WO2016025045A2 - Titanium alloys and their methods of production - Google Patents
Titanium alloys and their methods of production Download PDFInfo
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- WO2016025045A2 WO2016025045A2 PCT/US2015/030601 US2015030601W WO2016025045A2 WO 2016025045 A2 WO2016025045 A2 WO 2016025045A2 US 2015030601 W US2015030601 W US 2015030601W WO 2016025045 A2 WO2016025045 A2 WO 2016025045A2
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- titanium
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 57
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000004519 manufacturing process Methods 0.000 title description 10
- 239000000956 alloy Substances 0.000 claims abstract description 133
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 132
- 239000010949 copper Substances 0.000 claims abstract description 41
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 38
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 37
- 239000010703 silicon Substances 0.000 claims abstract description 32
- 229910052802 copper Inorganic materials 0.000 claims abstract description 29
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 26
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052742 iron Inorganic materials 0.000 claims abstract description 23
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 17
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 17
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 17
- 239000011733 molybdenum Substances 0.000 claims abstract description 17
- 239000010936 titanium Substances 0.000 claims abstract description 17
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 16
- 229910021341 titanium silicide Inorganic materials 0.000 claims abstract description 16
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 13
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000001301 oxygen Substances 0.000 claims abstract description 12
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 12
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract description 12
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 11
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 claims description 35
- 229910021332 silicide Inorganic materials 0.000 claims description 33
- 239000000243 solution Substances 0.000 claims description 29
- 238000005242 forging Methods 0.000 claims description 19
- 238000000265 homogenisation Methods 0.000 claims description 13
- 239000003381 stabilizer Substances 0.000 claims description 13
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 9
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 9
- 229910052726 zirconium Inorganic materials 0.000 claims description 9
- 238000005266 casting Methods 0.000 claims description 2
- 235000016768 molybdenum Nutrition 0.000 claims 4
- 239000000203 mixture Substances 0.000 abstract description 35
- 238000010438 heat treatment Methods 0.000 description 45
- 239000002245 particle Substances 0.000 description 44
- 238000012545 processing Methods 0.000 description 44
- 230000035882 stress Effects 0.000 description 35
- 238000001816 cooling Methods 0.000 description 31
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 24
- 239000000463 material Substances 0.000 description 24
- 238000003466 welding Methods 0.000 description 23
- 230000032683 aging Effects 0.000 description 22
- 239000007787 solid Substances 0.000 description 22
- 238000011282 treatment Methods 0.000 description 18
- 238000010791 quenching Methods 0.000 description 17
- 230000000171 quenching effect Effects 0.000 description 17
- 239000007789 gas Substances 0.000 description 16
- 229910000734 martensite Inorganic materials 0.000 description 16
- 230000008569 process Effects 0.000 description 13
- 150000001875 compounds Chemical class 0.000 description 11
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 10
- 239000002244 precipitate Substances 0.000 description 9
- 230000000717 retained effect Effects 0.000 description 9
- 238000007792 addition Methods 0.000 description 8
- 238000013459 approach Methods 0.000 description 8
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- 229910021330 Ti3Al Inorganic materials 0.000 description 7
- 230000015572 biosynthetic process Effects 0.000 description 7
- 238000013519 translation Methods 0.000 description 7
- 229910052721 tungsten Inorganic materials 0.000 description 6
- CYKMNKXPYXUVPR-UHFFFAOYSA-N [C].[Ti] Chemical compound [C].[Ti] CYKMNKXPYXUVPR-UHFFFAOYSA-N 0.000 description 5
- 230000000712 assembly Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 5
- IUYOGGFTLHZHEG-UHFFFAOYSA-N copper titanium Chemical compound [Ti].[Cu] IUYOGGFTLHZHEG-UHFFFAOYSA-N 0.000 description 5
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 238000001556 precipitation Methods 0.000 description 5
- 238000007711 solidification Methods 0.000 description 5
- 230000008023 solidification Effects 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 5
- 239000010937 tungsten Substances 0.000 description 5
- 238000000137 annealing Methods 0.000 description 4
- 230000005266 beta plus decay Effects 0.000 description 4
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 239000006104 solid solution Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000005749 Copper compound Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 2
- 239000003570 air Substances 0.000 description 2
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- 229910000714 At alloy Inorganic materials 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910004339 Ti-Si Inorganic materials 0.000 description 1
- 229910009601 Ti2Cu Inorganic materials 0.000 description 1
- 229910009816 Ti3Si Inorganic materials 0.000 description 1
- -1 Ti5Si3 Chemical compound 0.000 description 1
- 229910009871 Ti5Si3 Inorganic materials 0.000 description 1
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- 238000005275 alloying Methods 0.000 description 1
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- 238000010304 firing Methods 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
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Classifications
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D7/00—Casting ingots, e.g. from ferrous metals
- B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
-
- 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
- F01D5/28—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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/174—Titanium alloys, e.g. TiAl
-
- 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 generally relates to titanium alloys and their method of production.
- the titanium alloys disclosed herein are particularly suitable for use in rotary machines, such as gas turbines.
