US20080181808A1 - Methods and articles relating to high strength erosion resistant titanium alloy - Google Patents

Methods and articles relating to high strength erosion resistant titanium alloy Download PDF

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US20080181808A1
US20080181808A1 US11/669,607 US66960707A US2008181808A1 US 20080181808 A1 US20080181808 A1 US 20080181808A1 US 66960707 A US66960707 A US 66960707A US 2008181808 A1 US2008181808 A1 US 2008181808A1
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weight
titanium alloy
turbine blade
article
exposing
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US11/669,607
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English (en)
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Samuel Vinod Thamboo
Ling Yang
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General Electric Co
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General Electric Co
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Priority to US11/669,607 priority Critical patent/US20080181808A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: THAMBOO, SAMUEL VINOD, YANG, LING
Priority to EP08100604A priority patent/EP1953251A1/en
Priority to KR1020080009113A priority patent/KR20080071908A/ko
Priority to JP2008018421A priority patent/JP2008190039A/ja
Priority to CNA200810009528XA priority patent/CN101235449A/zh
Publication of US20080181808A1 publication Critical patent/US20080181808A1/en
Abandoned legal-status Critical Current

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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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • 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
    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to methods and articles comprising titanium alloys. These articles may be suitable for use in turbines, particularly steam turbines, and particularly relates to titanium alloys (known as Ti-62222) suitable for use in turbine blades, preferably long blades.
  • the titanium alloys may require an unconventional heat treatment.
  • last-stage buckets may be optimized in steam turbines.
  • the last stage of a steam turbine can be the highest loaded stage and may contribute on the order of about 10% to the overall output of the turbine.
  • last-stage buckets are exposed to a wide range of flows, pressures, loads and strong dynamic forces. A bucket's material, as well as other factors, may affect its performance.
  • Long steam turbine buckets which are usually at the end of the low pressure section of the turbine—are preferably lightweight.
  • the weight of the bucket generally adds to the centrifugal force pulling on the rotor attachment areas. These pull loads can exceed the tensile strength of the rotor alloy and may cause damage to the rotor.
  • Titanium alloys (such as Ti-6-4) have been used, because those alloys' density can be roughly one-third of steel alloys'.
  • the weight of the titanium blade can be high enough to exceed the yield strength of the titanium itself. This may cause deformation of the blade at the root. Therefore for these lengths the titanium alloy is preferably lightweight as well as high strength.
  • the steam can have considerable moisture, which may condense on the stationary airfoils just before the last stage. These droplets then may be released with high velocity onto the rotating blade. The impact with the rotating blade may cause erosion of the leading edge of the blades.
  • the bucket's material is preferably resistant to water droplets.
  • the present invention there is a method of treating an article comprising a titanium alloy.
  • the titanium alloy includes 5-6.5% aluminum by weight; 1.5-2.5% tin by weight; 1.5-2.5% chromium by weight; 1.5-2.5% molybdenum by weight; 1.5-2.5% zirconium by weight; and titanium.
  • the method includes the steps of: exposing the titanium alloy to a forging start temperature ranging from 1500° F. to 1800° F.; exposing the titanium alloy to an alpha-beta anneal process having a temperature ranging from 1550° F. to 1850° F.; and exposing the titanium alloy to an aging process having a temperature ranging from 800° F. to 1000° F. for a length of time ranging from 1 hour to 24 hours.
  • the method does not include exposing the titanium alloy to a beta anneal process.
  • an article that includes 5.25-6.25% aluminum by weight; 1.75-2.25% tin by weight; 1.75-2.25% chromium by weight; 1.75-2.25% molybdenum by weight; 1.75-2.25% zirconium by weight; 0.1-0.2% silicon by weight; 0-0.15% iron by weight; 0-0.08% carbon by weight; 0-0.15% oxygen by weight; 0-0.05% nitrogen by weight; 0-0.015% hydrogen by weight; and titanium.
  • the article which may be a turbine blade, has been subjected to a heat treatment process that does not include beta anneal.
  • FIG. 1 illustrates a steam turbine blade in accordance with an embodiment of the present invention.
  • FIG. 2 is a cross-section through line II-II shown in FIG. 1 .
  • FIG. 3 illustrates a steam turbine blade in accordance with an embodiment of the present invention.
  • FIG. 4 illustrates a steam turbine blade in accordance with an embodiment of the present invention.
  • FIG. 5 illustrates the grain structure for the titanium alloy treated using the Triplex and the Fine Grain process.
  • FIG. 6 is a plot illustrating the relative erosion resistance of several alloys.
  • Ti-6-4 can be relatively easily made into the airfoil shape by forging.
  • Ti-6-4 generally has a yield strength of approximately 90,000 psi at room temperature. This can work out very well for blades which are shorter than 45 inches long.
