WO1997010066A1 - Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane - Google Patents
Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane Download PDFInfo
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- WO1997010066A1 WO1997010066A1 PCT/JP1995/001817 JP9501817W WO9710066A1 WO 1997010066 A1 WO1997010066 A1 WO 1997010066A1 JP 9501817 W JP9501817 W JP 9501817W WO 9710066 A1 WO9710066 A1 WO 9710066A1
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- Prior art keywords
- cooling
- titanium alloy
- blade
- turbine blade
- forced
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Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/40—Heat treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0403—Refractory metals, e.g. V, W
- F05C2201/0412—Titanium
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S148/00—Metal treatment
- Y10S148/902—Metal treatment having portions of differing metallurgical properties or characteristics
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/1241—Nonplanar uniform thickness or nonlinear uniform diameter [e.g., L-shape]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12458—All metal or with adjacent metals having composition, density, or hardness gradient
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12639—Adjacent, identical composition, components
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component
Definitions
- the present invention relates to a method of manufacturing a turbine blade made of a titanium alloy that can be used for a steam turbine, a gas turbine, an aircraft engine, and the like, and in particular, can prevent erosion by water droplets, sand particles, and the like.
- the present invention relates to a ⁇ t method and a titanium alloy turbine blade capable of economically producing a titanium alloy turbine blade having high cost.
- titanium alloys have low specific gravity and good corrosion resistance, they are used in steam turbines for blades in the last stage and low-temperature section of low-pressure turbines, and for blades in low-temperature sections in front of compressors for gas turbines and aircraft engines.
- wet steam impinges at high speed in the low-pressure turbine in the steam bin and the water droplets in the turbine cause erosion (water droplet erosion) and wear.
- gas turbines and compressors of aircraft engines draw large amounts of air, causing sand and dust in the air to hit the turbine blades, causing the turbine blades to wear out and suffer erosion (sand erosion).
- FIG. 1 is a perspective view showing an example of the shape of a turbine blade for a steam turbine
- FIG. 2 is a perspective view showing an example of the shape of a turbine blade for an aircraft engine
- FIG. 3 is a perspective view of a turbine blade having a cover and a snubber bar.
- FIG. 1 to 3 erosion is concentrated on the leading edge of the leading edge where the blade 1 rotates, that is, the leading edge where the rotating speed is high.
- the erosion site 2 is indicated by an X mark c , 3 denotes a turbine rotor, 4a denotes a cover, and 4b denotes a snubber bar portion.
- the present invention has been made in order to solve such a problem, and provides a method for manufacturing a highly reliable titanium alloy turbine blade that can be economically S! Iig and that can prevent erosion.
- the purpose is to provide.
- Another object of the present invention is to provide a turbine blade made of a titanium alloy that has excellent erosion resistance at the tip end side of the blade leading edge portion including the cover and is excellent in reliability. Disclosure of the invention
- the first manufacturing method of the present invention includes a step of forming a turbine blade made of a titanium alloy by hot forging; and a step of forming a tip end side of a blade front portion of the turbine blade including a cover formed by hot forming. And a step of heat-treating the cooled turbine blade.
- the front end side of the blade front edge including the cover refers to a portion of the turbine blade where erosion concentrates and occurs, including a snubber.
- the cover-to-nut bar refers to a protrusion or a step provided at the tip or middle of the blade effective portion, in contact with an adjacent blade, for fixing the blade or suppressing vibration. Therefore, the tip side of the blade front edge including the cover refers to, for example, the erosion generation site 2 indicated by the X mark in FIGS. 1, 2, and 3.
- the blade front edge including the cover refers to a range within 1/2 of the blade width W when viewed from the direction in which steam is applied in FIGS.
- the blade width W should be within 1/3 of the blade width W when viewed from the direction in which the steam strikes. Is desirable.
- the leading end of the leading edge refers to a range within 1/2 of the effective length of the blade from the tip of the blade in FIG.
- the blade body refers to the remaining blade area excluding the tip side of the blade front edge including the cover.
- the step of forming the turbine blade according to the present invention by hot forging includes not only hot stamping forging, but also the process of hot stamping forging and subsequent hot re-bending performed by ⁇ .
- the step of treating the cooled turbine blade according to the present invention is a step of treating the blade for annealing or aging.