- At least some known rotary machines such as, but not limited to, steam turbine engines and/or gas turbine engines, include various rotor assemblies, such as a fan assembly, a compressor, and/or turbines that each includes a rotor assembly.
- At least some known rotor assemblies include components such as, but not limited to, disks, shafts, spools, bladed disks ("brisks"), seals, and/or bladed integrated rings (“brings”) and individual dovetail attached blades. Such components may be subjected to different temperatures depending on an axial position within the gas turbine engine.
- gas turbine engines may be subjected to an axial temperature gradient that extends along a central longitudinal axis of the engine.
- gas turbine engine components are exposed to lower operating temperatures towards a forward portion of the engine and higher operating temperatures towards an aft portion of the engine.
- known rotor assemblies and/or rotor components are generally fabricated from materials capable of withstanding an expected maximum temperature at its intended position within the engine.
- rotary assemblies and/or rotary components are each generally forged from a single alloy that is capable of wi thstanding the expected maximum temperature of the entire rotary assembly and/or rotary component.
- Ti-17 Ti-5AI-4Mo-4Cr-2Sn-2Zr
- Ti-6246 Ti-6Al-2Sn-4Zr-6Mo
- Ti- 64 Ti-6A1-4V
- Components such as blisks or integrally bladed rotors can also be fabricated from one or more alloys using solid state welding joining processes,
- the hub may be produced from one alloy such as beta processed Ti-6246 or beta processed Ti-17 having excellent thick section properties, while the airfoil may be produced from a second ahoy such as alpha plus beta processed Ti-64 having excellent fatigue properties in relative!)' small section sizes and foreign object damage (FOD) properties.
- Thick section refers to sectional size of exemplary components made from titanium alloys, for example, larger than about one to two inches in section, or another example from about one inch to 3 inches, again another example up to six inches or more.
- the airfoil may be solid state welded to the hub utilizing processes such as translation friction welding or linear friction welding.
- Blisks may also be solid state welded using a hub and an airfoil of the same alloy such as alpha plus beta processed Ti-64, where the alpha plus beta processed Ti-64 hub properties are sufficient for the application.
- Components such as compressor rotor drums may also be fabricated from one or more alloys using solid state welding joining processes such as inertia welding. For an inertia welded rotor, it may be desirable to have a higher temperature alloy used in the later stages of the rotor.
- Ti-64 is an alpha/beta processed titanium alloy that is highly
- Ti-64 has limited thick section strength and high-cycle fatigue (HCF) capability, especially at low A ratio (where A is the ratio of alternating stress divided by the mean stress), and deforms to a relatively high degree during FOD.
- HCF high-cycle fatigue
- Ti-17 and Ti-6246 are beta processed, are not as easily mamifacturable, have more anisotropic properties (especially ductility) as a result of beta processing, have higher density, are not as tolerant to FOD, are not as easily weldable or repairable, and have a higher cost.
- Ti-17 and Ti-6246 have good thick section strength, have good HCF capability, have a superior temperature capability than Ti- 64, and deform relatively less than Ti-64 during FOD impact,
- Ti-64 e.g., relatively isotropic properties, a relatively low density, is tolerant to FOD and does not deform too much during the FOD, and is repairable
- some of the benefits of Ti-17 and Ti-6246 e.g., thick section tensile strength, and HCF strength
- a composition of matter is generally provided, in one embodiment, a titanium alloy comprising about 5 wt% to about 8 wt% aluminum; about 2.5 wt% to about 5.5 wt% vanadium; about 0.1 wt % to about 2 wt% of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt% to about 0.2 w ⁇ % carbon; up to about 0.3 wt% oxygen; silicon and copper; and titanium.
- a turbine component is generally provided, in one embodiment, that comprises an article made from a titanium alloy having about 5 wt% to about 8 wt% aluminum; about 2.5 wt% to about 5.5 wt% vanadium; about 0.1 wt % to about 2 wt% of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt% to about 0.2 wt% carbon; up to about 0.3 wt% oxygen; at least one of silicon or copper; and titanium.
- a titanium alloy having about 5 wt% to about 8 wt% aluminum; about 2.5 wt% to about 5.5 wt% vanadium; about 0.1 wt % to about 2 wt% of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt% to about 0.2 wt% carbon; up to about 0.3 wt% oxygen; at least one of silicon or copper; and titanium.
- Methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature, with method steps comprising; hot working a titanium alloy ingot at a temperature that is above the beta transus temperature, wherein the titanium alloy ingot comprises about 5 wt% to about 8 wt% aluminum; about 2.5 wt% to about 5.5 wt% vanadium; about 0.1 wt % to about 2 wt% of one or more element selected from the group consisting of iron and molybdenum; about 0.01 wt% to about 0.2 wt% carbon; up to about 0,3 wt% oxygen; up to 2 wt% of one or more element selected from the group consisting of zirconium and tin; at least one of silicon or copper; and titanium; hot working the titanium alloy ingot at a temperature that is below both the beta transus temperature of the alloy and the silicide solvus temperature; hot working the titanium alloy ingot at a temperature that is above the beta transus
- FIG. 1 is a schematic illustration of an exemplary turbofan gas turbine engine assembly
- FIG. 2 is an isometric view of a blisk
- FIG. 3 is sectional view through two stages of blisks depicting optional location for weld zones
- Fig. 4 shows a chart of the maximum beta grain size for certain alloy compositions with respect to the beta annealing temperature
- Fig. 5 shows a plot of a wide range of commercial alloys based on their calculated aluminum equivalence and molybdenum equivalence
- Fig. 6, expanded from Fig. 5, shows a portion of aluminum equivalence and molybdenum equivalence of selected commercial alloys and includes example alloys of the present invention.
- axial and axially are used throughout this application and reference directions and orientations that are substantially parallel to a central rotational axis of the rotary machme.
- axial- circumferential edge is used throughout this application to refer to circumferential edges that are orientated substantially perpendicular to the central rotational axis of the rotary machine.
- radial and radially are used throughout this application to reference directions and orientations that are substantially perpendicular to the central rotational axis.
- radial-circumferential plane is used throughout this application to reference planes orientated substantially perpendicular to the central rotational axis of the rotary machme.
- forward is used throughout this application to refer to directions and positions located upstream and towards an inlet side of a gas turbine engine
- aft is used throughout this application to refer to directions and positions located downstream and towards an exhaust side of the gas turbine engine.
- a composition of matter in the cl ass of titanium alloys is generally provided.
- a component is also provided that is formed from the titanium alloy modified from Ti-64 in order to preserve the desired properties of Ti-64 (e.g., relatively isotropic properties, a relatively low density, tolerance to FOD,
- the cost of the new modified Ti-64 alloy can be minimized by designing the composition such that a high percentage of widely available Ti ⁇ 64 recycled materials can be used. Additionally, the billet and forge processing approach may be kept as close to Ti-64 as possible in order to minimize cost.
- a component within a turbofan engine assembly can be constructed from a titanium alloy.
- the titanium alloy includes, in one embodiment, about 5 wt% to about 8 wt% aluminium (e.g., about 6 wt% to about 7 wt% aluminium); about 2.5 wt% to about 5.5 wt% vanadium (e.g., about 3 wt% to about 5 wt% vanadium, such as about 3.5 wt% to about 4.5 wt% vanadium); about 0.1 wt % to about 2 wt% iron (e.g., about 0.1 wt% to about 1 wt% iron, such as about 0.1 wt% to about 0.6 wt% iron); about 0,01 wt% to about 0.2 wt% carbon (about 0.01 wt% to about 0.1 wt% carbon); at least one of silicon or copper, with the combined amount of silicon and copper being about 0.1 wt%
- the titanium alloy includes, in one embodiment, titanium; about 5 wt% to about 8 wt% aluminum; about 2.5 wt% to about 5.5 wt% vanadium; about 0.1 wt % to about 2 wt% iron; about 0.01 wt% to about 0.2 wt% carbon; and at least one of silicon or copper, with the combined amount of silicon and copper being about 0.1 wt% to about 4 wt% (e.g., about 0.1 wt% to about 2 wt% silicon and/or about 0.5 wt% to about 2 wt% copper).
- the titanium alloy can also optionally include up to about 0.3 wt% oxygen (e.g., about 0.1 wt% to about 0.2 wt% oxygen), up to about 0.05 wt% nitrogen (e.g., about 0.001 wt% to about 0.05 wt% nitrogen); up to about 2 wt% molybdenum (e.g., about 0.5 wt% to about 1 wt % molybdenum); up to about 2 wt% tin (e.g., about 0.5 wt% to about 2 wt % tin); up to about 2 wt% zirconium (e.g., about 0.5 wt% to about 2 wt % zirconium), up to about 2 wt% tungsten (e.g.. about 0.1 wt% to about 2 wt% tungsten), or combinations thereof.
- up to about 0.3 wt% oxygen e.g., about 0.1 wt% to
- compositional ranges set forth above can be summarized as shown in Table 1 below:
- Figure 2 shows an example of a component that may be constructed from a titanium alloy, depicting an isometric view of a single stage blisk 50, alternatively known as an integrally bladed rotor.
- the blisk 50 has a hub 52 that circumscribes the central rotational axis 12, reference also the axis 12 of turbofan engine assembly 10 of Figure 1. Extending substantially radially from hub 52 are airfoils 60.
- a bi-metallic blisk where the hub 52 and airfoils 60 are different alloys, may be preferred.
- the airfoil 60 may be solid state welded to the hub 52 utilizing processes such as translation friction welding or linear friction welding. Therefore, it may be desirable to select a material that provides excellent thick section properties for the hub 52, and excellent fatigue properties in relatively small section sizes and FOD properties for the airfoil 60.
