EP0298127A1 - Acier resistant a la chaleur et turbine a gaz composee de cet acier - Google Patents

Acier resistant a la chaleur et turbine a gaz composee de cet acier Download PDF

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Publication number
EP0298127A1
EP0298127A1 EP88900787A EP88900787A EP0298127A1 EP 0298127 A1 EP0298127 A1 EP 0298127A1 EP 88900787 A EP88900787 A EP 88900787A EP 88900787 A EP88900787 A EP 88900787A EP 0298127 A1 EP0298127 A1 EP 0298127A1
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European Patent Office
Prior art keywords
weight
less
turbine
compressor
disc
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EP88900787A
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German (de)
English (en)
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EP0298127A4 (en
EP0298127B1 (fr
Inventor
Masao Siga
Yutaka Fukui
Mitsuo Kuriyama
Katsumi Iijima
Yoshimi Maeno
Shintaro Takahashi
Nobuyuki Iizuka
Soichi Kurosawa
Yasuo Watanabe
Ryo Hiraga
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Hitachi Ltd
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Hitachi Ltd
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Publication of EP0298127A4 publication Critical patent/EP0298127A4/en
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    • 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
    • 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
    • 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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum

Definitions

  • the present invention relates to a novel heat-resistant steel and particularly to a novel gas turbine made of said steel.
  • a Cr-Mo-V steel is currently used in discs for a gas turbine.
  • the most useful means of improving the thermal efficiency of a gas turbine is to increase the temperature and pressure of a gas used.
  • an improvement in the efficiency of about 3% in terms of relative ratio can be expected by raising the gas temperature from 1,100°C to 1,300°C and increasing the pressure ratio from 10 to 15.
  • the austenitic steel is also undesirable not only because its high-temperature strength is not so high at around 400 to 450°C but also from the viewpoint of the entire gas turbine system.
  • the martensitic steel matches other constituent parts and also has a sufficient high-temperature strength.
  • Examples of known martensitic steel include those disclosed in Japanese Patent Laid-Open Nos. 55552/1981, 110661/1983, and 138054/1985 and Japanese Patent Publication No. 279/1971.
  • these materials do not necessarily exhibit a high creep rupture strength at 400 to 450°C and further exhibit low toughness after heating at a high temperature for a long period of time, which renders these materials unsuitable for use in turbine discs. This makes it impossible to improve the efficiency of a gas turbine.
  • An object of the present invention is to provide a heat-resistant steel having a combination of a high strength with a high toughness after heating at a high temperature for a long period of time.
  • Another object of the present invention is to provide a gas turbine having a high thermal efficiency.
  • the present invention relates to a heat-resistant steel characterized in that said heat-resistant steel comprises 0.05 to 0.2% by weight of C, 0.5% by weight or less of Si, 0.6% by weight or less of Mn, 8 to 13% by weight of Cr, 1.5 to 3% by weight of Mo, 2 to 3% by weight of Ni, 0.05 to 0.3% by weight of V, 0.02 to 0.2% by weight in total of either or both of Nb and Ta, and 0.02 to 0.1% by weight of N, the Mn to Ni ratio being 0.11 or less, with the balance being substantially Fe.
  • the present invention also relates to a heat-resistant steel characterized by comprising 0.07 to 0.15% by weight of C, 0.01 to 0.1% by weight or less of Si, 0.1 to 0.4% by weight or less of Mn, 11 to 12.5% by weight of Cr, 2.2 to 3.0% by weight of Ni, 1.8 to 2.5% by weight of Mo, 0.04 to 0.08% by weight in total of either or both of Nb and Ta, 0.15 to 0.25% by weight of V, and 0.04 to 0.08% by weight of N, the Mn to Ni ratio being 0.04 to 0.10, with the balance being substantially Fe and having a wholly tempered martensite structure.
  • the steel of the present invention may additionally comprises at least one member selected from among 1% by weight or less of W, 0.5% by weight or less of Co, 0.5% by weight or less of Cu, 0.01% by weight or less of B, 0.5% by weight or less of Ti, 0.3% by weight or less of A&, 0.1% by weight or less of Zr, 0.1% by weight or less of Hf, 0.01% by weight or less of Ca, 0.01% by weight or less of Mg, 0.01% by weight or less of Y, and 0.01% by weight or less of rare earth elements.
  • the components it is necessary for the components to be adjusted so that the Cr equivalent calculated by the following equation is 10 or less and the steel to be substantially free from 6-ferrite phase. wherein the value with respect to each element is calculated based on the content (% by weight) thereof in the alloy.
  • the present invention also relates to a disc having in its outer circumferential section a plurality of grooves into while blades are embedded, having a maximum thickness in its central section and having on its outer circumferential side through-holes into which bolts are inserted to connect a plurality of said discs, characterized in that said disc is made of a martensitic steel having a wholly tempered martensite structure and having a creep rupture strength of at least 50 kg/mm 2 at 450° C for 10 5 hr and a V-notch Charpy impact value of at least 5 kg-m/cm 2 at 25°C after heating at 500°C for 10 3 hr, or that said disc comprises a heat-resistant steel having the above-described composition.