  • Ti-6-4 may not have the strength to sustain its own centrifugal loading for steam turbines turning at 3000-3600 rpm.
  • This alloy may also have problems caused by only modest resistance to water droplet erosion. There have been attempts to improve the water droplet erosion of this material. These include hardening the tips (which are typically most susceptible) by using nitriding (e.g., U.S. Pat. Nos. 4,942,059 and 5,366,345), adding erosion shields made of other alloys like stellite or titanium carbides (e.g., U.S. Pat. Nos. 5,183,390, 4,842,663, 3,561,886, and 4,795,313).
  • FIGS. 1 and 2 illustrate a blade 1 from one of the last few rows of blades in a low pressure steam turbine.
  • the blade 1 is comprised of an airfoil portion 2 and a root portion 3 .
  • the root portion 3 serves to attach the blade 1 to the rotor of a steam turbine.
  • the airfoil 2 which is exposed to the steam flowing through the turbine, serves to extract the energy from the steam necessary to rotate the rotor.
  • the airfoil 2 is comprised of a leading edge portion 4 , a trailing edge portion 5 and a center portion 9 disposed between the leading and trailing edge portions and adjacent to each.
  • the airfoil 2 has a tip portion 6 and a platform 7 , which serves as the attachment point of the airfoil to the root 3 .
  • Water droplets may form in the steam flowing through the lowest pressure portions of low pressure steam turbines. These water droplets are entrained in the steam flow and, as a result of centrifugal force, may migrate outward toward the tips of the blades. The water droplets may cause harmful erosion of the trailing edge 5 of the blade airfoil 2 near its tip portion 6 .
  • the bucket of an embodiment of the present invention is generally designated 10 and has a root section 12 connected to a finger dovetail 14 for connection to the wheel of the turbine, not shown.
  • Bucket 10 also includes a tip 16 having radially projecting stepped tenons 18 and 20 for receiving inner and outer covers. Adjacent the midpoint of the bucket, there is provided a built-up section 22 having an aperture 40 for receiving a tiewire adjacent the bucket's midpoints for structural damping.
  • the dovetails 14 may have circumferentially projecting portions between their opposite axial ends and corresponding circumferentially opening recesses along their opposite sides.
  • FIGS. 3 and 4 illustrate a typical latter stage steam turbine blade which could be over 45 inches in length.
  • increasing blade length may improve efficiency.
  • This design of blade is supported at the mid-span with nubs and at the tips covers. Both these features make contact with adjacent blades during operation and provide mutual support.
  • the axial entry dovetails are the locations where the blade is attached to the rotor. This area typically sees the highest stresses and is in contact with the steel of the rotor. This area, therefore, may require a high strength material.
  • the edge of the blade is generally subjected to alternating stresses and, therefore, may require good low cycle fatigue and high cycle fatigue resistance.
  • the turbine blade generally may have good fracture toughness to prevent premature failure.
  • an alloy with 6% aluminum (Al) by weight, 2% chromium (Cr) by weight, 2% tin (Sn) by weight, 2% zirconium (Zr) by weight, 2% molybdenum (Mo) by weight, and the balance titanium (Ti).
  • Silicon (Si) up to 0.25% by weight can also be present, and other elements, such as iron (Fe), carbon (C), oxygen (O), nitrogen (N), and/or hydrogen (H) may also be present.
  • the titanium alloy preferably contains between 5 and 6.5% aluminum by weight, and all subranges therebetween, more preferably between 5.25 and 6.25% aluminum by weight, and all subranges therebetween, and most preferably 6.04% aluminum by weight.
  • the titanium alloy preferably contains between 1.5 and 2.5% tin by weight, and all subranges therebetween, more preferably between 1.75 and 2.25% tin by weight, and all subranges therebetween, and most preferably 1.99% tin by weight.
  • the titanium alloy preferably contains between 1.5 and 2.5% chromium by weight, and all subranges therebetween, more preferably between 1.75 and 2.25% chromium by weight, and all subranges therebetween, and most preferably 1.93% chromium by weight.
  • the titanium alloy preferably contains between 1.5 and 2.5% molybdenum by weight, and all subranges therebetween, more preferably between 1.75 and 2.25% molybdenum by weight, and all subranges therebetween, and most preferably 1.99% molybdenum by weight.
  • the titanium alloy preferably contains between 1.5 and 2.5% zirconium by weight, and all subranges therebetween, more preferably between 1.75 and 2.25% zirconium by weight, and all subranges therebetween, and most preferably 2.00% zirconium by weight.
  • the titanium alloy may also preferably contain between 0.05 and 0.25% silicon by weight, and all subranges therebetween, more preferably between 0.1 and 0.2% silicon by weight, and all subranges therebetween, and most preferably 0.15% silicon by weight.
  • the titanium alloy may contain additional elements.