- a turbine blade made of ⁇ +) 8 type titanium alloy as a titanium alloy hot forging is performed in the a + Siag region, which is 10 ° CJ3 ⁇ 4 ⁇ lower than Transus, and the cover is cooled when cooling.
- the leading edge portion of the blade leading edge is cooled faster than the blade body, and then the blade is heat-treated in a temperature range of 450 ° C to 850 ° C as a heat treatment for annealing or aging.
- a step of continuously performing a heat treatment at a single g for a predetermined time (FIG. 4 (a)) is performed continuously for a predetermined time at a predetermined temperature gradient.
- the heating step (FIG. 4 (b)), the step of continuously heating for a predetermined time by combining a plurality of different temperatures and a plurality of different times (FIG. 4 (c)), and the three heating steps described above. It consists of at least one process selected from the heating process (Fig. 4 (d)) in which at least one of the process S is intermittently repeated several times.
- the breaking gap represents a predetermined heating time. More specifically, in the case of an ⁇ + / 3 type titanium alloy, it is desirable that the forging be 930 to 970 ° C or lower, which is 10 or more lower than the beta transus temperature of the ⁇ -10 type titanium alloy, and cooling after forging.
- the front end of the blade including the cover is cooled by forced fan cooling with gas, forced cooling with compressed gas, forced cooling with water or oil, and the cooling rate of titanium alloy is water cooling.
- the blade body is heated at a temperature of 750 to 850 ° C for a predetermined period of time, and then heat-treated at 450 to 720 ° C 'a' continuously.
- the oil used for forced cooling with oil includes a coolant such as mineral oil, and the liquid in which the cooling rate of titanium alloy is between water cooling and oil cooling is a liquid mixture of the coolant and water or There is a liquid such as an aqueous solution in which mineral oil or the like is suspended in water.
- ⁇ -10 type titanium alloys include Ti-6A1-4V alloy (a titanium alloy containing 6SS% aluminum and 4% vanadium), Ti-6A1-2Sn-4Zr-2Mo-1O.ISi alloy (6 wt% Aluminum, 2% by weight tin, 4% by weight zirconium, 2% by weight molybdenum and 0.1% by weight silicon containing titanium alloy), Ti-6A1-6V-2Sn alloy (6% by weight aluminum) , A titanium alloy containing 6% by weight of vanadium and 2% by weight of tin).
- Ti-10V-2Fe-3A1 alloy (a titanium alloy containing 10fi *% vanadium, double i% iron, and 3fi *% aluminum), Ti-5A1-4Cr-1Mo-4Sn-2Zr alloy (Titanium alloy containing 5% fifi% aluminum, 4% chromium, 4SS% molybdenum, 2% tin, and 2% zirconium), Ti-5A1-2Sn-4Zr-4Mo-2Cr-lFe Near-type titanium such as alloys (titanium alloy containing 5Mfi% aluminum, 2% tin, 4% zirconium, 4% molybdenum, 2% chromium, and 1% iron by weight) For turbine blades made of alloys, 10 from the base and transus temperatures of each alloy.
- the blade body In the cooling process after hot forging by 730 to 875 ° C, which is lower than C, the blade body is allowed to cool, while the front end of the blade front edge including the cover is forced fan cooled by gas, compressed gas Forced cooling with water or oil, forced cooling with a liquid in which the cooling rate of the titanium alloy is between water cooling and oil cooling, and spraying or spraying liquid and gas under pressure. Cooling faster than the blade body by at least one cooling method selected from forced cooling with a mixture of the above, and then aging the blade at a single temperature or multiple temperatures in a temperature range of 420 to 650 ° C for a predetermined time Is heated.
- the temperature of hot curtain and aging treatment is It has a desirable range depending on the composition of the alloy, for example, in the above-mentioned alloy, set the hot-rolling temperature to 760 to 850 ° C and the aging temperature to 500 to 650 ° C. Is desirable.
- Ti-1V-3Cr-3A1-3Sn alloy (a titanium alloy containing 15% by weight of vanadium, 3% by weight of chromium, 3% by weight of aluminum and 3% by weight of tin), 3A1 -8V-6Cr—4Mo -4Zr alloy (titanium alloy containing 3 wt% aluminum, 8 wt% vanadium, 6 ftS% chromium, 4 wt% molybdenum, 4 wt% zirconium), Ti-11.5MO—6Zr-4.