  • a plurality of turbine discs are connected to each other on the outer circumferential side thereof with bolts through annular spacers.
  • the annular spacer is characterized by being made of a martensitic steel having the above-described properties or a heat-resistant steel having the above-described composition.
  • the present invention also relates to a gas turbine comprising a turbine stub shaft, a plurality of turbine discs connected to said shaft with a turbine stacking bolt through a spacer interposed between said turbine discs, a turbine bucket embedded into said turbine disc, a distance piece connected to said turbine disc with said turbine stacking bolt, a plurality of compressor discs connected to said distance piece with a compressor stacking bolt, a compressor blade embedded into said compressor disc and a compressor stub shaft formed integrally with a first stage disc of said compressor discs, characterized in that at least said turbine disc is made of a martensitic steel having a wholly tempered martensite structure and having a creep rupture strength of at least 50 kg/mm 2 at 450°C for 10 hr and a V-notch Charpy impact value of at least 5 kg-m/cm 2 at 25°C after heating at 500°C for 10 3 hr.
  • the martensitic steel particularly comprises heat-resistant steel having the above-described composition.
  • the application of the above-described martensitic steel to a gas turbine disc according to the present invention makes it possible to limit the ratio of the thickness (t) of the central portion to the outer diameter (D) to 0.15 to 0.3, thereby enabling a reduction in the weight of the disc.
  • the limitation of the ratio to 0.18 to 0.22 enables a decrease in the distance between the discs, so that an improvement in the thermal efficiency can be expected.
  • the content of C should be 0.05% at the lowest.
  • the content of C should be 0.20% or less.
  • the content of C is preferably 0.07 to 0.15%, more preferably 0.10 to 0.14%.
  • Si and Mn are added as a deoxidizer and a deoxidizer-desulfurizer, respectively, in melting a steel. They are effective even when used each in a small amount. Since Si is a 6-ferrite forming element, the addition thereof in a large amount causes the formation of 6-ferrite. Therefore, the Si content should be 0.5% by weight or less. When carbon vacuum deoxidation, electroslag melting, or the like is employed, there is no need of adding Si, so that it is preferred to add no Si.
  • the Si content is particularly preferably 0.2% or less from the viewpoint of embrittlement. Even if no Si is added, Si is contained as an impurity in an amount of 0.01 to 0.1%.
  • the Mn content should be 0.6% or less.
  • the Mn content is preferably 0.1 to 0.4% in order to avoid the thermal embrittlement, more preferably 0.1 to 0.25%. Further, in order to prevent the embrittlement, it is preferred that the total content of Si and Mn be 0.3% or less.
  • Cr enhances the corrosion resistance and high-temperature strength.
  • the addition of Cr in an amount of 13% or more causes the formation of a 5-ferrite structure.
  • the Cr content is less than 8%, the corrosion resistance and the high-temperature strength are unsatisfactory. For this reason, the Cr content was limited to 8 to 13%. In particular, it is preferred from the viewpoint of strength that the Cr content be 11 to 12.5%.
  • Mo not only enhances the creep rupture strength by virtue of its solid solution strengthening and precipitation strengthening actions but also has an effect of preventing the embrittlement.
  • its content is less than 1.5%, no sufficient improvement in the creep rupture strength can be attained.
  • its content is more than 3.0%, 6-ferrite tends to be formed.
  • the Mo content was limited to 1.5 to 3.0%.
  • Mo exhibits such an effect that the higher the Mo content, the higher the creep rupture strength. In particular, this effect is remarkable when the Mo content is 2.0% or above.
  • V and Nb each exhibit an effect of not only enhancing the high-temperature strength but also improving the toughness through precipitation of carbide.
  • V and Nb contents are less than 0.1% and less than 0.02%, respectively, the above-described effect is unsatisfactory, while when the V and Nb contents are more than 0.3% and more than 0.2%, respectively, there is caused a tendency that 6-ferrite is formed and the creep rupture strength is lowered.
  • the V and Nb contents be 0.15 to 0.25% and 0.04 to 0.08%, respectively.
  • Ta may be added instead of Nb in exactly the same amount as that of Nb. Further, Nb and Ta may be added in combination.
  • Ni has effects of not only enhancing the toughness after heating at a high temperature for a long period of time but also preventing the formation of 6-ferrite.
  • the Ni content is preferably 2.2 to 3.0%, more preferably more than 2.5%.
  • Ni has an effect of preventing the thermal embrittlement.
  • Mn has an adverse effect on the prevention of the thermal embrittlement.
  • the present inventors have found that there is a close correlation between these elements. Namely, the present inventors have found that the thermal embrittlement can be remarkably prevented when the Mn to Ni ratio is 0.11 or less. In particular, the ratio is preferably 0.10 or less, more preferably 0.04 to 0.10.
