EP1466993A1 - Acier résistant à la chaleur et turbine à gaz et composants réalisées en cet acier - Google Patents

Acier résistant à la chaleur et turbine à gaz et composants réalisées en cet acier Download PDF

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Publication number
EP1466993A1
EP1466993A1 EP04001026A EP04001026A EP1466993A1 EP 1466993 A1 EP1466993 A1 EP 1466993A1 EP 04001026 A EP04001026 A EP 04001026A EP 04001026 A EP04001026 A EP 04001026A EP 1466993 A1 EP1466993 A1 EP 1466993A1
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Prior art keywords
amount
turbine
steel
compressor
disc
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EP1466993B1 (fr
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Masahiko Hitachi Ltd. Intel. Prop. Group Arai
Hirotsugu Hitachi Ltd Int. Prop. Group Kawanaka
Hiroyuki Hitachi Ltd. Intel. Prop. Group Doi
Isao Hitachi Ltd. Intel. Prop. Group Takehara
Hidetoshi Hitachi Ltd Intel. Prop. Group Kuroki
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Hitachi Ltd
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Hitachi Ltd
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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
    • 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
    • C22C38/001—Ferrous alloys, e.g. steel alloys containing N
    • 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
    • C22C38/002—Ferrous alloys, e.g. steel alloys containing In, Mg, or other elements not provided for in one single group C22C38/001 - C22C38/60
    • 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
    • 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
    • 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
    • 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
    • C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
    • 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
    • C22C38/52—Ferrous alloys, e.g. steel alloys containing chromium with nickel with cobalt
    • 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
    • C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron

Definitions

  • the present invention relates to a novel heat resisting steel, a gas turbine using the steel, and various members of the gas turbine.
  • the conventional Cr-Mo-V steel and 12Cr-Mo-Ni-V-N steel have insufficient strength, and materials having higher strengths are required.
  • As the strength a creep rupture strength which influences high-temperature characteristics most is required.
  • a high tensile strength and high toughness are also required as well as the creep strength, and especially embrittlement has to be inhibited from occurring at the high temperature during the use.
  • austenitic steel As a structural material having a high creep rupture strength, austenitic steel, Ni-base alloy, Co-base alloy, martensitic steel, and the like have generally been known.
  • the Ni-base alloy and Co-base alloy are not preferable from the standpoint of hot workability, machinability, and vibration damping property.
  • the austenitic steel does not have a very high strength at around 400 to 450°C, and is not preferable in a whole gas turbine system.
  • the martensitic steel has satisfactory matching with another corresponding component, and also has a sufficient high-temperature strength.
  • JP-A-2001-49398 a heat resisting steel having high strength and toughness has been disclosed as a high/low pressure integral type steam turbine rotor. Further in JP-A-11-209851, PCT/JP97/04609, and JP-A-10-251809, a heat resisting steel for a gas turbine disc material has been disclosed.
  • the heat resisting steels disclosed in the publications cannot satisfy especially the high creep rupture strength and embrittlement reduction at the same time among the characteristics such as the high creep rupture strength, high tensile strength, high toughness, and embrittlement reduction, and are not sufficient as the gas turbine disc having a higher efficiency.
  • the gas temperature cannot further rise.
  • a high-temperature portion is cooled by a large amount of cooling air, further rise of the gas temperature can be anticipated, but thermal efficiency remarkably drops. Therefore, cooling air needs to be saved in order to prevent the drop of the thermal efficiency, but the saving is impossible until the above-described high material characteristics are obtained.
  • the toughness is lowered, and it is therefore difficult to achieve both the characteristics at the same time.
  • An object of the present invention is to provide a heat resisting steel which has high creep rupture strength to be capable of handling a higher temperature and which has high toughness even after heating at a high temperature for a long time, a gas turbine using the heat resisting steel, and various components of the gas turbine.