- titanium alloys (11.5Mfi% molybdenum, 6% titanium alloy containing B% zirconium and 4.5% S% tin), Ti-13V—llCr-3A1 (13-5% vanadium, 11-3% chromium and 3fi
- titanium alloys e.g.
- the forging heating temperature is 700 ⁇ in the S temperature range: After feiging at L050 ° C, the blade body is allowed to cool while the cover is Forced fan cooling with gas at the tip of the blade leading edge, including compressed air Forced cooling by body, Forced cooling by water or oil, Cooling of titanium alloy Forced cooling by liquid whose 3 ⁇ 4g is between water cooling and oil cooling, and by mixture of liquid and gas which becomes spray or ⁇ under pressure The cooling is performed faster than the blade body by at least one cooling method selected from forced cooling, and then the blade is heated for aging at ⁇ between 400 and 650 ° C.
- the hot forging and aging temperatures have a desirable range depending on the composition of the / 3 type Titanium alloy, for example, Ti-15V-3Cr-3A1-3Sn alloy, For Ti-3A1-8V-6Cr-4Mo-4Zr alloy and Ti-11.5Mo-6Zr-4.5Sn alloy, hot rolling temperature is 760-925 ° C and aging temperature is 500-550 ° C. It is desirable to set the temperature to
- a second manufacturing method includes a step of forming a turbine blade made of a titanium alloy by hot forging or a D-work, a step of solution-treating the formed turbine blade, and a step of solution-treating the turbine blade. It is characterized by comprising a step of cooling the leading end of the blade front edge including the cover of the turbine blade after the process earlier than the blade body, and a step of heat-treating the cooled turbine blade.
- the front end side of the blade front edge including the cover refers to the same range as the range in the first manufacturing method of the present invention. Titanium alloy turbine blades are hot forged or cut from round or square bars without hot forging to form turbine blades, and then subjected to erosion in the cooling process after high heat for solution.
- a production method for preventing erosion can be obtained.
- the same process as in the first ig ⁇ method of the present invention may be applied to a turbine blade made of ⁇ + type titanium " ⁇ , Near ⁇ type titanium alloy or; 5 type titanium alloy.
- the beta transus temperature 10 ° CJ When heating in the low L ⁇ + ⁇ region and then cooling, the leading edge of the blade's leading edge cools faster than the blade body and then cools the blade for annealing or aging.
- a process of continuously applying for a predetermined time with a single a process of performing a heat treatment for a predetermined time continuously with a predetermined temperature gradient, a plurality of different temperatures and a plurality of different times And a heat treatment step continuously selected for a predetermined time, and at least one heat treatment step selected from a heat treatment step in which at least one of the three heat treatment steps is intermittently repeated a plurality of times.
- Heat treatment More specifically, in the case of an ⁇ + type titanium alloy such as Ti-6A1-4V alloy, the heating temperature after forging or after heating is preferably 930 to 970 ° C, and the cooling after that is performed by cooling the blade body.
- the tip side of the blade leading edge including the cover is forced fan cooled by gas, forced cooled by compressed gas, forced cooled by water or oil, and the cooling rate of the titanium alloy is determined by water cooling and oil cooling. Cooling faster than the blade body by at least one cooling method selected from forced cooling with an intervening liquid and forced cooling with a liquid and gas mixture that becomes a spray or a spray under pressure and then (A) Heat treatment at a temperature of 750 to 850 ° C for a predetermined period of time, followed by continuous heat treatment at a temperature of 450 to 720 ° C.
- ⁇ + at 730 to 875 Heating for solution treatment is performed in the temperature range.
- the blade body is allowed to cool in the subsequent cooling process, while the front end of the blade front edge including the cover is forced fan cooled by gas, forced cooled by compressed gas, water Or by forced cooling with oil, by forced cooling with a liquid in which the cooling rate of the titanium alloy is between water cooling and oil cooling, and by forced cooling with a mixture of liquid and gas that becomes a spray or a spray under pressure.
- the blade is cooled faster than the blade body by at least one cooling method selected from the group below, and then the blade is heated in the range of 420 to 650 at a single temperature or at multiple temperatures for aging for a predetermined time. Cormorant.