  • N has effects of improving the creep rupture strength and preventing the formation of 6-ferrite.
  • the above-described effect is unsatisfactory.
  • the toughness is lowered.
  • excellent properties can be attained when the N content ranges from 0.04 to 0.08%.
  • Co enhances the strength but promotes the embrittlement. Therefore, the Co content should be 0.5% or less.
  • W contributes to an increase in the strength and may be contained in an amount of 1% or less.
  • the high-temperature strength may be improved by addition of 0.01% of B, 0.3% or less of Al, 0.5% or less of Ti, 0.1% or less of Zr, 0.1% or less of Hf, 0.01% or less of Ca, 0.01% or less of Mg, 0.01% or less of Y, 0.01% or less of rare earth elements, and 0.5% or less of Cu.
  • the material is uniformly heated at a temperature sufficient to cause a complete transformation thereof to austenite, i.e., at 900°C at the lowest and 1150°C at the highest, thereby forming a martensite structure.
  • the material is then quenched at a cooling rate of at least 100°C/hr, heated and held at a temperature of 450 to 600°C (first tempering), and then heated and held at a temperature of 550 to 650°C for second tempering.
  • first tempering it is preferred to stop the quenching at a temperature immediately above the Ms point for the purpose of preventing the occurrence of quenching crack. More particularly, it is preferred to stop the quenching at a temperature of 150°C or above. It is preferred to carry out the hardening by oil hardening or water spray hardening.
  • the first tempering is begun from the temperature at which the quenching is stopped.
  • One or more of the above-described distance piece, turbine spacer, turbine stacking bolt, compressor stacking bolt, and at least a final stage disc of the compressor discs may be made of a heat-resistant steel having a wholly tempered martensite structure and comprising 0.05 to 0.2% by weight of C, 0.5% by weight or less of Si, 1% by weight or less of Mn, 8 to 13% by weight of Cr, 3% by weight or less of Ni, 1.5 to 3% by weight of Mo, 0.05 to 0.3% by weight of V, 0.02 to 0.2% by weight of Nb, and 0.02 to 0.1% by weight of N with the balance being substantially Fe.
  • a highly safe turbine having a high resistance to embrittlement can be realized when at least one of the above-described parts is made of a heat-resistant steel comprising 0.05 to 0.2% by weight of C, 0.5% by weight or less of Si, 0.6% by weight or less of Mn, 8 to 13% by weight of Cr, 2 to 3% by weight of Ni, 1.5 to 3% by weight of Mo, 0.05 to 0.3% by weight of V, 0.02 to 0.2% by weight of Nb, and 0.02 to 0.1% by weight of N with the balance being substantially Fe, the Mn to Ni ratio being 0.11 or less, particularly 0.04 to 0.10, and having a wholly tempered martensite structure.
  • a martensitic steel having a creep rupture strength of at least 40 kg/mm 2 at 450°C for 10 5 hr and a V-notch Charpy impact value of at least 5 kg-m/cm 2 at 20°C is used as a material for these parts.
  • the steel has a creep rupture strength of at least 50 kg/ mm 2 at 450° C for 10 5 hr and a V-notch Charpy impact value of at least 5 kg-m/cm 2 at 20°C after heating at 500°C for 10 3 hr.
  • This material may further contain at least one member selected from among 1% or less of W, 0.5% or less of Co, 0.5% or less of Cu, 0.01% or less of B, 0.5% or less of Ti, 0.3% or less of A2, 0.1% or less of Zr, 0.1% or less of Hf, 0.01% or less of Ca, 0.01% or less of M g, 0.01% or less of Y, and 0.01% or less of rare earth elements.
  • At least the final stage disc or discs of all stages among the compressor discs may be made of the above-described heat-resistant steel.
  • other low-alloy steel may be used for the discs in this zone, and the above-described heat-resistant steel may be used for the discs in a zone from the middle stage to the final stage.
  • Ni-Cr-Mo-V steel comprising 0.15 to 0.30% by weight of C, 0.5% by weight or less of Si, 0.6% by weight or less of Mn, 1 to 2% by weight of Cr, 2.0 to 4.0% by weight of Ni, 0.5 to 1% by weight of Mo, and 0.05 to 0.2% by weight of V with the balance being substantially Fe and having a tensile strength of at least 80 kg/mm 2 at room temperature and a V -notch Charpy impact value of at least 20 kg-m/cm 2 at room temperature, and for the discs from the middle stage except for the final stage, it is possible to use a Cr-Mo-V steel comprising 0.2 to 0.4% by weight of C, 0.1 to 0.5% by weight of Si, 0.5 to 1.5% by weight of Mn, 0.5 to 1.5% by weight of Cr, 0.5% by weight or less of Ni, 1.0 to 2.0% by weight of Mo
  • the above-described Cr-Mo-V steel may be used for a compressor shaft and a turbine shaft.
