Classifications

• • 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 more particularly to a novel gas turbine using the heat-resistant steel.
• Cr-Mo-V steel is used for gas turbine discs.
• JP-A-56-55552, JP-A-58-11066, 60-13854, and JP-B-46-279 are known.
• these materials do not always have high creep rupture strength at 400 to 450 ° C, and have low toughness after long-time heating at high temperatures, making them unusable as turbine disks.
• gas turbine efficiency cannot be improved.
• An object of the present invention is to provide a heat-resistant steel having both high-temperature strength and high toughness after high-temperature long-time heating.
• An object of the present invention is to provide a gas turbine with high thermal efficiency.
• the present invention is based on the weight, C 0.05-0.2 ° /. , S i 0 . ⁇ % or less, ⁇ II 0 .S% or less, Cr 8 to: L 3%, Mo 1.5 to 3%, Ni 2 to 3. /. , V. 0.05 to 0.3%, and the total amount of one or two of Nb and Ta is G. 0 '2 to 0.2% and N 0.02 to 0.1%.
• the (M II ZN i) ratio is 0.1 1
• the present invention is based on the followings: W 1% or less, Co 0.5% or less, CuO 0.5% or less, 80.0 1% or less, ⁇ 0.5% or less, -A J2 0.3% or less, Zr 0.1% or less, Hf 0.1% or less, Ca 0.01% or less, Mg 0.01% or less, Y0.01% or less, and rare earth element 0.01% or less It contains at least one species.
• the present invention has a disk-like shape, and has a concave wing-implanted portion in which wings are implanted in an outer peripheral portion of the disk-like shape, and has a maximum thickness at a center portion of the disk, in a disk having a structure for connecting a plurality of the disc by said bolts has a through-hole you ⁇ the bolt, the disk 1 0 5 hour click Li Ichipu breaking strength at 4 5 0 ° C There 5 0 kg Z mm 2 or more and on 5 0 '0 ° C in ⁇ 0 3 hours V notch Charpy impact value of 2 5 ° C after heating 5 kg-m Z cnf more than is burnt back Mar sugarbeet preparative tissue It is characterized by being composed of a martensitic steel having the following composition, and further composed of a heat-resistant steel having the composition described above.
• the plurality of turbine disks are connected by bolts on the outer peripheral side of the disks via ring-shaped spacers, and the plurality of turbine disks are connected to a martensite system having the above-described characteristics. Characterized by being composed of heat-resistant steel having the following composition:
• Each of the compressor disks having the following thicknesses is made of a martensite steel having the above-described characteristics or a heat-resistant steel having the above-described composition.
• the present invention relates to a turbine stub shaft, a plurality of turbine disks connected to the shaft by spacers via a spacer, and a plurality of turbine disks.
• a turbine bucket implanted in the disk, a discrete piece connected to the disk by the bolt, and a complex sustaining bolt on the discrete piece.
• This V Roh pitch Charpy impact value of 2 5 ° C after heating 5 kg- m / cm 2 or more is burnt back Marte Nsai preparative tissue ing Marte Nsai DOO steels or found with which the It is in a gas turbine bin characterized by the following.
• Martensitic steel is composed of heat-resistant steel with the above composition
• the ratio (t ZD) of the center diameter (t) to the outer diameter (D) can be set to 0.15 to 0.3 by applying the above-mentioned martensite ⁇ . It is possible to reduce the weight. In particular, 0 ..
• the distance between the discs can be reduced, and improvement in thermal efficiency can be expected.
• C is required to be at least 0,05% in order to obtain high tensile strength and strength.
• Ri metal structure unstable Na if it is a long time is et to a high temperature, so reducing the 1 0 5 h click Li Ichipu breaking strength, to 0.20% or less Don't do it.
• it is from 0.07 to 0.15%. -0.1% to 0.14% is preferred
• Si is a deoxidizing agent
• Mn is a deoxidizing and desulfurizing agent added during the dissolution of ⁇ , and is effective even in small amounts.
• S i is
• the embrittlement point force is preferably 0.2% or less, and even if no Si is added, the content is 0.0 to 0.1% as an impurity.