- hub 52 is made from an example inventive alloy of the present invention, with the airfoil 60 being made from a commercially available, or conventional, materials with desirable fatigue life performance, such as, for example Ti-64,
- the interface between hub 52 and airfoil 60 can be referred to as the weld or heat affected zone 70, In this zone 70, a mix of hub and airfoil alloys are present, along with a wide range of
- microstructures This mix of alloys and range of microstructures may compromise the thick section fatigue, FGD, etc. of the portion of the biisk 50.
- hub 52 and airfoil 60 are both made from the same example inventive alloy of the present invention, or made from separate example inventive alloys of the present invention.
- hub 52 and airfoil 60 being the same inventive alloy, in zone 70, no mix of hub and airfoil alloys are present, but a wide range of microstructures exists. This range of microstructures may again compromise the thick section fatigue, FOD, etc. of the portion of the blisk 50.
- adjacent stages of blisks may be inertia welded. Similar to the bi-metallic hub/ airfoil, it may be desirable to have a front blisk stage made from a first material and an aft stage blisk made from a second material. As shown in Figure 3, the front blisk stage 80 may be made from an example inventive alloy of the present invention and the aft blisk stage 90 may be made from
- weld zone or heat affected zone 70 is presen t and a mix of front blisk and aft blisk alloys are presen t, along with a wide range of microstructures in zone 70, representing an area of reduced material properties.
- adjacent front blisk stage 80 and aft blisk stage 90 are both made from the same example inventive alloy of the present invention, or may be made from separate example inventive alloys of the present invention.
- any example inventive alloy may be used alone or in combination with commercially available alloys for one or more of the airfoil 60, hub 52, blisk 50, front stage blisk 80 or back stage blisk 90.
- Figure 3 describes two stages, more than two stages of blisks may be contemplated.
- microstructure and beta transus approach curves to refine the microstrueture (a P and lamellar morphology).
- C, O, and interstitials act as a stabilizers and can be present for solid solution strengthening.
- Cu, Mo, Fe, Si, and W act as ⁇ stabilizers, and may serve to increase hardenability.
- too much of Mo, Fe, and/or W can increase the density to levels too high, and/or may have the potential to form deleterious phases during rapid cooling following solid state welding.
- the weld zone may contain hexagonal martensitie alpha prime (hexagonal phase) that is relatively easy to decompose to alpha phase and precipitate out beta phase on subsequent stress-relief/aging treatment.
- alpha prime martensite start and finish temperatures are above room temperature, in contrast to Ti-64, alloys with increased beta stabilizer content can have martensite start and finish temperatures which can be lowered toward and below room temperature.
- Ti-6246 wi ll have lower martensite start and finish temperatures than Ti-64, showing a tendency to retain higher amounts of beta (martensite finish is below room temperature) and may form a percentage of orthorhombic martensite (indicating martensite start is above room temperature).
- the lower Al content and combination of Mo and Cr in Ti-17 produce a more heavily beta stabilized composition which may have both martensite start and martensite finish suppressed to below room temperature, so may show fully retained beta following rapid quenching from high temperatures, e.g. as may occur in a solid state weld, in the case of retained beta, it may be difficult to form alpha and beta phases of desired sizes and distribution following a conventional stress relief/age heat treatment.
- retained beta may also contain fine metastable athermal omega (termed to refer to following rapid quenching) or metastable omega (termed to distinguish a modest maturation beyond athermal omega) that transforms readily at lower temperatures, e.g. well below those applied during conventional stress relief and age heat treatment temperatures.
- This transformation of omega phase can occur during reheating of a component on the rise to the final stress relief and age heat treatment temperature.
- Associated with the transformation of metastable omega is a parallel presentation of increasing amounts of equilibrium alpha precipitates, the number density of which is increased by the presence and maturation of omega.
- the base alloy composition is designed such that it can be stress relieved and/or aged at a high temperature, for example at about 1300 °F or higher, enabling sufficiently high toughness in the weld to be achieved, whilst not adversely affecting the base alloy strength and fatigue.
- the new compositions that are especially useful in thick section components, and do not rely predominantly on rapid cooling and aging to achieve higher strength via fine alpha precipitation such as Ti-6246 and Ti-17. Rather, they rely on alternative strengthening mechanisms that remain effective, even at slower cooling rates from solution heat treatment temperature that may be experienced in a large section size component.
- microstructures between the inventive alloy hub and the Ti ⁇ 64 alloy airfoil may result in a solid state weld having a lower tendency to form defects during or following the welding process.
- the titanium alloy includes, in one embodiment, about 0.1 wt% to about 2 wt% silicon (e.g., about 0.5 w r t% to about 2 wt%, such as about 0.5 wt% to about 1 wt%).
- Si can lead to a refined microstructure in the titanium alloy, which can result in increased strength and potentially increased HCF strength.
- Si in solution can precipitate as a titanium silicide compound.
- the titanium silicide compound can be any compound containing both titanium and silicon (e.g., Ti 5 Si 3 , Ti 3 Si, etc.), with or without other elements (e.g., Sn and/or Zr) within the compound.
- the alloy composition can be designed with sufficient silicon such that the silicide solvus temperature of the titanium silicide compound is sufficiently above the beta transus temperature of the alloy.