  • the compressor disc of the present invention has a circular shape and is provided over the entire periphery of the outer portion with a plurality of holes for inserting stacking bolts, and it is preferred that the ratio of the minimum thickness (t) of the compressor disc to the diameter (D) thereof (t/D) be 0.05 to 0.10.
  • the distance piece of the present invention has a cylindrical shape and is provided on its both ends with flanges for connecting both ends of the distance piece to the compressor disc and the turbine disc, respectively, with bolts and it is preferred that the ratio of the minimum thickness (t) to the maximum inner diameter (D) thereof (t/D) be 0.05 to 0.10.
  • the ratio of the spacing (Q) between individual gas turbine discs to the diameter (D) of the disc (£/D) be 0.15 to 0.25.
  • the discs from the first stage to the 12th stage, the discs from the 13th stage to the 16th stage, and the disc of the 17th stage may be made of the above-described Ni-Cr-Mo-V steel, the above-described Cr-Mo-V steel, and the above-described martensitic steel, respectively.
  • the first-stage disc has higher rigidity than that of the disc subsequent thereto, and the final-stage disc has higher rigidity than that of the disc preceding it. Further, this disc assembly has such a structure that the thickness of the discs is gradually reduced from the first stage towards the final stage to reduce the stress caused by high-speed rotation.
  • the blade of the compressor be made of a martensitic steel comprising 0.05 to 0.2% of C, 0.5% or less of Si, 1% or less of Mn, and 10 to 13% of Cr and optionally 0.5% or less of Mo and 0.5% or less of Ni with the balance being Fe.
  • the first stage of the shrouds which are formed in a ring shape and are in sliding contact with the leading end of the turbine blade is made of a cast alloy comprising 0.05 to 0.2% by weight of C, 2% by weight or less of Si, 2% by weight or less of Mn, 17 to 27% by weight of Cr, 5% or less of Co, 5 to 15% by weight of Mo, 10 to 30% by weight of Fe, 5% by weight or less of W , and 0.02% by weight or less of B with the balance being substantially Ni, while the other stages of the shrouds are each made of a cast alloy composed of 0.3 to 0.6% by weight of C, 2% by weight or less of Si, 2% or less of Mn, 20 to 27% by weight of Cr, 20 to 30% by weight of Ni, 0.1 to 0.5% by weight of Nb, and 0.1 to 0.5% by weight of Ti with the balance being substantially Fe.
  • These alloys are formed into a ring-shaped structure with a plurality of blocks.
  • the diaphragm for the first-stage turbine nozzle is made of a Cr-Ni steel comprising 0.05% by weight or less of C, 1% by weight or less of Si, 2% by weight or less of Mn, 16 to 22% by weight of Cr, and 8 to 15% by weight of Ni with the balance being substantially Fe, while the diaphragms for the other turbine nozzles are each made of a high C-high Ni cast alloy.
  • the turbine blade is made of a cast alloy comprising 0.07 to 0.25% by weight of C, 1% by weight or less of Si, 1% by weight or less of Mn, 12 to 20% by weight of Cr, 5 to 15% by weight of Co, 1.0 to 5.0% by weight of Mo, 1.0 to 5.0% by weight of W, 0.005 to 0.03% by weight of B, 2.0 to 7.0% by weight of Ti, and 3.0 to 7.0% by weight of AQ and at least one member selected from among 1.5% by weight or less of Nb, 0.01 to 0.5% by weight of Zr, 0.01 to 0.5% by weight of Hf, and 0.01 to 0.5% by weight of V with the balance being substantially Ni and having a structure in which a y' phase and a y" phase are precipitated in an austenite phase matrix.
  • the turbine nozzle is made of a cast alloy comprising 0.20 to 0.60% by weight of C, 2% by weight or less of Si, 2% by weight or less of M n, 25 to 35% by weight of Cr, 5 to 15% by weight of Ni, 3 to 10% by weight of W , 0.003 to 0.03% by weight of B with the balance being substantially Co and further optionally at least one member selected from among 0.1 to 0.3% by weight of Ti, 0.1 to 0.5% by weight of Nb and 0.1 to 0.3% by weight of Zr, and having a structure in which eutectic carbide and secondary carbide are contained in an austenite phase matrix.
  • These alloys are subjected to an aging treatment subsequent to a solution treatment to form the above-described precipitates, thereby strengthening the alloys.
  • a diffusion coating made of Ak, Cr, or Ak + Cr may be applied to the turbine blade. It is preferred that the coating layer have a thickness of 30 to 150 ⁇ m and be provided on the blade which are exposed to the gas.
  • a plurality of combustors are provided around the turbine and each have a dual structure comprising outer and inner cylinders.