• Mn promotes embrittlement by heating, G.6% or less Should be below.
• Mn is effective as a desulfurizing agent, its content is preferably 0.1 to 0.4% so as not to cause heating embrittlement. Further, 0.1 to 0.25% is most preferable.
• the amount of Si + Mn is set to 0.3 in order to prevent embrittlement. It is preferred that:
• Cr enhances corrosion resistance and high-temperature strength, but when added in an amount of 13% or more, it causes the formation of ⁇ ferrite structure. If less than 8%, the corrosion resistance and high-temperature strength are insufficient, so Cr was determined to be 8 to 13%. From the viewpoint of strength, 1% to 12.5% is particularly preferable.
• ⁇ 0 has the effect of strengthening the clip breaking strength by strengthening the solid solution and prayer, and at the same time has the effect of preventing embrittlement.
• ⁇ When the content is 1.5% or less, the effect of improving the creep rupture strength is insufficient, and when the content is 3.0% or more, ferrite is generated. Therefore, 1.5 to 3.0%. It is particularly preferable that the content is limited to about 0.8 to 2.5%. Furthermore, when the content of Ti exceeds 2.1%, the greater the content of Mo, the more effective the creep rupture strength is, especially when the content of Mo is more than 2.0%. The effect is great.
• V and Nb increase the high-temperature strength by praying carbides and have the effect of improving toughness. If the VG is less than .1% and b0.02%, the effect is not enough. If it is more than V0.3% and Nb0.2%, it causes the generation of S ferrite and Clearness / breaking strength tends to decrease, especially V 0.15 ⁇ 0 : .25%, Nb 0.04 ⁇ 0.08% is preferred.
• T a can be added in exactly the same manner, and multiple additions can be made.
• Ni has the effect of increasing the toughness after high-temperature and long-time heating, and has the effect of preventing the formation of S ferrite. If it is 2.0% or less, the effect is not sufficient, and if it is 3% or more, the creep rupture strength for a long time is reduced. More preferably, it is in excess of 2.5%.
• N i impairs the prevention of heat embrittlement, while M n does harm. Therefore, the present inventors have found that there is a close correlation between these elements. That is, it has been found that by setting the ratio of MIINi to 0.11 or less, force [I thermal embrittlement can be prevented very significantly. In particular, 0.10 or less is preferred, and 0.04 to 0.10 is preferred.--N is effective for improving creep cut strength and preventing S ferrite generation, but when it is less than 0.02% The effect is not enough, 0.1 ° /. Beyond this decreases toughness-especially
• the C.o of the shochu fever according to the present invention is strengthened but promotes embrittlement, and therefore should be set to 0.5% or less. Since W contributes to strengthening in the same manner as Mo, it can contain up to 1% of BO. 1% or less, A £ G. 3% i3 ⁇ 4, T i G.5% or less, Zr 0.1% 3 ⁇ 4 below, H f 0.]% i 3 ⁇ 4 below, C a 0.0 ⁇ %
• the high temperature strength can be improved by including Mg 0.01% or less, Y 0.01% or less, rare earth 0.01% or less, and Cu 0.5% or less. it can.
• the material is uniformly heated to a temperature sufficient to transform completely into austenite, at least 900 ° C, and at most 115 ° C, to obtain a martensite structure.
• Rapid cooling at a speed of 100 ° C or higher, then 450-600.
• Heat and hold at the temperature of C (first tempering), then heat and hold at a temperature of 550 to 650 to perform second tempering.
• first tempering it is preferable to keep the temperature just above the M s point in order to prevent quenching.
• the specific temperature should be kept at 150 ° C or higher.
• the quenching is preferably performed by quenching in oil or water mist.
• the first tempering heats more than the temperature.
• the above-mentioned distorted pieces, tooling bases, tooling tacking bolts, compressors, tacking bolts and compressor discs At least one of the last stages is C 0.05-0.2%, Si 0.5% or less, Mn 1% or less, Cr 8-13%, i 3 % Or less, Mo 1.5 to 3%, V 0.05 to 0.3%, Nb 0.02 to 0.2%, X ⁇ 0.2 to 0.1%, and the balance substantially