  • a heat resisting martensitic steel comprising, by weight, 0.05 to 0.30% C, not more than 0.50% Si, not more than 0.60% Mn, 8.0 to 13.0% Cr, 0.5 to 3.0% Ni, 1.0 to 3.0% Mo, 0.1 to 1.5% tungsten (W), 0.5 to 4% Co, 0.05 to 0.35% vanadium (V), 0.02 to 0.30% in total of one or two elements selected from the group consisting of Nb and Ta, and 0.02 to 0.10% nitrogen (N), wherein a value of the square of a difference between the Ni amount and the Co amount, and the Ni amount are not more than values determined by a straight line drawn on a point A (1.0, 2.7%) and a point B (2.5, 1.0%) in the orthogonal coordinates shown in the attached drawing of Fig. 2 which represents a relationship between the above square value and the Ni amount, and wherein an amount ratio of Mo/(Mo + 0.5W) is not less than 0.5
  • an amount ratio of W/Mo, and the Mn amount are not more than values determined by a straight line drawn on a point C (1.3, 0.15%) and a point D (2.5, 0.37%) in the orthogonal coordinates shown in the attached drawing of Fig. 4 which represents a relationship between the amount ratio and the Mn amount.
  • an amount ratio of Mo/(Mo + 0.5W), and the Mn amount are not less than values determined by a straight line drawn on a point E (0.25, 0.4%) and a point F (0.7, 0.15%) in the orthogonal coordinates shown in the attached drawing of Fig. 6 which represents a relationship between the amount ratio and the Mn amount.
  • the invention steel may comprise, by weight, at least one element of not more than 1.5% Re and 0.001 to 0.015% boron (B).
  • the invention steel may comprise, by weight, at least one element selected from the group consisting of not more than 0.5% Cu, not more than 0.5% Ti, not more than 0.2% Al, not more than 0.1% Zr, not more than 0.1% Hf, not more than 0.01% Ca, not more than 0.01% Mg, not more than 0.01% yttrium (Y), and not more than 0.01% of a rare earth element.
  • the invention heat resisting steel is adjusted to have such a chemical composition that the Cr-equivalent, as defined by the following equation, is not more than 10, and the steel does not essentially contain the ⁇ ferrite phase:
  • the invention steel preferably has not less than 1180 MPa of tensile strength at room temperature, more preferably not less than 1200 MPa, not less than 420 Mpa of creep rupture strength at 510°C for 10 5 hours, more preferably not less than 430 Mpa, and not less than 19.6 J/cm 2 of a V-notch Charpy impact value at 25°C after heating at 530°C for 10 4 hours.
  • a gas turbine comprising:
  • a disc for a gas turbine which is a disc member comprising a circumferential implanting section for a turbine blade, and a plurality of bores receiving a plurality of stacking bolts by which a plurality of the disc members are integrally fastened to one another, wherein the disc is made of the heat resisting steel having the above chemical composition and properties.
  • the disc member may have optionally a central bore.
  • the gas turbine disc should have high fatigue strength as well as high tensile strength in order to bear high centrifugal stress and vibration stress due to high-speed rotation. If the gas turbine disc has a metal structure containing the detrimental delta ( ⁇ ) ferrite, the fatigue strength is excessively deteriorated. Therefore, the Cr-equivalent is so adjusted to be not more than 10 that the steel has an entire temper martensite structure.
  • a gas turbine distant piece which is a cylindrical member comprising protrusions provided at both opposite ends of the cylindrical member; a plurality of bores in one of the protrusions, which receive a plurality of stacking bolts by which the cylindrical member is integrally fastened to turbine discs, and a plurality of other bores in the other protrusion, which receive a plurality of other stacking bolts by which the cylindrical member is integrally fastened to compressor discs, wherein the gas turbine distant piece is made of the above heat resisting steel having the same properties as mentioned above.
  • gas turbine compressor discs each of which is a disc member comprising a circumferential implanting section for compressor blades, and a plurality of bores receiving a plurality of stacking bolts by which a plurality of the disc members are integrally fastened to one another, wherein the gas turbine compressor discs are made of the above heat resisting steel having the same properties as mentioned above.
  • a gas turbine stacking bolt which is a bar member comprising a screw portion at one end thereof, and a polygonal head portion at the other end, wherein the gas turbine stacking bolt is made of the above heat resisting steel having the same properties as mentioned above.
  • a carbon (C) content is set to not less than 0.05% in order to obtain high tensile strength and yield strength.
  • the content is set to not more than 0.30%, especially preferably 0.07 to 0.23%, more preferably 0.10 to 0.20%.
  • Si is a deoxidizer, and Mn is a desulfurizing/deoxidizing agent. These are added at the time of melting of heat resisting steel, and are effective even in small amounts.