  • the inner cylinder is made of 0.05 to 0.2% by weight of C, 2% by weight or less of Si, 2% by weight or less of Mn, 20 to 25% by weight of Cr, 0.5 to 5% by weight of Co, 5 to 15% by weight of Mo, 10 to 30% by weight of Fe, 5% by weight or less of W, and 0.02% by weight or less of B with the balance being substantially Ni.
  • the inner cylinder is manufactured by welding the material in the form of a plate which has been subjected to plastic working to have a thickness of 2 to 5 mm and provided over the whole periphery of the cylinder body with crescent louver holes for suppling air.
  • the material for the inner cylinder is a solution-treated material having a wholly austenite structure.
  • Fig. 1 is a cross-sectional view of the rotary section of an example of a gas turbine according to the present invention
  • Fig. 2 a diagram showing the relationship between the impact value after embrittlement and the Mn to Ni ratio
  • Fig. 3 a diagram showing the relationship between the impact value after embrittlement and the Mn content
  • Fig. 4 a diagram showing the relationship between the impact value after embrittlement and the Ni content
  • Fig. 5 a diagram showing the relationship between the creep rupture strength and the Ni content
  • Fig. 6 a cross-sectional view of an example of a turbine disc according to the present invention
  • Fig. 7 a partial sectional view around the rotary section of an example of a gas turbine according to the present invention.
  • Samples respectively having the compositions (in % by weight) shown in Table 1 were melted in an amount of 20 kg and heated at 1150°C, followed by forging to prepare experimental materials. These materials were heated at 1150°C for 2 hr and then subjected to air blast cooling. The cooling was stopped when the temperature reached 150°C. Then, a first tempering was conducted by heating the materials from that temperature to 580°C, maintaining the temperature for 2 hr and then subjecting the materials to air cooling. Thereafter, a second cooling was conducted by heating the materials at 605°C for 5 hr and then cooling them in a furnace.
  • Test pieces for a creep rupture test, a tensile test, and a V-notch Charpy impact test were sampled from the materials after heat treatment and applied to the experiments.
  • the impact test was conducted on an embrittled material prepared by heating at 500°C for 1000 hr a material as heat-treated. This embrittled material corresponds to a material heated at 450°C for 10 5 hr according to the Larson-Miller parameter.
  • samples Nos. 1 and 8 are materials according to the present invention
  • samples Nos. 2 to 7 are comparative materials
  • sample No. 2 is a material corresponding to M152 steel which is currently used as a material for discs.
  • Fig. 2 is a diagram showing the relationship between the impact value after embrittlement and the Mn to Ni ratio. As shown in this figure, no significant difference in the effect is observed when the Mn to Ni ratio is 0.12 or more. However, when the ratio is 0.11 or less, the resistance to embrittlement is greatly improved, and the impact value is at least 4 kg-m (5 kg-m/cm 2 ). Further, when the ratio is 0.10 or less, the impact value is as high as 6 kg-m (7.5 kg-m/cm 2 ). M n is indispensable as a deoxidizer and a desulfurizer, and it is necessary that Mn should be added in an amount of 0.6% or less.
  • Fig. 3 is a diagram showing the relationship between the impact value after embrittlement and the Mn content.
  • the Ni content is 2.1% or less, no significant effect on the impact value after embrittlement can be attained even by reducing the Mn content, while when the Ni content exceeds 2.1%, a reduction in the Mn content brings about a significant effect.
  • the Ni content is 2.4% or more, a remarkable effect can be attained.
  • the Mn content is around 0.7%, no improvement in the impact value is attained irrespective of the Ni content.
  • the Mn content is 0.6% or less and the Ni content is at least 2.4%, the lower the Mn content, the higher the impact value.
  • Fig. 4 is a diagram showing the relationship between the impact value after embrittlement and the Ni content.
  • the Mn content is at least 0.7%, no significant improvement in the resistance to the embrittlement can be attained even by increasing the Ni content, while when the Mn content is less than 0.7%, the resistance to the embrittlement is significantly improved with an increase in the Ni content.
  • the Mn content is 0.15 to 0.4% and the Ni content is at least 2.2%, a remarkable improvement can be attained.
  • the impact value is 6 kg-m (7.5 kg-m/cm 2 ) or more
  • the Ni content is 2.5% or more
  • the impact value is 7 kg-m/cm 2 or more.
  • Fig. 5 is a diagram showing the relationship between the creep rupture strength at 450°C for 10 5 hr and the Ni content. As shown in this figure, a Ni content up to about 2.5% has no significant effect on the strength. However, when the Ni content exceeds 3.0%, the creep rupture strength is less than 50 kg/mm 2 , so that no intended strength can be attained. It is noted that the strength is increased with a lowering in the Mn content and the most remarkable strengthening, i.e., the highest strength, can be attained when the Mn content is about 0.15 to 0.25%.
  • Fig. 6 is a cross-sectional view of a gas turbine disc according to the present invention. The chemical composition (in % by weight) is shown in Table 3.