• the heat-resistant steel can be composed of a heat-resistant steel having a fully-burned martensite structure composed of Fe. By setting the temperature, a higher gas temperature can be obtained, and the thermal efficiency can be improved. In particular, at least one of these parts is by weight, C 0.05-0.2,
• These materials further include W 1% or less, Co 0.5% or less, Cu 0.5% or less, B 0.5% or less, Ti 0.5% or less, A ⁇ 0.5% or less. 3% ⁇ bottom, Zr 0.1% or less, Hf 0.1
• At least the last stage of the compressor disk or the entire stage can be made of the above-mentioned heat-resistant steel, but since the gas temperature is low from the first stage to the center, other low-alloy steels can be used.
• the heat-resistant steel described above can be used from the center to the final stage.
• the weight from the first stage upstream of the gas to the center is C 0.15 to 0.30%, Si 0.5% or less, Mn 0.6% or less, and Cr 1 to 2 %, Ni 2.0 to 4.0%, Mo 0.5 to 1.%, V 0.05 to 0.2
• the compressor stub shaft and the turbine stub shaft can use the above-mentioned Cr-Mo-V steel: the compressor of the present invention.
• Thousand disks are disc-shaped, A plurality of holes for inserting a stacking bolt are provided around the entire circumference, and the ratio (tZD) of the thickness (t) to the minimum thickness (t) of the compressor disk (D) is 0.0. Five ⁇
• the distance piece according to the present invention has a cylindrical shape and is provided with a flange connected at both ends to a compressor disk and a single disk by bolts, and has a minimum diameter corresponding to the maximum inner diameter (D). It is preferable that the ratio (tZD) to the wall thickness (t) is set to 0.05 to 0.10.
• the ratio (ZD) of the distance (£) between the discs to the diameter (D) of the turbine disc is 0.15 ⁇ to 0.2-5.
• the 3rd stage to 1S stage can be formed by C-Mo-V ⁇ and 17th stage by the above-mentioned martensitic steel.
• the de I first stage and the last stage co compressors disk has a structure-out stage bets with the following: or by any even steel of Ri that of the previous case of the last stage of the first stage
• the disc has a structure that gradually reduces the thickness from the first step to reduce the stress due to high-speed rotation:
• the compressor blade is ⁇ 0.05 to 0.2%, S i 0.5% or less, Mn 1% or less, Cr 10 or more; 13% or ⁇ 0.5% or less and Ni 0.5% or less, with the balance Fe or It is preferred to be composed of such martensite steel.
• the first stage of the ring which is in sliding contact with the tip of the turbine blade and formed into a ring, is C 0.05 to 0.2%, Si 2% or less, and Mn 2 % Or less, Cr 1 to 27%, C 0 5% or less, upper M 05 to: L 5%, Fe 10 to 3.0%, W 5% or less, B 0.02% or less, and the remainder
• a forged alloy consisting essentially of Ni is used, and the other parts are C 0.3 to 0.6%, Si 2% or less, Mn 2% or less, Cr 20 to 2 7 ° /. , Ni20.30% or less, NbO.l to 0.5%, Ti0.1 to 0.5%, and the balance substantially consisting of Fe is used.
• These alloys are composed of a plurality of blocks to form a ring.
• the first stage bin nozzle part is the weight, which is C 0.05% or less, Si 1% or less, Mn 2% or less, Cr 16 ⁇ 2 2%:, N i 8 ⁇
• 0.1 to 0.3% contains at least one kind, and is composed of a forged alloy containing eutectic carbide and secondary carbide in the primary phase base-all of these alloys are solution-treated After the aging treatment, the precipitate is formed and strengthened.
• Turbine blades can be coated with ⁇ , Cr or ⁇ + Cr diffusion coating to prevent corrosion due to high-temperature twisting gas. At 50 am, it is preferable to provide the wing in contact with the gas.
• a plurality of combustors are provided around the turbine, and the combustor has a double structure consisting of a cylinder and an inner cylinder.
• the inner cylinder is CO.05 to 0.2% by weight, Si 2% or less, and ⁇ 2% down, Cr 20 ⁇ 25%, Co 0.5 to 5%, Mo 5 to 15%, Fe 10 to 30%, W 5% or less, B 0.02% or less, and the balance is practically N a three-month louver hole that supplies air over the entire circumference of the cylindrical body, and is formed by welding a plastically processed material with a thickness of 2 to 5 sheets, and has a full-austenite structure. Processing materials are used.