- / 3 type titanium alloy such as Ti-15V-3Cr-3A1-3Sn alloy
- the blade body is allowed to cool, while the front end of the blade including the cover, including the cover, is forcedly cooled with gas, forced cooling with compressed gas, forced cooling with water or oil, and the cooling rate of the titanium alloy
- At least one cooling method selected from the group consisting of forced cooling with liquid between water cooling and oil cooling, and forced cooling with a liquid and gas mixture that becomes a spray or a spray under pressure.
- the blade cools faster than the blade body, and then the blade is 400-650. Heat for aging with ⁇ between C.
- the turbine blade does not necessarily have to be finished to the final shape, and the effect of the present invention can be obtained even if the final blade has a surplus force.
- the inventors conducted an erosion test simulating water droplet erosion by applying various materials to the tip of a rotating blade, rotating the blade at high speed, and spraying water droplets on the tip of the blade to form water droplet erosion generated in a steam turbine or the like.
- the erosion resistance of various materials it was found that, for materials having the same basic composition, the higher the hardness of the material, the smaller the erosion loss and the better the water droplet erosion resistance.
- ⁇ S was measured as a test to simulate the erosion by sand, at high speed, blowing the S i 0 2 particles are minute standing, was measured reduced ⁇ S, regardless to the material, it is reduced the higher the hardness of the material It turned out to be less. Therefore, for both types of erosion, it was found that increasing the hardness of the material was effective in reducing and preventing erosion.
- the hardness and other properties of titanium alloys vary with heat treatment, but in particular, cooling from high-temperature solution treatment i ⁇ is an important factor that determines the properties of titanium alloys. .
- cooling from high-temperature solution treatment i ⁇ is an important factor that determines the properties of titanium alloys. .
- it is effective to increase the cooling rate from the solution treatment 2 ⁇ , to make the microstructure fine, or to harden it by the subsequent aging treatment.
- the heating temperature for the final hot forging serves the same role as the solution treatment, so that hot-rolling is completed and the turbine is still hot. Quenching quickly is effective in increasing hardness.
- the cooling rate is the speed L, which is effective for increasing the hardness.
- the cooling method is a forced fan ⁇ cooling with a gas that blows air-containing gas by compressed gas, water, oil or water and oil. Liquid cooling with a liquid having an intermediate cooling rate or liquid spraying with a mixture of compressed liquid and gas is suitable.
- the erosion-prone portion at the leading edge of the leading edge of the turbine blade must be For blades that have been cooled to room temperature or formed by machining from a high temperature immediately after hot forging or hot forging and then formed by machining, they are rapidly cooled from the solution treatment temperature, and then subjected to annealing, Alternatively, to increase the hardness by aging treatment, while maintaining the ductility and toughness of the other parts, allow the turbine blades to be cooled or gradually cooled without sudden ⁇ ⁇ ⁇ "
- the hot ⁇ t process here is used to adjust the change in blade thickness after hot stamping and stamping forging, and to correct warpage and twist.
- the process includes a process of cooling from high temperature immediately after the application of heat, the above-mentioned object will be satisfied.
- various conditions for various titanium alloys there are various conditions for various titanium alloys. The optimal conditions for typical titanium alloys are described.
- the hot working or solution treatment temperature is required to maintain the ⁇ + structure uniform throughout the long turbine blades.
- the temperature of hot forging or solution treatment is 10 times higher than that of beta transus S ⁇ ⁇ ⁇ of each ⁇ + type titanium alloy.
- 930 ⁇ 970 is 3 ⁇ 4 ⁇ .
- the leading edge of the leading edge of the turbine blade including the cover quenched from this temperature range needs aging treatment to increase hardness, and it is higher than 450 ° C to perform age hardening sufficiently effectively Achieved by a heat treatment for several to several tens of hours in the temperature range as low as possible.
- a suitable aging temperature is 450 to 720 ° C. At higher temperatures, age hardening hardly occurs, and at lower temperatures, it takes a long time of several tens of hours, which is not industrially efficient. However, it is effective to perform annealing at an intermediate temperature of 850 or less before aging treatment in order not to significantly reduce tensile ductility and toughness. This processing is 750 ⁇ 850. A few hours in C.
- aging at a low temperature of 450-600 ° C and then aging at a higher ⁇ of 625-721TC is effective. It is. The effect is the same even if the two-stage heat treatment is performed continuously or discontinuously from the first temperature to the second temperature. Except for the turbine blade cover and the quenching zone on the leading edge front side, the blade body has a relatively slow cooling rate, so there is almost no hardening due to the above aging treatment, and the intermediate annealing also hardly causes a decrease in strength. High L, ductility and toughness can be maintained after these heat treatments without causing.