  • the melting of the steel material was conducted by carbon vacuum deoxidation. After the completion of the forging, the steel was heated at 1050°C for 2 hr and hardened in an oil of 150°C. Tempering was then conducted by heating the steel from that temperature, maintaining the temperature at 520°C for 5 hr and cooling the steel with air. Thereafter, further tempering was conducted by heating the steel at 590°C for 5 hr and cooling the heated steel in a furnace. After the completion of the heat treatment, the steel was machined into a shape shown in the drawing, and the formed disc had an outer diameter of 1000 mm and a thickness of 200 mm. The diameter of a center hole 11 is 65 mm.
  • Numeral 12 designates a section in which are provided holes into which stacking bolts are inserted
  • numeral 13 designates a section in which a turbine blade is embedded.
  • This disc exhibited excellent properties, i.e., an impact value of 8.0 kg-m (10 kg-m/cm 2 ) after embrittlement under the same conditions as those described above and a creep rupture strength of 55.2 kg/mm 2 at 450°C for 10 5 hr.
  • Fig. 1 is a cross-sectional view of the rotary section of an example of a gas turbine in which the above-described disc is used according to the present invention.
  • Numeral 1 designates a turbine stub shaft, numeral 2 a turbine bucket, numeral 3 a turbine stacking bolt, numeral 4 a turbine spacer, numeral 5 a distance piece, numeral 6 a compressor disc, numeral 7 a compressor blade, numeral 8 a compressor stacking bolt, numeral 9 a compressor stub shaft, numeral 10 a turbine disc, and numeral 11 a center hole.
  • the number of stages of the compressor discs 6 is 17, and the number of stages of the turbine buckets 2 is 2.
  • the number of stages of the turbine buckets 2 may be 3.
  • the steel of the present invention can be applied to both cases.
  • the distance piece had a size of 60 mm in thickness x 500 mm in width x 1000 mm in length, while the compressor disc had a diameter of 1000 mm and a thickness of 180 mm.
  • Sample No. 7 was used for production of a disc having a size of 1000 mm in diameter x 180 mm in thickness
  • sample No. 8 was used for production of a spacer having a size of 1000 mm in outer diameter x 400 mm in inner diameter x 100 mm in thickness
  • sample No. 9 was used for production of a stacking bolt having a size of 40 mm in diameter x 500 mm in length for both of the turbine and the compressor.
  • Sample No. 9 was also used for production of a bolt for connecting the distance piece to the compressor disc.
  • test pieces except for sample No. 9 were extracted from the central portion of the samples in a direction perpendicular to the axial (longitudinal) direction thereof. In this example, the test piece was extracted in the longitudinal direction of the sample.
  • Table 5 shows the results of the tensile strength test at room temperature, the V-notch Charpy impact test at 20°C and the creep rupture strength test.
  • the creep rupture strength at 450°C for 10 hr was determined according to a commonly used method, i.e., Larson-Miller method.
  • Samples Nos. 6 to 9 (12Cr steel) according to the present invention had a creep rupture strength of at least 51 kg/mm 2 at 450°C for 10 5 hr and a V-notch Charpy impact value of 7 kg-m/cm at 20°C. Therefore, it has been confirmed that samples Nos. 6 to 9 satisfy the requirement for the strength of the material for a high-temperature gas turbine.
  • Samples Nos. 10 and 11 for the stub shaft exhibited a low creep rupture strength at 450°C but had a tensile strength of 86 kg/mm2 or more and a V-notch Charpy impact value of 7 kg-m/cm or more at 20°C. Therefore, it has been confirmed that these samples satisfy the requirement for the strength of the stub shaft (tensile strength ⁇ 81 kg/mm 2 ; and a V -notch Charpy impact value at 20°C ⁇ 5 kg- m/cm 2 ) .
  • the gas turbine of the present invention made of a combination of the above-described materials enables the adoption of a compression ratio of 14.7, a temperature of 350°C or above, a compressor efficiency of 86% or more, a gas temperature of about 1200°C in the inlet of the first-stage nozzle, which brings about a thermal efficiency (LHV) of 32% or more.
  • the temperature of both the distance piece and the final-stage compressor disc reaches 450°C at the highest. It is preferred that the thickness of the distance piece and that of the final-stage compressor disc be 25 to 30 mm and 40 to 70 mm, respectively.
  • the turbine and the compressor disc are each provided at its central portion with a through-hole. A compressive residual stress is caused at the through-hole of the turbine disc.
  • the heat-resistant steel shown in the above-described Table 3 was used for production of the turbine spacer 4, the distance piece 5, and the final stage of the compressor disc 6, and the other parts were produced by using the same steels as those described above, thereby forming a gas turbine of the present invention.
  • This gas turbine enabled the adoption of a compression ratio of 14.7, a temperature of 350°C or above, a compression efficiency of 86% or more, and a gas temperature of 1200°C at the first-stage nozzle inlet. Consequently, it becomes possible to attain not only a thermal efficiency of 32% or more but also, as described above, a high creep rupture strength and a high impact strength after thermal embrittlement, thus realizing the formation of a more reliable gas turbine.