• FIG. 1 is a cross-sectional view of a rotating portion of a gas turbine showing one embodiment of the present invention
• FIG. 2 is a diagram showing a relationship between an impact value after embrittlement and an (M n / N i) ratio
• Fig. 3 is a graph showing the relationship with the Mn content
• Fig. 4 is a graph showing the relationship with the Ni content
• Fig. 5 is a graph showing the creep rupture strength and the Ni content.
• FIG. 6 is a cross-sectional view showing one embodiment of the turbine disk of the present invention
• FIG. 7 is a portion near a rotating portion of a gas turbine showing one embodiment of the present invention. It is sectional drawing.
• Samples having the composition (% by weight) shown in Table 1 were each dissolved in 2 O kg, heated to 115 ° C and forged, and used as experimental materials. This material was heated at 115 ° C for 2 hours and then cooled by blast, and the cooling temperature was 1 ⁇ 0. Stopped at C, heated at 580 ° C for 2 h from that temperature, then air-tempered primary tempering, then heated at S05 ° C for 5 h, then furnace-cooled secondary tempering Creep rupture test pieces, tensile test pieces and V-notch impact test pieces were collected from the heat-treated material and used for the experiment. The impact test was performed on the as-heat-treated material at 500 ° C. for 1 000. This embrittlement material is equivalent conditions to those heated 1 0 5 hour Ri by para Nuta of Raruso emissions' Mi La one 4 5 0 ° C.
• Test Nos. 1 and 8 are the materials of the present invention, Test Nos. 2 to 7 are comparative materials, and Test No. 2 is the current disk material Ml52 steel equivalent material.
• Figure 2 is a diagram showing the relationship between the impact value after the embrittlement test and the (Mn / 'Xi) ratio. As shown in the figure, there is no significant difference up to the (Mn / Ki) ratio of 0. ⁇ 2. When the ratio is below 11.1, the embrittlement is sharply improved, and 4 kg — rv: ( ⁇ kg- ⁇ / cnf) Furthermore, it can be seen that excellent characteristics of 6 kg-m (7.5 kg-m / cn?) Or more can be obtained below 0.10. Mn is indispensable as a deoxidizing agent and a desulfurizing agent, and must be added in an amount of 0.6% or less.
• FIG. 3 is a graph showing the relationship with the Mn amount. As shown in the figure, the impact value after embrittlement is less than 2.1% for the N content, and no significant effect is obtained even if the ⁇ content is reduced, and the Ni content is more than 2.1%. As a result, the effect of reducing Mn is remarkable. In particular, the effect is significant when the Ni content is 2.4% or more.
• the amount of M n is' 0.7. /. In the vicinity, no improvement in the impact value is obtained regardless of the Ni content, but if the Mn content is 0.6% or less, the N ⁇ content becomes 2.4 as the Mn content becomes lower. /. Thus, one having a high impact value can be obtained.
• Fig. 4 is also a diagram showing the relationship with the amount of Ni.- As shown in the figure, when the amount of Mn is 0 * 7% or more, the improvement in embrittlement is small even if Ni is increased. It is clear that embrittlement is markedly improved by increasing Ni for Mn below that. In particular, for Mn contents of 0.15 to 0.4%, the improvement was remarkable at i contents of 2.2% or more, at 2.4% or more, 6 kg—m (7.5 kg-m / ⁇ or more, and further at 2.5% or more. It is clear that high values of more than 7 kg—m / d) can be obtained with ⁇ ⁇ FIG.
• FIG. 5 is a diagram showing a relationship between a 4 5 0 ° CX 1 0 5 h click Li-loop breaking strength and N i weight. Although 2. No ho and command affects the strength up to around 5% N i amount ⁇ rather shown in FIG, 3. Exceeds 0% when 5 0 KGZ Ri drops below the Yuzuru 2, the strength as a target to obtain Absent. It should be noted that the smaller the Mn, the higher the strength. The strength is most strengthened in the vicinity of 0.15 to 0.2%, and a high strength is obtained.
• FIG. 6 is a sectional view of a gas turbine disk of the present invention. Table 3 shows the chemical composition (% by weight).