  • Si is a ⁇ ferrite generating element. When a large amount of this element is added, detrimental ⁇ ferrite is generated to lower fatigue strength and toughness. Therefore, the content is set to 0.50% or less. It is to be noted that Si does not have to be added in a carbon vacuum deoxidizing process and electro slag remelting process, and no Si is preferably added. The content is especially preferably 0.10% or less, more preferably 0.05% or less.
  • the content is set to 0.60% or less.
  • Mn is effective as the desulfurization agent
  • the content is preferably 0.30% or less, especially preferably 0.25% or less, further preferably 0.20% or less from the standpoint of enhancement of the toughness.
  • the content of 0.05% or more is preferable from the standpoint of the toughness.
  • Cr enhances corrosion resistance and tensile strength, but with an addition amount exceeding 13%, a ⁇ ferrite structure is generated.
  • the content of Cr is set to 8 to 13%.
  • the content is especially preferably 10.0 to 12.8%, more preferably 10.5 to 12.5%.
  • Mo is effective in improving the creep rupture strength by virtue of solid-solution strengthening and precipitation strengthening with carbide/nitride.
  • Mo content is not more than 1.0%, Mo has an insufficient effect of enhancing the creep rupture strength.
  • the Mo content is not less than 3%, delta ( ⁇ ) ferrite is generated. Therefore, the Mo content is set to 1.0 to 3.0%, preferably 1.2 to 2.7%, more preferably 1.3 to 2.5%.
  • W has an effect similar to that of Mo.
  • the content may be equal to that of Mo.
  • W has an insufficient effect of enhancing the creep rupture strength.
  • the content is preferably 0.2 to 1,4%, more preferably 0.3 to 1.3%.
  • the content is preferably increased with the increase of the temperature. With a content less than 0.5%, the effect is not sufficient. With a content exceeding 4.0%, heating embrittlement is promoted, and therefore an upper limit is set to 4%.
  • the content is preferably 0.8 to 3.5%.
  • V and Nb precipitate carbide, enhance the tensile strength, and further have an effect of enhancing the toughness.
  • the effect is insufficient.
  • the content of V is preferably 0.15 to 0.30%, more preferably 0.20 to 0.30%.
  • the content of Nb is 0.04 to 0.22%, more preferably 0.10 to 0.20%.
  • Ta can be added in the same manner, and a total amount is similar to the content even in composite addition.
  • Ni enhances low-temperature toughness, and also has an effect of preventing ⁇ ferrite from being generated. This effect is preferable with not less than 0.5% Ni, and the effect is saturated with an addition amount exceeding 3.0%. When a large amount of Ni is added, the creep rupture strength is lowered.
  • the content is preferably 0.5 to 2.5%, more preferably 0.7 to 2.3%.
  • N is effective in enhancing the creep rupture strength and in preventing ⁇ ferrite from being generated.
  • the effect is insufficient with a content less than 0.02%, and the toughness is lowered with a content exceeding 0.10%.
  • superior properties are obtained in a range of 0.04 to 0.080%.
  • Re is effective in improving the creep rupture strength by virtue of solid-solution strengthening. Since an excess addition promotes the embrittlement, an addition amount of not more than 2% is preferable. However, since Re is a rare element, a content of not more than 1.5% is preferable in a practical use, more preferably not more than 1.2%.
  • B has a function of enhancing a grain boundary strength, and has an effect of enhancing the creep rupture strength. This effect is insufficient with a content of not more than 0.001%, and the toughness drops with an addition amount exceeding 0.015%.
  • the content is especially preferably 0.002 to 0.008%.
  • the reduction of P and S has an effect of enhancing the low-temperature toughness without impairing the creep rupture strength, and the reduction to the utmost is preferable.
  • the enhancement of the low-temperature toughness not more than 0.015% phosphor (P), not more than 0.015% sulfur (S) are preferable.
  • not more than 0.010% phosphor (P), not more than 0.010% sulfur (S) are preferable.
  • the reduction of Sb, Sn, and As also has the effect of enhancing the low-temperature toughness, and the reduction to the utmost is preferable, but from the standpoint of an existing steel making technique level, the content is limited to not more than 0.0015% Sb, not more than 0.01% Sn, and not more than 0.02% As. Especially, not more than 0.001% Sb, 0.005% Sn, and not more than 0.01% As are preferable.