  • Fig. 7 is a partial sectional view of the rotary section of an example of a gas turbine having a gas turbine disc made of the heat-resistant steel according to the present invention:
  • the number of stages of the gas turbine discs 10 in this example are 3.
  • the first stage and the second stage on the upstream side of the gas flow are each provided with a center hole 11.
  • each of the turbine discs is made of the heat-resistant steel shown in Table 3.
  • the heat-resistant steel shown in the above-described Table 3 was used for the final stage of the compressor disc 6 on the downstream side of the gas flow, the distance piece 5, the turbine spacer 4, the turbine stacking bolt 3, and the compressor stacking bolt 8.
  • the alloys shown in Table 6 were used for construction of the other parts, i.e., the turbine blade 2, the turbine nozzle 14, the liner 17 of the combustor 15, the compressor blade 7, the compressor nozzle 16, the diaphragm 18, and the shroud 19.
  • the turbine nozzle 12 and the turbine blade 2 were made of a casting.
  • the number of stages of the compressor discs in this example was 17, and the discs were arranged in the same manner as that of Example 2.
  • the turbine stub shaft 1 and the compressor stub shaft 9 were each also constructed in the same manner as that of Example 2.
  • the final stage of the compressor disc 6 has a ratio (t/D) of the minimum thickness (t) to the outer disameter (D) of 0.08
  • the distance piece 5 has a ratio (t/D) of the minimum thickness (t) to maximum inner diameter (D) of 0.04.
  • the ratio (t/D) of the maximum thickness (t) of the central section of the turbine disc to the diameter (D) thereof is 0.19 in the case of the first stage and 0.205 in the case of the second stage, and the ratio (£/D) of the spacing (Q) between the discs to the diameter (D) thereof is 0.21.
  • a spacing is provided between the turbine discs.
  • the turbine disc is provided over the entire periphery with a plurality of holes at equal intervals for inserting the bolts for the purpose of connecting the discs.
  • the above-described construction enables the adoption of a compression ratio of 14.7, a temperature of 350°C or above, a compression efficiency of 86% or more, a gas temperature of 1200°C at the inlet of the first-stage turbine nozzle, which brings about a thermal efficiency of 32% or more.
  • a heat-resistant steel which has a high creep rupture strength and is less susceptible to thermal embrittlement can be used for the turbine disc, the distance piece, the spacer, the final stage of the compressor disc, and the stacking bolt.
  • the present invention enables the formation of a heat-resistant steel satisfying the requirements for the creep rupture strength and the impact value after thermal embrittlement of a high-temperature and high-pressure gas turbine disc (a gas temperature of 1200°C or above; and a compression ratio of about 15).
  • the gas turbine comprising this material exhibits an excellent effect of attaining a remarkably high thermal efficiency.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Acier résistant à la chaleur comportant, en pourcentage du poids, de 0,05 à 0,2 % de C, jusqu'à 0,5 % de Si, jusqu'à 0,6 % de Mn, de 8 à 13 % de Cr, de 1,5 % à 3 % de Mo, de 2 à 3 % de Ni, de 0,05 à 0,3 de V, au moins un élément parmi le Nb et le Ta, la somme étant comprise entre 0,02 et 0,2 %, de 0,02 à 0,1 % de N, le rapport Mn/Ni allant jusqu'à 0,11, le solde étant essentiellement du Fe. L'acier résistant à la chaleur ci-décrit est utilisé au moins pour un disque d'une turbine à gaz comprenant un arbre de turbine, une pluralité de disques de turbine reliés à l'arbre et comportant entre chaque élément des entretoises représentées par des boulons d'empilement de turbine, des ailettes de turbine implantées dans les disques, une pièce éloignée reliée au disque par les boulons, une pluralité de disques compresseurs reliés à la pièce éloignée par des boulons d'empilement de compresseur, des pales de compresseur implantées dans les disques de compresseur et un faux arbre de compresseur façonné en une seule pièce avec l'étage initial du disque de compresseur. En outre, l'acier résistant à la chaleur ci-décrit peut être utilisé pour les boulons d'empilement, les entretoises, les pièces éloignées et les pales de compresseur. Cet acier résistant à la chaleur présente des caractéristiques telles qu'une résistance à la rupture par fluage d'au moins 50 kg/mm2 à 450°C pendant 10 105 heures et un valeur d'essai de choc de Charpy à entaille en V à 35°C au moins égale à 5 kg/cm2 après traitement thermique à 500°C pendant 103 heures.