  • the alloy may contain up to 0.25%, more preferably up to 0.15% (and all subranges therebetween), iron by weight; up to 0.15%, more preferably up to 0.08% (and all subranges therebetween), carbon by weight; up to 0.25%, more preferably up to 0.15% (and all subranges therebetween), oxygen by weight; up to 0.1%, more preferably up to 0.05% (and all subranges therebetween), nitrogen by weight; and/or up to 0.025%, more preferably up to 0.015% (and all subranges therebetween), hydrogen by weight.
  • the titanium alloy contains 0.09% iron by weight, 0.01% carbon by weight, 0.11% oxygen by weight, 0.004% nitrogen by weight, 0.0005% hydrogen by weight.
  • the balance of the titanium alloy comprises titanium.
  • the Triplex heat treatment process may provide good strength and good fracture toughness for airframe structures. But because a steam turbine blade is different, a modified process may be necessary.
  • this invention uses a heat treatment practice for the Ti-62222 alloy to produce a fine grain size, which may produce the right balance of properties for this application.
  • This is the Fine Grain Heat Treat process and a preferred embodiment of the process details are listed in Table 1.
  • a difference is that a beta anneal step is not required. The absence of the beta anneal step may produce a significant difference in microstructure as shown in FIG. 5 and improvement in properties as shown in Table 2 set forth below.
  • a titanium alloy is exposed to a forging start temperature preferably ranging from 1500° F. to 1800° F., and all subranges therebetween, more preferably from 1600° F. to 1700° F., and all subranges therebetween, and most preferably at 1650° F.
  • a beta anneal process step the titanium alloy is exposed to an alpha-beta anneal process step having a temperature ranging from 1550° F. to 1850° F., and all subranges therebetween, more preferably from 1650° F. to 1750° F., and all subranges therebetween, and most preferably at 1700° F.
  • the alpha-beta anneal process step preferably includes a water quench.
  • the titanium alloy is exposed to aging at a temperature ranging from 800° F. to 1200° F., and all subranges therebetween, more preferably from 900° F. to 1100° F., and all subranges therebetween, and most preferably at 1000° F.
  • the aging preferably occurs for a length of time ranging from 1 hour to 24 hours, and all subranges therebetween, more preferably from 6 hours to 10 hours, and all subranges therebetween, and most preferably for 8 hours.
  • Test buckets were processed into blade shapes as shown in FIG. 1 .
  • the starting material had a composition as follows: 6.04% wt. Al; 1.99% wt. Sn; 1.93% wt. Cr; 1.99% wt. MO; 2.00% wt. Zr; 0.15% wt. Si; 0.09% wt. Fe; 0.01% wt. C; 0.11% wt. O; 0.004% wt. N; 0.005% wt. H; balance Ti.
  • the forging was done in closed dies.
  • the temperatures for the forging and heat treatment process are listed as the “Triplex” process in Table 1.
  • As the requirements for the steam turbine blade include good fatigue resistance a different heat treatment was also tried. This is called the “Fine Grain” process in Table 1. In some applications, fine grains may enhance fatigue resistance.
  • Table 2 lists mechanical properties obtained for both the Triplex heat treatment and the Fine Grain process.
  • a latter stage steam turbine bucket can operate as high as 400° F. under some specific conditions. Accordingly, tensile properties were measured also at 400° F. Fracture toughness and fatigue properties may stay the same or gets better with temperature, and thus these properties were measured only at room temperatures.
  • HCF High cycle fatigue
  • test frequency 45 Hz was used not because that the bucket will typically experience such frequencies in commercial operation but because that is the highest frequency that can be tested on a fatigue test machine. It is believed that the test frequency does not affect the results significantly. Rather, it is believed that the number of cycles is a relatively more important testing criteria.
  • the Fine Grain process shows almost a ten-fold improvement in the number of cycles to failure.
  • Low cycle fatigue (LCF) occurs only during start up and shut down. This happens because the blade goes through a transient in load during these times.
  • steam turbines may not experience many starts and shutdowns.
  • the test was conducted conservatively at a high strain range of 1%, which is believed to be well above anything that would typically happen in a typical steam turbine. It can be seen that the Fine Grain process is greater than five-fold over the Triplex process.
  • FIG. 5 shows the grain structure for the titanium alloy treated using the Triplex and the Fine Grain process. It can be seen that the grain diameter of the Triplex process is 10 times more than the Fine Grain process.
  • FIG. 6 is plot of the relative erosion resistance of several alloys.
  • Stellite 6 B is a cobalt-based alloy which is used in the prior art as an erosion shield which is physically attached to the leading edge of the blade.
  • Ti-6-4 is the current titanium alloy used for steam turbine blades below 45 inches in length.
  • Ti6Q2( ⁇ ) is an alloy in accordance with an embodiment of the present invention and used in the beta-processed or Triplex heat treat listed in Table 1.