  • At least one of MC carbide forming elements such as Ti, Al, Zr, Hf, Ta is preferably contained by not more than 0.5% in total.
  • the content of Al, which is used as a deoxidizer and a grain refiner, is set to not less than 0.0005%. If the Al content exceeds 0.2%, nitrogen, which is effective for improving the creep strength, is fixed to deteriorate the creep rupture strength. Thus, the Al content is preferably not more than 0.2%.
  • a value of the square of a difference between the Ni amount and the Co amount, and the Ni amount have been set to be not more than values determined by a straight line drawn on a point A (1.0, 2.7%) and a point B (2.5, 1.0%) in the orthogonal coordinates shown in the attached drawing of Fig. 2 which represents a relationship between the above square value and the Ni amount, and an amount ratio of Mo/(Mo + 0.5W) is set to be not less than 0.5, whereby the above properties can be obtained.
  • the tungsten (W) amount is not more than 1.5%.
  • the above square value is preferably set to be not more than 1.8. If the tungsten (W) amount exceeds 1.5%, the high creep strength mentioned above can be obtained, but the toughness is deteriorated after heating at high temperature for a long time. Thus, more than 1.5% tungsten (W) is not preferable.
  • Ni and Co contribute to improving martensitic steel in toughness.
  • Ni is effective for improving the toughness, but deteriorates the creep strength.
  • Co is effective for improving the creep strength, but promotes embrittlement of the steel during operation, and deteriorates the toughness. Therefore, since the toughness and creep strength are kept and the heating embrittlement is inhibited, it has been found that the difference between the Ni amount and the Co amount is an effective index indicating a preferable balance between the additive amounts of Ni and Co in the present invention.
  • an amount ratio of W/Mo, and the Mn amount are set to be not more than values determined by a straight line drawn on a point C (1.3, 0.15%) and a point D (2.5, 0.37%) in the orthogonal coordinates shown in the attached drawing of Fig. 4 which represents a relationship between the amount ratio and the Mn amount. Accordingly, a high toughness is obtained even after the heating at high temperature for the long time.
  • an amount ratio of Mo/(Mo + 0.5W), and the Mn amount are set to be not less than values determined by a straight line drawn on a point E (0.25, 0.4%) and a point F (0.7, 0.15%) in the orthogonal coordinates shown in the attached drawing of Fig. 6 which represents a relationship between the amount ratio and the Mn amount. Accordingly, the high toughness is obtained especially even after the heating at high temperature for the long time.
  • the addition of W is effective under a use environment at a temperature exceeding 600°C, but a use temperature of the gas turbine disc is lower, and the high toughness is required. Therefore, the Mo addition is more preferable in the present invention. Therefore, when the amount ratio of (Mo/(Mo + 0.5W) is set to 0.5 or more, preferably 0.6 to 0.95, more preferably 0.75 to 0.95, the high toughness is obtained even after the heating at high temperature for the long time.
  • the material of the present invention In a preferable thermal treatment of the material of the present invention, first the material is uniformly heated at a temperature sufficient for transformation to complete austenite, 1000°C at minimum, 1150°C at maximum, quenched (preferably oil cooling or water spraying), and subsequently heated/retained and cooled at a temperature of 540 to 600°C (primary tempering). Subsequently, the material is heated/retained and cooled at a temperature of 550 to 650°C (secondary tempering) to form an entirely tempered martensitic steel.
  • the temperature of the secondary tempering is set to be higher than a primary tempering temperature.
  • quenching it is preferable to stop cooling just above an Mf point in order to prevent occurrence of cracks.
  • the above cooling-stop temperature is preferably not lower than 150°C.
  • Table 1 indicates a chemical composition (weight %) of heat resisting 12% Cr steel for a gas turbine disc material, and the balance is Fe.
  • Each specimen was subjected to vacuum arc melting at 150 kg, heated at 1150°C, and forged to form a raw material.
  • the raw material was heated at 1050°C for two hours and subsequently oil-cooled, heated at 560°C for five hours and subsequently air-cooled to be subjected to the primary tempering, and next heated at 580°C for five hours and furnace-cooled to be subjected to the secondary tempering.
  • a creep rupture specimen, tensile specimen, and V-notch Charpy impact specimen were sampled from the raw material, and used in experiments.