• Z.0000 / 88df / lDd 980S0 / 88 OM Dissolution is carried out by carbon vacuum deoxidation method, after forging, heating at 150 ° C for 2 hours, quenching in oil at 150 ° C, and then from that temperature for 5 hours at 52 ° C. After heating, air-cooling and heating at 590 ° C for 5 hours were followed by furnace-cooled tempering.
• This disk had an outer diameter of 1,000 thighs, a thickness of 200 mm, and was machined into the shape shown in the figure after heat treatment.
• the central hole 11 is 65 mm.
• Reference numeral 12 denotes a portion where a stud bolt is provided with an insertion hole
• reference numeral 13 denotes a portion where a turbine blade is implanted.
• FIG. 1 is a sectional view of a rotating portion of a gas turbine showing an embodiment of the present invention using the above-mentioned disk.
• 1 is a turbine stub shaft
• 2 is a turbine socket
• 3 is a turbine bucking bolt
• 4 is a turbine spacer
• 5 is a discrete piece
• 6 is a compressor.
• 7 is a compressor disk
• 7 is a compressor stub
• 9 is a compressor stub shaft
• 10 is a compressor disk.
• the disc, 11 is a center hole.
• the gas turbine of the present invention has 17 stages of the combustor S and 2 stages of the turbine socket 2.
• Turbino Ket 2 is a three-stage In some cases, the steel of the present invention can be applied to any of them.
• Table 4 shows the chemical composition (% by weight) of the sample.
• the microstructures of these materials were as follows: ⁇ 6 to 9 were burnt-tempered martensite structures, and 10 and 11 were burnt-tempered and knight-structures. ! '(iS is used for desktop and final stage compressor discs. The former is 60 thighs x the width of 500, the so-called iX length 100 thighs, and the latter is the diameter of 100 thighs.
• thickness 180 thigh, ⁇ 7 has a diameter of 100 mm x thickness 180 as a disk
• No. 8 has an outer diameter of 100 mm as a disk
• No. 9 was used as a stacking bolt for either the turbine or the compressor, with a diameter of 40 thighs and a length of 500 mm.
• bolts for connecting the distur- te piece and the compressor disk were also manufactured using the steel of No. 9.
• No. 10 and No. 11 were the turbine stub shaft and the compressor stub bush, respectively. As a foot, it was forged to a diameter of 250 thighs and a length of 300.
• an alloy of 1 ⁇ 10 was used for the 1st to 16th stages of the compressor disk 6, and the ⁇ 1 Steel for yumpresa 6 These were used from the first stage to the 12th stage.All of them were manufactured to the same size as a single-bin disk. With the exception of No. 9 from the central part, samples were taken at right angles to the axial (longitudinal) direction. In this example, a specimen was taken in the longitudinal direction.
• Table 5 shows the results of room temperature tensile, 20 ° CV notch Charpy impact and creep rupture tests. Was determined by 45 0 ° CX 1 0 5 h click Li-loop breaking strength is generally that have been have use in Raruso down one mirror method.
• ⁇ 6 to 9 (12Cr steel) of the present invention, it is 450.
• C 1 0 5 h click rie flop fracture ⁇ degree 5 1 kg ZI thigh 2 or more, 2 0 ° CV Roh Tchisharupi ⁇ value 7 kg-m Z cnf or der is, a material for high temperature Antofagasta over bottle It was confirmed that the required strength was sufficiently satisfied.
• stub shafts No. 10 and 11 (low alloy steel) have low creep rupture strength at 450 ° C, but have a tensile strength of 86 kg Z ram 2 or more.
• 20 ° CV Notch Charpy impact value is 7 kg-m / CD! Or more, and strength required for stub shaft
• the gas turbine of the present invention constituted by a combination of the above materials has a compression ratio of 14.7 and a temperature of 350. C, the compressor efficiency is 8'6% or more, the gas temperature at the inlet of the first stage nozzle is about 1200 ° C, and the thermal efficiency (LHV) of 32% or more is obtained. You.
• the temperature of the detent piece and the temperature of the final stage compressor disk will be up to 450 ° C.
• the former preferably has a thickness of 25 to 30 thighs, and the latter has a thickness of 40 to 7 O moi.
• Both turbine and compressor discs are provided with through holes at the center. Compressive residual stress is formed in the award hole in the turbine disk.