  • Ti6Q2( ⁇ / ⁇ ) is the alpha-beta or fine grain processed version of this alloy. The erosion test is done in a laboratory test under accelerated conditions of water droplet erosion.
  • FIG. 6 provides a relative comparison of the erosion resistance (or volume loss of metal).
  • the test has been calibrated to the erosion rate for real buckets and is believed to be valid for the relative ranking. It can be seen that the Triplex processed alloy has very high volume loss of material compared to stellite. It is even higher than the conventionally used Ti-6-4 alloy. But the fine grain processed alloy is coming close to stellite 6 B in volume loss. This indicates that with proper design controls it may be possible to make a long titanium alloy bucket with this material in the fine grain process which will not need any separately joined stellite or other shield. This may represent a substantial savings in cost as well as a reduction in the risk of separation.
  • this fine grain process for an alloy in accordance with the present invention may achieve the goals and requirements for long (i.e., greater than 45 inches) steam turbine blades.

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
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  • Metallurgy (AREA)
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  • General Engineering & Computer Science (AREA)
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  • Turbine Rotor Nozzle Sealing (AREA)
US11/669,607 2007-01-31 2007-01-31 Methods and articles relating to high strength erosion resistant titanium alloy Abandoned US20080181808A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US11/669,607 US20080181808A1 (en) 2007-01-31 2007-01-31 Methods and articles relating to high strength erosion resistant titanium alloy
EP08100604A EP1953251A1 (en) 2007-01-31 2008-01-17 Method and article relating to a high strength erosion resistant titanium Ti62222 alloy
KR1020080009113A KR20080071908A (ko) 2007-01-31 2008-01-29 고강도 내식성 티타늄 합금에 관한 방법 및 제품
JP2008018421A JP2008190039A (ja) 2007-01-31 2008-01-30 高強度耐エロージョン性チタン合金に関する方法及び物品
CNA200810009528XA CN101235449A (zh) 2007-01-31 2008-01-31 涉及高强度耐腐蚀钛合金的方法和制品

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US (1) US20080181808A1 (zh)
EP (1) EP1953251A1 (zh)
JP (1) JP2008190039A (zh)
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US20120308390A1 (en) * 2011-06-03 2012-12-06 Hitachi, Ltd. Steam turbine
CN103014575A (zh) * 2012-12-26 2013-04-03 洛阳双瑞特种装备有限公司 一种提高含Ti耐蚀合金锻件抗腐蚀性能的锻造方法
TWI585806B (zh) * 2008-04-11 2017-06-01 荏原製作所股份有限公司 試料觀察方法與裝置，及使用該方法與裝置之檢查方法與裝置
US10385702B2 (en) * 2015-06-30 2019-08-20 Napier Turbochargers Ltd Turbomachinery rotor blade
US11674200B2 (en) 2018-05-07 2023-06-13 Ati Properties Llc High strength titanium alloys
CN116516273A (zh) * 2023-05-25 2023-08-01 宝鸡西工钛合金制品有限公司 一种适用于Ti6242合金叶片的多重退火处理工艺
US11724813B2 (en) 2021-05-24 2023-08-15 General Electric Company Midshaft rating for turbomachine engines
US11920231B2 (en) 2018-08-28 2024-03-05 Ati Properties Llc Creep resistant titanium alloys

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JP6100037B2 (ja) 2013-03-13 2017-03-22 三菱重工業株式会社 蒸気タービン翼製造方法
CN104805328B (zh) * 2014-01-24 2017-10-20 深圳市洁驰科技有限公司 一种钛合金、制备方法及其应用
JP6242700B2 (ja) 2014-01-31 2017-12-06 三菱日立パワーシステムズ株式会社 タービン翼の製造方法
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BR112016024906A2 (pt) * 2014-05-15 2017-08-15 Gen Electric liga de titânio, componente e método para formação de um componente
WO2016142474A1 (en) * 2015-03-11 2016-09-15 Sandvik Intellectual Property Ab A process for manufacturing a product of commercially pure titanium
CN106048307B (zh) * 2016-08-20 2017-10-10 西北有色金属研究院 一种七元系两相钛合金
CN108843402A (zh) * 2018-06-08 2018-11-20 南京赛达机械制造有限公司 一种耐高温钛合金汽轮机叶片
CN108754298A (zh) * 2018-06-08 2018-11-06 南京赛达机械制造有限公司 一种抗冲击钛合金汽轮机叶片及其制造方法
CN109763026A (zh) * 2018-12-29 2019-05-17 西北工业大学 一种高强度铸造用钛合金及其制备方法
US11242588B2 (en) 2019-12-12 2022-02-08 General Electric Company System and method to apply multiple thermal treatments to workpiece and related turbomachine components
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