  • the embrittled material has conditions equal to those of a material heated at 510°C for 100 thousand hours on the basis of the Larson-Miller parameter.
  • Specimen Nos. 7 to 13 are of the invention steel exhibiting not less than 1180 MPa of tensile strength at room temperature which is required for a high-temperature/high-pressure gas turbine disc material, not less than 420 MPa of creep rupture strength at 510°C for 10 5 hours, and not less than 19.6 J/cm 2 of the V-notch Charpy impact value at 25°C after embrittle treatment. It has been confirmed that the specimens are sufficiently satisfactory.
  • Specimen Nos. 1 to 6 which are of comparative steel, cannot simultaneously satisfy mechanical properties required for the high-temperature/pressure gas turbine disc material. For any one of Specimen Nos.
  • Specimen Nos. 3 and 6 in which the amount ratio of Mo/(Mo + 0.5W) of an Mo-equivalent is less than 0.5 have a low impact value.
  • FIG. 1 is a diagram showing a relation between the creep rupture strength and the square of (difference between Ni amount and Co amount). As shown in FIG. 1, the creep rupture strength remarkably drops as the value of the square of a difference between the Ni amount and the Co amount increases. Especially, the relation with the Ni amount is large. When the Ni amount is 1.0 to 1.2%, the creep rupture strength is high as compared with an amount of 2.2 to 3.2%. However, with high Ni, when the square value increases, the creep rupture strength rapidly drops.
  • FIG. 2 is a linear diagram showing a relationship between the square value and the Ni amount having a creep rupture strength at 510°C for 10 5 hours of not less than 420 MPa from the relation of FIG. 1.
  • the above square value has a close relation with the Ni amount.
  • the value represented by the relation between the square value and the Ni amount is set to be not more than the value determined by a straight line drawn on a point A (1.0, 2.7%) and a point B (2.5, 1.0%) in the orthogonal coordinates shown in the attached drawing of Fig. 2 which represents a relationship between the above square value and the Ni amount, a creep rupture strength of 420 MPa or more is obtained.
  • FIG. 3 is a linear diagram showing a relation between the V-notch Charpy impact value at 25°C and an amount ratio of W/Mo after the embrittle treatment.
  • the impact value rapidly drops with an increase of the ratio of W/Mo.
  • the impact value is high with a large Mn amount of 0.32 to 0.4% as compared with an amount of 0.15%, and is further high with a large C amount. Furthermore, the impact value remarkably drops with any Mn amount, when the ratio of W/Mo increases.
  • FIG. 4 is a linear diagram showing a relationship between the ratio W/Mo and the Mn amount having a V-notch Charpy impact value at 25°C of 19.6 J/cm 2 or more after the embrittle treatment.
  • the value represented by the relation between the (W amount/Mo amount) ratio and the Mn amount is set to be not more than the value determined by a straight line drawn on a point C (1.3, 0.15%) and a point D (2.5, 0.37%) in the orthogonal coordinates shown in the attached drawing of Fig. 4 which represents a relationship between the amount ratio and the Mn amount
  • a 25°C V-notch Charpy impact value of not less than 19.6 J/cm 2 is obtained.
  • FIG. 4 is applied with a C amount of not more than 0.17%.
  • FIG. 5 is a linear diagram showing a relationship between the V-notch Charpy impact value at 25°C and an amount ratio of Mo/Mo + 0.5W) after the embrittle treatment. As shown in FIG. 5, when the ratio is further increased, the high toughness is obtained even after the heating at high temperature for the long time.
  • the impact value is high with a large Mn amount of 0.32 to 0.4% as compared with an amount of 0.15%, and further with a large C amount, and increases as the ratio of Mo/(Mo + 0.5W) increases.
  • the Mn amount is 0.15%
  • a carbon amount is not more than 0.15%.
  • the Mn amount is 0.32 to 0.4%, the carbon amount is 0.11 to 0.17%.
  • FIG. 6 is a linear diagram showing a relationship between the amount ratio of Mo/(Mo + 0.5W) and the Mn amount in which a V-notch Charpy impact value at 25°C after the embrittle treatment of not less than 19.6 J/cm 2 is obtained.
