焼き戻し工程ST3を実行する。
さらに、タービンロータ30に動翼列50を設置する動翼列設置工程ST4を実行する。動翼列設置工程ST4では、ディスク32に周方向に間隔をあけて動翼51を固定していく。そして各動翼列50が回転軸線Oの方向に並ぶように回転軸線Oの方向に互いに間隔をあけて設けられる。
実際には、ケーシング設置工程ST5、及び静翼列設置工程ST6では、例えば、まず反割れのケーシング10の下部を設置し、その後、静翼列40をケーシング10の下部に固定する。この状態で、動翼列50が設けられたタービンロータ30をケーシング10の下部に組み込む。また、反割れのケーシング10の上部に静翼列40を固定しておき、このケーシング10の上部を、タービンロータ30を組み込んだケーシング10の下部に設置する。
また、低温靱性が50%FATT(Fracture Appearance Transition Temperature)<40〔℃〕を満足する。
タービンロータ30の耐高温性を確認する材料試験を下記の通り行った。
(試験材)
試験材として、ロータ粗材30Aと同じ材料から30〔mm〕×30〔mm〕×150〔mm〕の試験材ブロックを準備した。
上記の試験材に対して、外径がφ500〔mm〕、φ1000〔mm〕、φ1500〔mm〕のロータ粗材30Aを想定した熱処理シミュレーションを実行した。
熱処理シミュレーションでは実機ロータ材の予備熱処理と調質熱処理を模擬した熱処理を実施した。熱処理シミュレーションではまず溶体化処理を実施した。この溶体化処理は試験片に実施された熱処理の影響を無くす目的で実施する。即ち、1200℃まで加熱し1hr保持した後、空冷する。その後、実機ロータの予備熱処理に相当する焼ならし焼もどし処理を実施した。焼ならしでは1010℃に加熱し、5hr保持した後、実機ロータの空冷に相当する冷却速度で200℃以下まで炉冷した。さらに焼もどしは720℃まで加熱し9hr保持した後に200℃以下まで炉冷した。その後、実機ロータの調質熱処理に相当する熱処理を実施した。950℃に加熱し9hr保持した後、実機の油冷に相当する冷却速度で200℃以下になるまで炉冷した。その後、実機の焼もどし工程に相当する熱処理を実施した。即ち、焼戻温度(T℃)まで加熱し10h保持した後に200℃以下になるまで炉冷した。
上記の試験材から試験片を加工し、材料試験を実行した。上記の熱処理サイクルを実行した場合の、0.2%耐力〔MPa〕、引張強さ〔MPa〕、伸び〔%〕、絞り〔%〕、衝撃値〔J/cm2〕、50%FATT〔℃〕について、外径がφ500〔mm〕、φ1000〔mm〕、φ1500〔mm〕の各ケース(中心部を想定)と、表層部を想定したケースについて、4つの温度条件で試験を行った試験結果は、下記の表1から表4に示す通りである。
10 ケーシング
20 調整弁
21 調整弁室
22 弁体
23 弁座
24 蒸気室
30 タービンロータ
30A ロータ粗材
31 ロータ本体
32 ディスク
40 静翼列
41 静翼
50 動翼列
51 動翼
60 軸受部
61 ジャーナル軸受装置
62 スラスト軸受装置
O 回転軸線
S 蒸気
ST1 成形工程
ST2 焼き入れ工程
ST3 焼き戻し工程
ST4 動翼列設置工程
ST5 ケーシング設置工程
ST6 静翼列設置工程
Claims (2)
- 重量%で炭素:0.20%以上0.35%以下、ケイ素0.35%以下、マンガン:1.00%以下、ニッケル:0.50%以上1.50%以下、クロム:2.00%以上2.50%以下、モリブデン:0.90%以上1.50%以下、バナジウム:0.20%以上0.30%以下を含有する低合金鋼から、最大外径が1000mm以下のロータ粗材を成形する成形工程と、
前記ロータ粗材に、940℃以上960℃以下の温度範囲で加熱した後、少なくとも500℃以下250℃以上の温度範囲で2.0℃/min以上の冷却速度で油焼き入れを施す焼入れ工程と、
前記焼入れ工程の後に、630℃以上の温度範囲で、かつ、数式P=T(C+logt)で定義される焼き戻しパラメータPが19700以上19900以下となる条件(Tは絶対温度(K)、tは時間(h)、Cは材料定数)で、前記ロータ粗材に焼き戻しを施す焼き戻し工程と、
を含むタービンロータの製造方法。 - 請求項1に記載のタービンロータの製造方法で得られるタービンロータの回転軸線の方向に並ぶように、前記タービンロータに複数の動翼列を固定する動翼列設置工程と、
前記タービンロータ、及び、前記動翼列を前記回転軸線を中心として相対回転可能となるように、前記タービンロータを覆うケーシングを設けるケーシング設置工程と、
前記ケーシングに、前記回転軸線の方向に前記動翼列と交互に配置されるように複数の静翼列を固定する静翼列設置工程と、
を含むタービンの製造方法。
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