- the silicide solvus temperature of a titanium silicide compound can be at least about 50 °F greater than the beta transus temperature of the alloy (e.g., about 75 °F to about 400 °F greater than the beta transus temperature of the alloy).
- the difference in the silicide solvus temperature and the beta transus tem perature of the all oy can allow processing of the ingot billet in the beta plus silicide phase field.
- silicon within the ingot as a result of segregation during solidification, during subsequent billet processing intended to be in the beta plus silicide phase field, it is possible that in local regions that are depleted in silicon relative to the overall composition, this local region may actually be above the local silicide solvus.
- These areas with different silicon content can be reduced via a homogenization treatment (as discussed below) to produce a volume fraction and size of the silicide particles that are sufficiently small and spaced apart to lead to a finer beta grain structure after subsequent processing.
- the silicide particle volume fraction and/or size are not appropriate, even though the billet is recrystallized in the beta plus silicide phase field, a uniform, very refined beta structure may not be achievable. Regions enriched in silicon content due to segregation may also result locally in material being above the beta transus during treatments intended to be below the beta transus. If this occurs, it is believed (without wishing to be bound by any particular theory) that in these silicon-enriched regions, silicide particles will form with these particles pinning the beta grains. Thus, even though these silicon-enriched regions may be above the local beta tranus, a refined microstructure may be retained during alpha beta processing, such as billet forging, component forging and/or solution heat treatment.
- a maximum predicted recrystallized beta grain size as a function of annealing temperature in a two phase materia! may be represented by the equation: volume fraction.
- the alloy composition is, in one particular embodiment, formed with the silicide solvus sufficiently higher than the beta transus such that the processing scheme described below is practical.
- the titanium alloys disclosed herein can have a beta transus temperature of about 1700 °F to about 1950 °F and a silicide solvus temperature of about 1775 °F to about 2200 °F.
- Si tends to segregate during solidification.
- a homogenization treatment can optionally be performed prior to any subsequent processing steps in order to smooth out the local peak/trough in the Si composition in the ingot. That is, a more uniform distribution of Si in the alloy with smaller sizes can be formed to create the potential for finer beta grain recrystallization when recrystallized in the beta plus silicide phase field. For example, a
- homogenization treatment can be performed at a treatment temperature that is above both the beta transus temperature of the al loy and the silicide solvus temperature of the titanium silicide compounds.
- the diffusivity of Si in Ti-64 appears to be faster than that determined from the binary Ti-Si system, resulting in a potentially lower homogenization temperature and/or shorter homogenization time, reference lijima, Y., Lee, S.Y., Hirano, K. (1993) Phil. Mag. A 68: pp. 901-14, the disclosure of which is also incorporated by reference herein.
- the homogenization treatment may be performed after a portion of the hot working bill et operations.
- a further potential advantage of a homogenization treatment is as follows: if during
- silicon-rich particles may precipitate. Above a certain size range in the final heat treated condition, these particles may reduce mechanical properties such as fatigue, ductility, impact resistance and weldability.
- Use of a homogenization treatment and optionally a controlled cooling above a certain rate will result in either complete dissolution of these particles, or precipitation of a finer particle during cooling, resulting in improvements in properties such as fatigue, ducti lity, impact resistance and weldability.
- additional silicon-rich particles may be expected to form, however, the size of these particles wi ll likely be smal ler than those produced during initial solidification and cooling.
- the al loy is subjected to high temperature beta processing at beta processing temperatures that are above both the beta transus temperature of the alloy and the silicide solvus
- the high temperature beta processing can be carried out from just above to several hundred degrees above the silicide solvus temperature (e.g., about 10 °F above to about 400 °F above). This high temperature beta processing can help assure that the alloy is substantially ail in the beta phase.
- the alloy billet can then be subjected to lower temperature alpha/beta work at temperatures below both the beta transus temperature of the alloy and the silicide solvus temperature. This alpha/beta work is at least partially retained, and leads to recrystallization in the following or subsequent step.
- the alloy billet can then be subjected to beta processing (e.g., an annealing operation or a beta forging operation, see
- the alloy billet can be subjected to a post-beta processing cooling process using a variety of cooling techniques known to those skilled in the art, such as, but not limited to, fan air, oil, gas, and water quenching, to produce a post-forged cooled article.
- the alloy billet is cooled as fast as possibl e to minimize the size of the microstructure formed at room
- the beta phase begins to transform to alpha phase below the beta transus temperature.
- fast quenching leads to thinner alpha platelets formed, which later transforms into smaller alpha particles in subsequent alpha/beta work and, in turn, controls HCF in the resulting article.
- a subsequent alpha/beta work step is then typically performed, which is designed to convert the alpha platelets into primary (or equiaxed) alpha particles with as small of a size as possible, at temperatures below both the beta transus temperature of the alloy and the silicide solvus temperature.
- This alpha/beta work in combination with the beta processing steps above, leads to much smaller prior beta grain sizes, which in turn results in significantly finer alpha colony size (with each colony being an organization of plates having a simil ar cry stal orientation).