- the ⁇ + organization of the final hot-rolling or solution treatment must be maintained. It is necessary, and for that purpose, it is desirable that the temperature is 10 ° C or lower than the base transus of each type of titanium alloy ⁇ , for example, 875 ° C or lower for Ti-5A1-2Sn-4Zr-4Mo-2Cr-lFe alloy. However, if this i3 ⁇ 4S is too low, the age hardening will be less, so the lower limit is preferably 730 ° C. More preferably 760 ⁇
- Subsequent aging treatment may be carried out in the range of 420 to 650 for several hours to ten to several hours, preferably at a temperature of 500 to 650. C.
- the final hot forging and solution treatment be between 700 and 1,050 mm. Further, it is necessary that the crystal grains are not coarsened, and more preferably 700 to 850 ° C.
- aging treatment As the aging treatment, a temperature of 650 ° C or less is required to cause hardening due to the fine dispersion of the ⁇ phase in a few hours, but if the temperature is too low, the ⁇ phase precipitates, Since toughness is extremely reduced, aging treatment at a temperature of 400 ° C or more is desirable to prevent it.
- the conditions listed here are typical conditions for each type of titanium alloy. If the required characteristics and hardness differ depending on the application of the turbine blade, it may not necessarily be within the range of these conditions.
- the object of the present invention can be achieved in that the front end of the leading edge of the turbine blade including the cover is made harder than the main body.
- FIG. 1 is a perspective view of a turbine blade for a steam turbine.
- FIG. 2 is a perspective view of a turbine blade for an aircraft engine.
- FIG. 3 is a perspective view of a turbine blade having a cover and a snubber bar.
- FIG. 4 is a diagram schematically showing a specific mode of the heat treatment. DETAILED DESCRIPTION OF THE INVENTION
- a turbine blade with an effective part length of 1000 mm was formed by hot rolling.
- the final hot forging was performed after heating at 950 ° C.
- a plurality of blades A which were showered with pressurized water, were placed inside the top 500 mm of the leading edge of the blade including the cover.
- multiple blades B were quenched by blast air cooling.
- other parts were covered with protective covers to prevent direct water showers or blasts. This quenching process after 95 (TC heating) simulates the final forging or hot re-bending of hot-rolling, either process.
- the leading edge of the blade including the cover by water shower or blast air cooling After the tip side was rapidly cooled to room temperature, the temperature of the blade body returned to room temperature after about 5 hours.After that, some of the blades A and B were kept at 800 ° C for 1 hour and air-cooled. Furthermore, it was aged for 6 hours at 550 ° C (referred to as blades A to C.) Some blades were also aged for 6 hours at 550 ° C followed by 675 ° C. C was heat treated for 2 hours (referred to as blades B-C), while the remaining blades A and B were 600. Only heat-treated for 3 hours at C (blades A-D, respectively). In parallel with this, after hot forging at the same temperature The blade from gradual cooling was fabricated comparative blade 1 of the conventional process that annealed the 2 hour hold at 700 ° C.
- test specimens are cut out from the tip of the blade leading edge and from the implanted part, and a hardness test is performed, and a tensile test and a Charpy impact test are performed on the test piece from the implanted part.
- a water droplet erosion test was performed on the test piece cut out from the tip side.
- the implantation part is a part of the blade body. I chose it as a table.
- the hardness test is based on the Vickers hardness test method according to JIS Z 2244
- the tensile test is based on the tensile test method based on JIS Z 2241 using a tensile test piece based on No. 14A of JIS Z 2201
- the Charpy impact test is JIS No.
- test piece 20 was using a test piece. Performed in C. In the water drop erosion test, a test piece was attached to the tip of a small rotating blade, rotated at a peripheral speed of 300 ffl / s, and water drops were sprayed on the test piece for 1 hour to compare the weight loss of the pieces. Table 1 shows the test results.
- the blades according to the present invention have higher tensile strength and hardness values at the leading edge than at the implanted portion, and are harder than the blade main body, as compared with Comparative Blade 1.
- the tensile strength and strength are the same as those of the comparative blade 1, and have the same impact value and excellent toughness.