  • the value represented by this relation is set to be not less than the value determined by a straight line drawn on a point E (0.25, 0.4%) and a point F (0.7, 0.15%) in the orthogonal coordinates shown in the attached drawing of Fig. 6 which represents a relationship between the amount ratio and the Mn amount, the above-described impact value is obtained.
  • FIG. 6 is applied with a carbon amount of 0.17% or less.
  • FIG. 7 is a sectional view of a turbine upper half of an air compression type three-stage turbine including an air cooling system.
  • a gas turbine of the present example is constituted of a casing 80, a compressor including a compressor rotor 2 and a blade array of an outer peripheral portion, a combustion unit 84, alternately arranged turbine nozzles 81 to 83 and turbine blades 51 to 53, a turbine rotor 1, and the like.
  • the turbine rotor 1 includes three turbine discs 11, 12, 13 and a turbine stub shaft 4, and is closely bonded as a high-speed rotating member.
  • the turbine blades 51 to 53 are disposed on the outer periphery of each turbine disc, connected to the compressor rotor 2 and turbine stub shaft via a distant piece 3, and rotatably supported by a bearing.
  • air compressed by the compressor is used, and a high-temperature/pressure working gas generated by the combustion unit 84 expands while flowing. Accordingly, the turbine rotor 1 is rotated to generate a motive energy.
  • a combustion gas flowing out of the turbine section is fed to an exhaust heat recovery boiler (HRSG) to produce steam.
  • HRSG exhaust heat recovery boiler
  • a main constitution of the gas turbine in the present embodiment includes the turbine stub shaft 4, turbine stacking bolts 5, turbine spacers 18, the distant piece 3, compressor discs 17 constituting a compressor rotor, compressor blades, compressor stacking bolts, and a compressor stab shaft.
  • the compressor discs 17 are of not less than seventeen stages, and the turbine blades are of three stages. The constitution can similarly be applied also with respect to four stages.
  • air compressed by the compressor is used to cool each component by a flow of air shown by an arrow in FIG. 7.
  • Air flows in via an outer side wall in the first-stage turbine nozzle 81 and the second-stage turbine nozzle 82, and is exhausted from a blade section.
  • the second-stage turbine nozzle 82 is cooled over an inner side wall.
  • air flows in via the outer side wall, flows out of the inner side wall, and is exhausted to the outside via the spacer section.
  • compressed air passes through the side wall from a central portion of the turbine disc 11.
  • the air passes through a spacer 18 section and through cooling bores provided in the blade, and is exhausted via the tip end of the blade and a trailing portion of a blade section to cool both the blade and disc.
  • the combustion gas is sealed not to flow inside by a seal fin disposed in a shank portion.
  • air passes through the spacer 18 and the cooling bore provided in the blade from the turbine disc 12, and is exhausted via the tip end, and cooled.
  • the third-stage turbine blade 53 does not include any cooling bore, but air passes through the side wall from the central portion of the turbine disc 13, passes through the seal fins to cool these fins, and enters the exhaust heat recovery boiler together with the combustion gas.
  • steam is formed as a power source of a steam turbine.
  • Example 1 As the material for use in the turbine discs 11, 12, 13 in the present embodiment, a large-sized specimen including composition No. 1 shown in Table 1 of Example 1 was melted, heated at 1150°C, and forged to form an experiment material. The material was heated at 1050°C for eight hours and cooled with a blast air, and the cooling temperature was stopped at 150°C. The material was heated at 580°C for 12 hours and air-cooled to perform the secondary tempering. Next, the material was heated at 605°C for five hours, and furnace-cooled to perform the secondary tempering. A creep rupture specimen, tensile specimen, and V-notch Charpy impact test specimen were sampled from the material after the thermal treatment, and used in the experiments. The impact test of the thermally treated material was conducted with respect to the heated/embrittled material in the same manner as in Example 1. These properties in the present embodiment are equivalent to those of Example 1.
  • any of the entirely tempered martensitic steel Nos. 7 to 13, Nos. 17 to 19 shown in Example 1 is usable in the distant piece 3 and turbine stacking bolt 5 in addition to the turbine discs 11, 12, 13.
  • these martensitic steels have a ferrite-based crystalline structure, but the ferrite-based material has a small thermal expansion coefficient as compared with an austenite-based material such as Ni-base alloy.
  • the thermal expansion coefficient of the disc material is further small. Therefore, thermal stress generated in the disc is reduced, cracks are inhibited from being generated, and collapse can be reduced.