- the primary alpha grain size can be smaller because it started out with thinner platelets (compared to that in alpha/beta processed Ti-64), which leads to improved strength and HCF properties. It should also be noted that the much finer colon)' sizes result in improved ultrasonic inspectability at the billet and component stage.
- the processed billet can then be alpha/beta forged at forging temperatures below bot the beta transus temperature of the alloy and the silici.de solvus temperature. It should be noted that the cooling rate used for the post-forged cooling process can be dependent on several factors.
- the post-forged cooled article can then be solution heat treated to a temperature below the beta transus and the silicide solvus temperature (e.g., a temperature from about 50 °F to about 250 °F below the beta transus) but at a temperature above the alpha/beta component forged processing temperature, and held for a certain time to ensure that the entire part is at the heat treatment temperature (e.g., up to about 4 hours) to produce a solution heat-treated article containing particles of primary alpha in a matrix of beta phase.
- the silicide solvus temperature e.g., a temperature from about 50 °F to about 250 °F below the beta transus
- This solution heat-treated article can then be subjected to a controlled post- solution cooling process to produce a post-solution cooled article.
- the cooling rate following post solution heat treatment is generally desired to be as quick as possible.
- the controlled post solution-cooling rate in articles having a cross- section size on the order of 6 inches or more may be faster than about 100 °F/minute, calculated from an approximately linear cooling rate (e.g., from about 25-50°F below the solution temperature to the beginning of the secondary alpha precipitation).
- an approximately linear cooling rate e.g., from about 25-50°F below the solution temperature to the beginning of the secondary alpha precipitation.
- the cooling occurs as quickly as possible.
- the alloy structure is designed (e.g., via pre-machining) such that the slower cooling rates (associated with these thicker parts) are minimized and/or controlled such that improvements in strength FICF with good ductility are realized.
- solution heat-treating methods can include heat- treating in air, vacuum, or inert (i.e. argon) atmospheres.
- the controlled post-solution cooling process can have the most significant impact on achieving the strength (particularly HCF) and desired ductility and may again involve a variety of cooling techniques known to those skilled in the art, such as fan air, oil, gas, polymer, salt and water quenching.
- solution heat treatment can he conducted above the beta transus, but below the silicide solvus.
- This processing method results in a finegrained, beta-annealed structure (e.g., good for airframe components) in that the resultant structure has similar fatigue crack growth properties to a Ti-64 beta annealed structure, but because the beta grain size is smaller, and the presence of Si and/or Cu, and Fe and/or Mo, thick section strength and HCF will be better.
- the billet and forge processing can be streamlined, for example, including initial beta hot work followed by alpha-beta hot work to form the forging from the billet prior to solution heat treatment of the forging above the beta transus but below the silicide solvus.
- the forging can be pre- machined in order to increase the cooling rate to further increase strength and HCF properties.
- the configuration of the post forged cooled article which may involve rough machining after the final forge operation, and the specific cooling method, may be selected to achieve the desired controlled post- solution cooling rate range. In portions of the article where ductility may be of less concern, controlled post-solution cooling rates above the desired range are acceptable. Similarly, controlled post-solution cooling rates that fall below the desired range are acceptable in portions of the article where lower strength or HCF is allowable.
- the post-solution cooled article may be subjected to an aging and/or stress relief heat treatment at a temperature of from about 1 100 °F (about 593 °C) to about 1350 °F (about 732 °C) or higher for a period of about 1 hour to about 8 hours, followed by uncontrolled cooling to about room temperature, to produce a final article.
- a temperature less than 1 100 °F may be used, but may require a longer time. It is known that the addition of too high a level of Si may result in reduced ductility and/or toughness due to the presence of silicide particles and/or a greater tendency to form ordered Ti3 Ai particles in the alpha phase, see, for example, Woodfield, A. P.
- the volume fraction of primary alpha present during soluti on h eat treatment will set the local primary alpha composition, and therefore its tendency to form ordered Ti3AI particles during subsequent age and/or stress relief treatments, if ordered Ti3Al particles have a tendency to form during the aging and/or stress relief heat treatment, the temperature can be increased to above the Ti3Al solvus. in this case, it may be necessary to control the cooling rate after heat treatment to minimize the formation of Ti3Al particles. If a subsequent aging and/or stress relief
- the alloy composition may be designed with a level of Si such that the siiicide solvus is below the beta transus, or Si may be entirely in solution, Billet and component forging and heat treatment approaches for this range of alloy compositions may be conducted in a similar manner to
- the ingot may be optionally homogenized, then beta forged followed by an alpha-beta pre-strain, followed by a beta anneal or beta forge, with final billet processing performed below the beta transus. All subsequent component forge and heat treatment steps may then be conducted below the beta transus.
- Any silicides present at alpha beta processing and/or heat treatment temperatures may prevent local beta grain coarsening, and primary alpha coarsening during thermomechaiiical processing and/or heat treatment.