- the erosion ratio is greatly reduced in proportion to the hardness of the comparative blade 1 compared to the same position, and the present invention is achieved. It can be seen that both methods have excellent erosion resistance with a water droplet erosion amount of about 40% or less of the it3 ⁇ 4 blade.
- This erosion resistance is not inferior to that of the Co-based alloy stellite conventionally used for preventing erosion.
- a blade having high erosion resistance at the erosion-producing portion on the leading edge side of the blade leading edge, while having high toughness and high reliability at other portions of the implanted portion. Can be manufactured.
- Ti-6A1-2Sn-4Zr-21- alloy or Ti-6A1-2Sn-4Zr-0.3Si alloy is used, and the processing temperature is not necessarily the same.
- a turbine blade with an effective part length of 1000 lots was formed by hot forging and cooled to room temperature. After that, it is maintained at 950 ° C for 1 hour as a solution treatment.After heating, multiple blades E with water cooled about 500 mm on the tip side of the leading edge of the blade, or multiple blades F cooled rapidly by impingement air cooling are manufactured. did. Water cooling only at the leading edge front side was performed by immersing only the relevant portion of the blade in water. In blast air cooling, the other parts were covered with protective covers to prevent direct blast. After the leading edge of the blade was rapidly cooled to room temperature by water cooling or 113 ⁇ 4 cooling, the temperature of the blade body returned to room temperature after about 5 hours.
- blade E-C After holding at C for 1 hour, it was further aged at 550 for 6 hours (this is called blade E-C). Also, some blades have a 6-hour aging treatment at 550 ° C followed by 675. Heat treatment was performed for 2 hours at C (this is called blade FC). On the other hand, the remaining blades E and F were only subjected to aging treatment at 600 ° C for 3 hours (referred to as blades E-D and F-D, respectively). In parallel with this, the blade was gradually cooled after hot-rolling, and the solution was treated in 950. After heating for 1 hour at C, the steel was allowed to cool, and then annealed at 700 ° C for 2 hours to produce a comparative process blade 2 of a normal process.
- the blade according to the present invention has higher values of tensile strength and hardness at the leading edge side than at the implanted portion, and is harder than the blade main body, as compared with Comparative Blade 2.
- the implanted part has the same tensile strength as the comparative blade, the same impact value, and has excellent toughness.
- the erosion ratio was significantly reduced in proportion to the hardness of the comparative blade compared with the same position of the comparative blade. It can be seen that in any of the methods, the water droplet erosion amount has an excellent erosion resistance of 40% or less of the i ⁇ blade. This erosion resistance is not inferior to the C0-based alloy stellite conventionally used for erosion prevention. like this
- Example 2 a blade formed by hot-rolling and then cooled to room temperature was described. However, a blade formed by forging a forged rod of Ti-6A1-4V alloy was also used. The same effect as in Table 2 can be obtained by performing the same processing as
- a turbine blade with an effective part length of 850 mm was formed by hot rolling using a Ti-10V-2Fe-3A1 alloy of type 5 titanium alloy.
- the final hot curtain was performed after heating at 785 ° C.
- a plurality of blades G were prepared by oil cooling about 300 thighs on the tip side of the blade front edge, and after a similar hot l ⁇ g, Several blades H were quenched by blast air cooling. Oil cooling only at the leading edge side was performed by immersing only the relevant part of the blade in oil. In blast air cooling, a protective cover was placed on the other parts to prevent direct blast.
- blade G and blade ⁇ each part of the blade is 600. C was aged for 6 hours (referred to as blades G-1 and H-1 respectively). On the other hand, the remaining blades G and H were aged at 50 CTC for 10 hours (referred to as blades G-2 and H-2, respectively).
- a comparative blade 3 of the conventional process was manufactured by hot forging at the same temperature, allowing the blade to cool, and then annealing at 550 ° C for 8 hours.
- test specimens were cut out from the tip side and the front edge of the blade, and a hardness test, a tensile test, a Charpy impact test, and a water droplet erosion test were performed under the same conditions as in Example 1. The results are shown in Table 3.
- the blade according to the present invention has a higher bow I tension strength and hardness at the leading edge side than at the implanted portion, and is harder than the blade body as compared with the comparative blade 3 at all. You can see that.
- the implanted portion has the same tensile strength as Comparative Blade 3, the same impact value, and excellent toughness.