• the gas turbine of the present invention uses the heat-resistant steel shown in the above-mentioned Table 3 at the final stage of the turbine spacer 4, the distant piece 5, and the compressor disk S, and the other parts are the same as those described above.
• a compression ratio of 14.7, a temperature of 35 Q ° C or more, a compression efficiency of 86% or more, and a gas temperature at the inlet of the first stage nozzle of 1200 ° C are possible.
• a creep rupture strength and a high impact value after heating embrittlement can be obtained as described above, and a more reliable gas turbine can be obtained.
• FIG. 7 is a partial sectional view of a rotating portion of a gas turbine showing an embodiment having a gas turbine disk using the heat-resistant steel of the present invention.
• the turbine disk 10 in this embodiment has three stages, and a center hole 11 is provided in the first stage and the second stage from the upstream side of the gas flow.
• all of the heat-resistant steels shown in Table 3 are used.
• the last stage downstream of the gas flow of the compressor disk 6 and the The top piece 5, the ta-bin spacer 4, the tabin-stating bolt 3, and the 'compressor-stating king vol. 8' are made of the heat-resistant steel shown in Table 3 above.
• turbine blades, turbine nozzles, shroud segments (1), and diaphragms were all used in the first stage on the gas upstream side.
• the shroud segment (2) is used in the second stage.
• the ratio (t ZD) of the minimum thickness (t) to the outer diameter of the final stage of the compressor disk 6 is 0.08
• the maximum inner diameter (D) of the delta piece 5 is The ratio of the minimum thickness (t) to the diameter (D) of the turbine disk. 0.04, and the ratio of the maximum thickness (t) at the center to the diameter (D) of the turbine disk (tD) is the first stage. Is 0.19 and the second stage is 0.205, and the ratio ( ⁇ D) of the intervals ( ⁇ ) between the disks is Q.21.
• a space is provided between each turbine disk.
• the turbine disc is provided with a plurality of bolts 6 for connecting the discs at equal intervals around the entire circumference.
• the above configuration makes it possible to achieve a compression ratio of 14.7, a temperature of 350 ° C or more, a compression efficiency of 86% or more, and a gas temperature of 1200 ° C at the inlet of the first turbine nozzle.
• a thermal efficiency of 32% or more can be obtained, as well as a reduction in turbine disks, discharge peaks, smoothers, and compressor disks.
• the starting bolts are used on a bin blade with a high clip rupture strength such as a forehead and a heat resistant ridge with less heat embrittlement. High strength at high temperatures. Gas turbines are highly reliable and balanced because of the high temperature strength and high temperature ductility of the swarf and the same high temperature strength and fatigue resistance of the combustor liner. Is obtained.
• high temperature and high pressure gas temperature: 1200. C or more, compression ratio: 15 class
• gas temperature 1200. C or more, compression ratio: 15 class
• the creep rupture strength and heat embrittlement required for gas turbine discs A gas turbine that satisfies a later impact value is obtained, and a gas turbine using the same has a remarkable effect of achieving extremely high thermal efficiency.

Landscapes

• 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)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

Family

ID=11506852

Family Applications (1)

Country Status (5)

Cited By (2)

Families Citing this family (47)

Citations (8)

Family Cites Families (23)

• 1987
  • 1987-01-09 JP JP62001630A patent/JPS63171856A/ja active Granted
• 1988
  • 1988-01-06 KR KR1019950702931A patent/KR950014312B1/ko not_active Expired - Fee Related
  • 1988-01-06 WO PCT/JP1988/000007 patent/WO1988005086A1/ja active IP Right Grant
  • 1988-01-06 EP EP88900787A patent/EP0298127B1/en not_active Expired - Lifetime
  • 1988-01-06 KR KR1019880701093A patent/KR950009221B1/ko not_active Expired - Fee Related
  • 1988-01-09 CN CN88100065A patent/CN1036666C/zh not_active Expired - Fee Related

Patent Citations (8)

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events