- ordering of the alpha matrix may stil l occur, depending on the volume fraction of primary alpha and levels of other elements such as Al, (), C and/or N added to the alloy. If this occurs, then aging and/or stress relief heat treatment temperatures and/or times may need to be adjusted.
- Cu When Cu is included as a component in the alloy composition, with or without Si present, Cu may form a titanium copper compound precipitate (e.g., Ti 2 Cu) at relatively low temperatures (e.g., about 800 °F to about 1000°F or higher, depending upon the level of Cu in the alloy) in the titanium alloys, which may strengthen the alpha phase resulting in improved strength and HCF properties.
- relatively low temperatures e.g., about 800 °F to about 1000°F or higher, depending upon the level of Cu in the alloy
- the addition of Cu may also lead to refinement of both primary and secondary alpha phases which may also result in improved strength and HCF properties.
- the optional homogenization treatment described above (above the beta transus temperature) may be utilized to smooth out the peak/trough of the Cu composition in the ingot, or may be performed following a portion of the billet hot working operations to covert the ingot into a billet.
- the optional homogenization treatment may also dissolve any primary titanium copper compound precipitates that may be relatively large in size.
- the process for forming the alloy article can be similar to that of the alloy Ti-64 (e.g., initial beta work, alpha/beta pre-strain, beta forging or annealing to recrystallize the beta grains, and final alpha/beta billet processing), with an optional homogenization process (such as described above) prior to processing or after a portion of the billet processing, and an aging treatment after all billet and component processing (including any welding operations, such as inertia welding) to bring out the strength properties from Cu.
- an optional homogenization process such as described above
- an aging treatment after all billet and component processing (including any welding operations, such as inertia welding) to bring out the strength properties from Cu.
- the alloy can then be designed such that following billet conversion and part forging plus heat treatment and quenching (such as described above), an additional lower temperature age treatment can be employed to precipitate out Ti?Cu or other titanium-copper-containing particles, leading to improved strength and HCF properties.
- the copper containing titanium alloy ingot can be high temperature beta processed above the beta transus temperature of the alloy, followed by lower temperature alpha/beta processing at temperatures below the beta transus temperature of the alloy, and then processed through a subsequent high temperature beta process followed by water quenching.
- the final alpha/beta work can then be performed at temperatures below the beta transus temperature of the alloy.
- Component forging can then be performed at temperatures below the beta transus of the alloy.
- solution heat treatment can then be performed at temperatures below the beta transus temperature of the alloy, but slightly above the alpha/beta forge temperature, followed by quenching (e.g., fast quenching as described above).
- quenching e.g., fast quenching as described above.
- a low temperature age treatment to precipitate the titanium-copper particles can then be performed.
- Sn can optionally be included in the alloy composition, as stated above, and can potentially serve to stabilize the titanium silicide (e.g., phase in Si- containing alloys to higher temperatures.
- Sn may act to keep the silicide solvus temperature sufficiently higher than the beta transus temperature to allow for a wider process field for billet conversion during processing, particularly during the beta processing at a beta processing temperature that is above the beta transus temperature of the alloy but below the silicide solvus temperature of the titanium silicide solvus.
- Zr may be optionally included within the alloy composition to potentially serve as a stabilizing component for the titanium silicide phase (e.g., TisSi 3 ) in Si-containing alloys, particularly at elevated temperatures.
- TisSi 3 titanium silicide phase
- carbon can optionally be present in the alloy composition in an amount of about 0.01 wt% to about 0.2 wt% (about 0.01 wt% to about 0.1 wt%).
- the amount of carbon can be increased from a nominal level typically found in Ti ⁇ 64 to about 1000 wppm or greater (but below the titanium carbon containing compound solvus, e.g., Ti 2 C) in order to increase strength and HCF properties.
- the amount of C in the alloy can be increased above the titanium carbon containing compound solvus where the titanium carbon containing compound solvus temperature is above the beta transus temperature.
- the titanium carbon containing compound particles can be used and processed similar to that described above with respect to Si.
- the titanium carbon containing compound particles can be used to control the beta crystallization during billet conversion in order to obtain as fine a prior beta grain size as possible.
- This use of C in the alloy can be used in conjunction with Si (to control the prior beta grain size) and/or Cu (for precipitate strengthening). It is known that additions of C to Ti alloys tend to increase the beta transus and result in a relatively shallow beta approach curve. This allows a relatively low volume fraction of primary alpha to be present at temperatures relatively far below the beta transus, increasing the range of
- the C addition when below the solid solubility limit in the alpha phase may result in increased properties such as strength and HCF due to a combination of C in solid solution in the primary and secondary alpha phases and refined primary alpha grain size.
- too high a level of C may also result in reduced ductility and/or toughness possibly due to a greater tendency to form ordered Ti3Al particles in the primary alpha phase.