  • the compressor blade includes 17 stages, and an obtained air compression ratio is 18.
  • an Ni-base super alloy is used in the first-stage turbine nozzle 81 and first-stage turbine blade 51 of the gas turbine.
  • a polycrystalline cast material is used in 1300°C class, and a monocrystalline cast material is used in 1500°C class.
  • an Ni-base super alloy is used containing, by weight percentage, 4 to 10% Cr, 0.5 to 1.5% Mo, 4 to 10% W, 1 to 4% Re, 3 to 6% Al, 4 to 10% Ta, 0.5 to 10% Co, and 0.03 to 0.2% Hf.
  • the equivalent alloy containing 10 to 15% Cr is used in the polycrystalline cast material.
  • the second-stage turbine nozzle and third-stage turbine nozzle are constituted of the Ni-base super alloy containing, by weight percentage, 21 to 24% Cr, 18 to 23% Co, 0.05 to 0.20% C, 1 to 8% W, 1 to 2% Al, 2 to 3% Ti, 0.5 to 1.5% Ta, and 0.05 to 0.15% B.
  • These nozzles include an equiaxed structure obtained by usual casting.
  • the Ni-base super alloy is used in the second-stage turbine blade 52 and third-stage turbine blade 53.
  • the polycrystalline cast material is used in the 1300°C class
  • a directionally solidified prismatic Ni-base super alloy cast material is used in 1500°C class.
  • Either material is constituted of the Ni-base super alloy containing, by weight percentage, 5 to 18% Cr, 0.3 to 6% Mo, 2 to 10% W, 2.5 to 6% Al, 0.5 to 5% Ti, 1 to 4% Ta, 0.1 to 3% Nb, 0 to 10% Co, 0.05 to 0.21% C, 0.005 to 0.025% B, 0.03 to 2% Hf, and 0.1 to 5% Re.
  • the blade of the directionally solidified prismatic Ni-base super alloy is obtained by entire solidification in one direction toward a dove-tail direction from the tip end.
  • the toughness is high even with strength enhancement and heating embrittlement. Accordingly, since especially the material temperature of the turbine disc can be set to be high, the above-described cooling can be reduced. Furthermore, the thickness or diameter of the above-described member for use can be reduced, reduction in weight is achieved, and start properties are enhanced.
  • a gas turbine for power generation in which a natural gas, light oil, and the like are used as fuels for use, a gas inlet temperature into the first-stage turbine nozzle is 1500°C, a metal temperature of the first-stage turbine blade is 900°C, an exhaust gas temperature of the gas turbine is 650°C, and a power generation efficiency is 37% or more in LHV indication. This also applies with the gas inlet temperature into the first-stage turbine nozzle of 1300°C.
  • a multiaxial combined cycle power generation system including a combination of one gas turbine and one high/medium/low pressure integral steam turbine having a steam inlet temperature into the first-stage turbine blade at 566°C.
  • Each turbine includes a power generator. A higher power generation efficiency can be obtained.
  • a high-efficiency high-temperature gas turbine is obtained in which a creep rupture strength and an impact value after heating embrittlement required especially for a gas turbine in a gas temperature class at 1300 to 1500°C are high. Furthermore, the present invention can also be applied to a turbine stacking bolt, turbine spacer, and distant piece exposed at a high temperature in a heating embrittlement range. Therefore, according to the present invention, since a combustion temperature and member temperature of a gas turbine power generation plant can be raised, the cooling in a high-temperature section can be reduced. Further, on the other hand, a rotation section can be reduced in weight, and therefore further high efficiency is achieved. Moreover, it is possible to save a fossil fuel and to reduce a generated amount of exhaust gas and to contribute to global environment preservation.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04001026A 2003-04-04 2004-01-19 Acier résistant à la chaleur et turbine à gaz et composants réalisées en cet acier Expired - Lifetime EP1466993B1 (fr)