EP88900787A 1987-01-09 1988-01-06 Acier resistant a la chaleur et turbine a gaz composee de cet acier Expired - Lifetime EP0298127B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP62001630A JPS63171856A (ja) 1987-01-09 1987-01-09 耐熱鋼
JP1630/87 1987-01-09
PCT/JP1988/000007 WO1988005086A1 (fr) 1987-01-09 1988-01-06 Acier resistant a la chaleur et turbine a gaz composee de cet acier

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EP0298127A1 true EP0298127A1 (fr) 1989-01-11
EP0298127A4 EP0298127A4 (en) 1993-05-26
EP0298127B1 EP0298127B1 (fr) 1996-07-31

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EP (1) EP0298127B1 (fr)
JP (1) JPS63171856A (fr)
KR (2) KR950014312B1 (fr)
CN (1) CN1036666C (fr)
WO (1) WO1988005086A1 (fr)

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EP0759499A1 (fr) * 1995-08-21 1997-02-26 Hitachi, Ltd. Installation de turbines à vapeur et turbine à vapeur
WO1997039158A1 (fr) * 1996-04-12 1997-10-23 Abb Research Ltd. Acier martensitique-austenitique
EP0831203A2 (fr) * 1996-09-24 1998-03-25 Hitachi, Ltd. Aubage pour une turbine à vapeur d'une installation à cycle combiné gaz-vapeur
US5749228A (en) * 1994-02-22 1998-05-12 Hitachi, Ltd. Steam-turbine power plant and steam turbine
EP0881360A1 (fr) * 1996-02-16 1998-12-02 Hitachi, Ltd. Installation de production d'energie par turbine a vapeur et cette turbine
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METAL PROGRESS, vol. 120, mid-June 1981, pages 90-91, Am. Soc. for Metals, Metals Park, Ohio, US; "Cobalt-base alloys" *
METAL PROGRESS, vol. 120, mid-June 1981, pages 90-91, Am. Soc. for Metals, Metals Park, Ohio, US; "Cobalt-base alloys" * Alloy: "FSX-414" * *
See also references of WO8805086A1 *

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0384181A3 (fr) * 1989-02-03 1990-12-05 Hitachi, Ltd. Arbre de turbine à vapeur et acier réfractaire pour cet arbre
EP0384181A2 (fr) * 1989-02-03 1990-08-29 Hitachi, Ltd. Arbre de turbine à vapeur et acier réfractaire pour cet arbre
US6123504A (en) * 1994-02-22 2000-09-26 Hitachi, Ltd. Steam-turbine power plant and steam turbine
US6174132B1 (en) 1994-02-22 2001-01-16 Hitachi, Ltd. Steam-turbine power plant and steam turbine
US5749228A (en) * 1994-02-22 1998-05-12 Hitachi, Ltd. Steam-turbine power plant and steam turbine
EP0759499A1 (fr) * 1995-08-21 1997-02-26 Hitachi, Ltd. Installation de turbines à vapeur et turbine à vapeur
EP0881360A1 (fr) * 1996-02-16 1998-12-02 Hitachi, Ltd. Installation de production d'energie par turbine a vapeur et cette turbine
EP0881360A4 (fr) * 1996-02-16 2000-03-08 Hitachi Ltd Installation de production d'energie par turbine a vapeur et cette turbine
WO1997039158A1 (fr) * 1996-04-12 1997-10-23 Abb Research Ltd. Acier martensitique-austenitique
EP0831203A3 (fr) * 1996-09-24 2000-04-19 Hitachi, Ltd. Aubage pour une turbine à vapeur d'une installation à cycle combiné gaz-vapeur
US6074169A (en) * 1996-09-24 2000-06-13 Hitachi, Ltd. High and low pressure sides-integrating steam turbine, long blades thereof and combined cycle power generation system
EP0831203A2 (fr) * 1996-09-24 1998-03-25 Hitachi, Ltd. Aubage pour une turbine à vapeur d'une installation à cycle combiné gaz-vapeur
US6182439B1 (en) 1996-09-24 2001-02-06 Hitachi, Ltd. High and low pressure sides-integrating system turbine, long blades thereof and combined cycle power generation system
CN105648356A (zh) * 2014-12-02 2016-06-08 现代自动车株式会社 具有优越的高温强度和抗氧化性的耐热铸钢
CN105648356B (zh) * 2014-12-02 2020-11-03 现代自动车株式会社 具有优越的高温强度和抗氧化性的耐热铸钢
CN117305726A (zh) * 2023-08-21 2023-12-29 北京首钢吉泰安新材料有限公司 一种耐热腐蚀钢合金及其制备方法与应用

Also Published As

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JPH0563544B2 (fr) 1993-09-10
CN1036666C (zh) 1997-12-10
JPS63171856A (ja) 1988-07-15
WO1988005086A1 (fr) 1988-07-14
KR950009221B1 (ko) 1995-08-18
CN88100065A (zh) 1988-10-05
KR890700690A (ko) 1989-04-26
KR950014312B1 (ko) 1995-11-24
EP0298127A4 (en) 1993-05-26
EP0298127B1 (fr) 1996-07-31

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