- the erosion ratio was significantly reduced in proportion to the hardness of the comparative blade 3 compared to the same position, and the present invention It can be seen that in any of the following methods, the water droplet erosion amount is excellent erosion resistance of about 1/3 or less of the comparative blade 3.
- This erosion resistance is not inferior to conventional Co-based alloy stellite used for erosion prevention.
- the erosion resistance is high at the portion where erosion occurs on the tip side of the blade leading edge, and the toughness is high at other portions such as the ⁇ portion. (See Table 3)
- Multiple turbine blades with an effective part length of 600 mm were formed by milling using rolling rods of Ti-10V-2Fe-3A1 alloy of Near S type titanium alloy. After that, a part of this blade was heat-treated at 760 ° C for 1 hour as a solution treatment, and then about 200 mm on the tip side of the leading edge of the blade was oil-cooled. . Oil cooling only at the leading edge front side was performed by immersing only the relevant portion of the blade in oil. After the leading edge of the blade was rapidly cooled to room temperature by oil cooling, the temperature of the blade body returned to room temperature after about 5 hours. After that, some blades of blade I were 600. C was aged for 6 hours.
- the blades according to the present invention have higher values of tensile strength and cm at the leading edge portion than at the ⁇ ⁇ portion, and are harder than the blade body as compared with the comparative blade 4. You can see that.
- the implant and the implant have the same tensile strength as Comparative Blade 4 and the same impact value, and have excellent toughness.
- the erosion ratio was significantly reduced in proportion to the hardness of the comparative blade 4 compared to the same position, and the present invention It can be seen that in any of the following methods, excellent erosion resistance of water droplet erosion force ⁇ approximately 30% or less of comparative blade 4 is obtained.
- This erosion resistance is not inferior to the C0-based alloy stellite conventionally used for erosion prevention.
- the erosion resistance is high in the portion where erosion occurs at the leading end side of the blade leading edge, but the toughness and reliability are high in other portions such as the 3 ⁇ 4 ⁇ portion. Blades can be manufactured.
- Example 4 the force was applied to the blade formed by processing, and the same as Example 4 for a blade formed by hot rolling of Ti-10V-2Fe-3A1 alloy and cooled to room temperature.
- the same effect as in Table 4 was obtained by performing the above processing.
- Ti-5A1-4Cr-4o-2Sn-2Zr alloy as Near / S type titanium alloy
- Tables 3 and 4 were obtained.
- a turbine blade having the same characteristics as described above was obtained. Table 4
- a plurality of turbine blades having an effective part length of 600 were formed by rolling using a rolled bar of a titanium-type titanium alloy 15V-3Cr-3Al-3Sn alloy. After that, a part of this blade was subjected to solution treatment 785. After holding at C for 1 hour, about 250 mi of the leading edge of the blade front edge was quenched with compressed air, and the rest of the blade was allowed to cool. At this time, the remaining part was covered with a protective cover so that compressed air was not directly applied. After the leading edge of the blade was rapidly cooled to room temperature by compressed air, the temperature of the blade body returned to room temperature after about 5 hours. Then the blade :! Is 480. In C Aged for 16 hours. The remaining blades were used as comparative blades 5.
- test specimens were cut out from the tip side and the front edge of the blade, and a hardness test, a tensile test, a Charpy impact test, and a water droplet erosion test were performed under the same conditions as in HI! Table 5 shows the results.
- the blades of the present invention have higher values of the tensile strength and hardness at the leading edge portion than at the implanted portion, and are harder than the blade body, compared to the comparative blade 5 at the leading edge.
- the filj ⁇ portion has the same tensile strength as the comparative blade 5 and the same impact value, and has excellent toughness.
- the erosion ratio was significantly reduced in proportion to the hardness of the comparative blade 5 in comparison with the same position, and the present invention It can be seen that in any of the following methods, the water droplet erosion amount is excellent erosion resistance of about 30% or less of the comparative blade 5.
- the erosion resistance is high in the portion where the erosion occurs on the tip side of the blade leading edge, but the toughness is high in other portions such as the implanted portion. Highly efficient blades can be manufactured.
- Example 5 The manufacturing method shown in Example 5 is an example in which a turbine blade is formed by machining or the blade after the last hot forging, and the turbine blade is formed by hot forging.