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JP2003101401A JP3921574B2 (ja) 2003-04-04 2003-04-04 耐熱鋼とそれを用いたガスタービン及びその各種部材

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EP2478988A1 (fr) * 2011-01-20 2012-07-25 Alstom Technology Ltd Matériau d'apport de soudage basé sur le fer
WO2014066570A1 (fr) * 2012-10-24 2014-05-01 Crs Holdings, Inc Alliage d'acier résistant à la corrosion trempé et revenu
CN104831160A (zh) * 2015-03-26 2015-08-12 哈尔滨汽轮机厂有限责任公司 用于630℃超超临界汽轮机叶片的含Re钢材料及其制造方法
RU2585591C1 (ru) * 2014-11-28 2016-05-27 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса
RU2598725C2 (ru) * 2014-11-28 2016-09-27 Федеральное государственное автономное образовательное учреждение высшего образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса и способ ее получения
RU2615931C1 (ru) * 2016-06-16 2017-04-11 Юлия Алексеевна Щепочкина Сплав на основе железа
US10094007B2 (en) 2013-10-24 2018-10-09 Crs Holdings Inc. Method of manufacturing a ferrous alloy article using powder metallurgy processing
RU2757923C1 (ru) * 2020-12-25 2021-10-25 Федеральное государственное автономное образовательное учреждение высшего образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса
US11634803B2 (en) 2012-10-24 2023-04-25 Crs Holdings, Llc Quench and temper corrosion resistant steel alloy and method for producing the alloy

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JP4887506B2 (ja) * 2008-03-26 2012-02-29 防衛省技術研究本部長 フェライト系耐熱鋼の製造方法
JP6113456B2 (ja) * 2012-10-17 2017-04-12 三菱日立パワーシステムズ株式会社 析出硬化型マルテンサイト系ステンレス鋼とそれを用いた蒸気タービン長翼
CN113278890A (zh) * 2013-06-25 2021-08-20 特纳瑞斯连接有限公司 高铬耐热钢
JP6317566B2 (ja) * 2013-11-08 2018-04-25 三菱日立パワーシステムズ株式会社 析出硬化型マルテンサイト系ステンレス鋼、該ステンレス鋼を用いたタービン部材、および該タービン部材を用いたタービン

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CN102601538B (zh) * 2011-01-20 2016-08-17 通用电器技术有限公司 焊接填充材料
CN102601538A (zh) * 2011-01-20 2012-07-25 阿尔斯通技术有限公司 焊接填充材料
CH704427A1 (de) * 2011-01-20 2012-07-31 Alstom Technology Ltd Schweisszusatzwerkstoff.
EP2478988A1 (fr) * 2011-01-20 2012-07-25 Alstom Technology Ltd Matériau d'apport de soudage basé sur le fer
WO2014066570A1 (fr) * 2012-10-24 2014-05-01 Crs Holdings, Inc Alliage d'acier résistant à la corrosion trempé et revenu
US10458007B2 (en) 2012-10-24 2019-10-29 Crs Holdings, Inc. Quench and temper corrosion resistant steel alloy
US11634803B2 (en) 2012-10-24 2023-04-25 Crs Holdings, Llc Quench and temper corrosion resistant steel alloy and method for producing the alloy
US10094007B2 (en) 2013-10-24 2018-10-09 Crs Holdings Inc. Method of manufacturing a ferrous alloy article using powder metallurgy processing
RU2585591C1 (ru) * 2014-11-28 2016-05-27 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса
RU2598725C2 (ru) * 2014-11-28 2016-09-27 Федеральное государственное автономное образовательное учреждение высшего образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса и способ ее получения
CN104831160A (zh) * 2015-03-26 2015-08-12 哈尔滨汽轮机厂有限责任公司 用于630℃超超临界汽轮机叶片的含Re钢材料及其制造方法
CN104831160B (zh) * 2015-03-26 2016-09-28 哈尔滨汽轮机厂有限责任公司 用于630℃超超临界汽轮机叶片的含Re钢材料及其制造方法
RU2615931C1 (ru) * 2016-06-16 2017-04-11 Юлия Алексеевна Щепочкина Сплав на основе железа
RU2757923C1 (ru) * 2020-12-25 2021-10-25 Федеральное государственное автономное образовательное учреждение высшего образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") Жаропрочная сталь мартенситного класса

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JP3921574B2 (ja) 2007-05-30
JP2004307910A (ja) 2004-11-04
DE602004005910D1 (de) 2007-05-31
US20050074356A1 (en) 2005-04-07
EP1466993B1 (fr) 2007-04-18
DE602004005910T2 (de) 2007-12-06
US20090068052A1 (en) 2009-03-12

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