- the same effect as in Table 5 was obtained by performing the same processing as in Example 5 on the blade cooled to room temperature.
- the tip side of the leading edge of the blade including the cover of the turbine blade formed by hot rolling is cooled faster than the blade main body, and thereafter, annealing and aging are performed.
- the tip of the leading edge of the blade which is susceptible to erosion due to water droplets and sand particles during turbine operation, has a high erosion resistance, and has a high stiffness.
- a blade having excellent ductility and toughness as well as strength can be obtained. As a result, a highly reliable chip An evening alloy turbine blade can be provided.
- another method of manufacturing a turbine blade made of a titanium alloy of the present invention includes forming the turbine blade by hot forging or a machine, solution-treating the formed turbine blade, and including a cover of the turbine blade.
- the leading edge of the blade's leading edge cools faster than the blade body, and then is subjected to heat treatment for annealing and aging, so it has excellent erosion resistance and is economical and reliable, similar to the manufacturing method described above. It is possible to obtain a titanium alloy turbine blade having high performance.
- the titanium alloy turbine blade of the present invention is more excellent in long-term reliability because the erosion resistance of the leading edge of the blade leading edge including the cover is superior to that of the blade body.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Forging (AREA)
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP95931401A EP0852164B1 (en) | 1995-09-13 | 1995-09-13 | Method for manufacturing titanium alloy turbine blades and titanium alloy turbine blades |
US09/043,025 US6127044A (en) | 1995-09-13 | 1995-09-13 | Method for producing titanium alloy turbine blades and titanium alloy turbine blades |
PCT/JP1995/001817 WO1997010066A1 (fr) | 1995-09-13 | 1995-09-13 | Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane |
DE69529178T DE69529178T2 (de) | 1995-09-13 | 1995-09-13 | Verfahren zum herstellen einer turbinenschaufel aus titanlegierung und titanlegierungsturbinenschaufel |
JP51181697A JP3531677B2 (ja) | 1995-09-13 | 1995-09-13 | チタン合金製タービンブレードの製造方法およびチタン合金製タービンブレード |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP1995/001817 WO1997010066A1 (fr) | 1995-09-13 | 1995-09-13 | Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1997010066A1 true WO1997010066A1 (fr) | 1997-03-20 |
Family
ID=14126261
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1995/001817 WO1997010066A1 (fr) | 1995-09-13 | 1995-09-13 | Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane |
Country Status (5)
Country | Link |
---|---|
US (1) | US6127044A (ja) |
EP (1) | EP0852164B1 (ja) |
JP (1) | JP3531677B2 (ja) |
DE (1) | DE69529178T2 (ja) |
WO (1) | WO1997010066A1 (ja) |
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JP2005002473A (ja) * | 2003-06-10 | 2005-01-06 | Boeing Co:The | 金属部材を形成し、チタンベースの合金を熱処理しかつ航空機を製造するための方法、および負荷のかかる構造部材を含む航空機 |
WO2007007497A1 (ja) * | 2005-07-14 | 2007-01-18 | Jfe Steel Corporation | 熱間鍛造設備 |
US7827842B2 (en) | 2005-07-14 | 2010-11-09 | Jfe Steel Corporation | Hot forging facility |
JP2011007093A (ja) * | 2009-06-25 | 2011-01-13 | Hitachi Ltd | タービン動翼 |
JP2015520033A (ja) * | 2012-04-19 | 2015-07-16 | スネクマ | 複合物でできた前縁を保護するためのインサートを備えた金属補強材を形成するための方法 |
US9963971B2 (en) | 2012-04-19 | 2018-05-08 | Snecma | Method for creating a metal reinforcement with insert for protecting a leading edge made of composite |
US10934847B2 (en) | 2016-04-14 | 2021-03-02 | Mitsubishi Power, Ltd. | Steam turbine rotor blade, steam turbine, and method for manufacturing steam turbine rotor blade |
Also Published As
Publication number | Publication date |
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EP0852164A1 (en) | 1998-07-08 |
US6127044A (en) | 2000-10-03 |
DE69529178D1 (de) | 2003-01-23 |
DE69529178T2 (de) | 2003-10-02 |
JP3531677B2 (ja) | 2004-05-31 |
EP0852164B1 (en) | 2002-12-11 |
EP0852164A4 (en) | 1999-03-10 |
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