- ordered ⁇ 3 ⁇ 1 particles have a tendency to form during the aging and/or stress relief heat treatment, the temperature can be increased to above the ⁇ 3 ⁇ 1 soivus. In this case, it may be necessary to control the cooling rate after heat treatment to minimize the formation of T13A1 particles. If a subsequent aging and/or stress relief temperature is required, then the degree of formation of ⁇ 3 ⁇ particles and impact to properties such as ductility and toughness needs to be considered when selecting the subsequent heat treatment.
- oxygen can optionally be present in the alloy composition up to about 0.3 wt%, or alternatively about 0.1 wt% to about 0,2 wt.
- too high a level of O may also result in reduced ductility and/or toughness due to a greater tendency to form ordered ⁇ 3 ⁇ 1 particles in the primary alpha phase.
- ordered ⁇ 3 ⁇ 1 particles have a tendency to form during the aging and/or stress relief heat treatment, the temperature can be increased to above the Ti3Al soivus. In this case, it may be necessary to control the cooling rate after heat treatment to minimize the formation of ⁇ 3 ⁇ 1 particles. If a subsequent aging and/or stress relief
- Fe and Mo can optionally be present in the alloy singly, or in combination in an amount of [for Fe about 0.1 wt % to about 2 wt% iron (e.g., about 0.1 wt% to about 1 w r t%, such as about 0.1 wt% to about 0.6 wt%), and for Mo up to about 2 wt% (e.g., about 0.5 wt% to about 1.5 wt %, such as about 0.5 wt% to about 1 wt%)].
- Fe and Mo are both beta stabilizers and will tend to reduce the beta tratisus of the alloy.
- Zone 1 contains near alpha commercial alloys that have low beta stabilizer content and are not typically very hardenable in thick section size. These al loys may be used as hub materials for blisks, however, their application may be limited as a result of limited hardenability and relatively poor fatigue properties in thick section size. Zone 1 alloys may form a predominantly hexagonal martensite structure following quenching as a result of solid state welding.
- the solid state welds can typically be toughened by aging at a temperature that will not degrade the base alloy properties away from the weld and heat affected zone. Note, the solid state weld could be toughened by a local heat treatment affecting only material in the vicinity of the weld, however, there are control issues surrounding this approach, including residual stress control. Therefore, it may be more desirable to heat treat the entire welded component.
- Zone 2 contains beta or near-beta commercial alloys that have high beta stabilizer content and are typically hardenable in thick section size following quenching and aging. Alloys such as Ti-17 in zone 2 may be used as hub materials for blisks as a result of their excellent hardenab lity. Zone 2 alloys may form retained beta following quenching as a result of solid state welding. The retained beta welds may be lower strength than the base alloy away from the weld, and require post weld aging to increase the strength of the weld. Aging at lower temperatures may result in excessive hardening in the weld as a result of ultra-fine alpha or omega phase precipitation. Aging at higher temperatures may result in a tough weld, however, depending on the base alloy composition, the higher aging temperature used to toughen the weld may result in a reduction in strength and fatigue in the base alloy material away from the weld.
- Zone 3 contains alpha plus beta alloys having intermediate levels of beta stabilizer content and are hardenable up to intermediate section sizes following quenching and aging.
- Zone 3 in Figures 5 and 6 is shown as a dotted line, and may extend up to the boundaries shown delineating Zones 1 and 2, Alloys such as Ti-6246 in zone 3 may be used as a hub material for blisks as a result of their hardenabiiity.
- Zone 3 alloys may form a combination of orthorhombic martensite, hexagonal martensite and/or retained beta following quenching as a result of solid state welding.
- the welds may have higher strength than the base alloy away from the weld, and require post weld heat treatment to reduce the strength of the wel d. Aging at high temperature may be required in order to reduce the strength and toughen the weld, however, depending on the base alloy composition, the high aging temperature used to toughen the weld may result in a reduction in strength and fatigue in the base al loy material away from the weld. As noted above, the solid state weld could be toughened by a local heat treatment affecting only material in the vicinity of the weld, Howes or. there are control issues surrounding this approach, including residual stress control. Therefore, it may be more desirable to heat treat the entire w r elded component.
- Figure 6 shows the lower portion of Figure 5, centered on zones 1 and 3 and also shows the experimental alloys from Table 2 below.
- the experimental alloys may have increased hardenabiiity over Ti-64 as a result of increased beta stabilizer content, but to also have a high age temperature, allowing heat treatment of a solid state welded component to toughen the solid state weld without reducing the base alloy properties away from the weld.
- Forging methods to reduce primary alpha grain size include, but are not limited to, processing at a lower final alpha/beta forge temperature, or forging in multiple directions, see, for example, US2014/0261922, EP i 546429B i , and US2012/0060981.
- Table 2 shows that the reduction in primary alpha grain size of approximately seven-fold results in an approximate 30% increase in HCF strength. Therefore, additional processing to refine primary alpha grain size may result in a component with an enhanced balance of properties.
- FIG. 1 is a schematic illustration of an exemplary turbofan engine assembly 10 having a central rotational axis 12.
- turbofan engine assembly 10 includes an air intake side 14 and an exhaust side 16.
- Turbofan engine assembly 10 also includes a core gas turbine engine 18 that includes a high-pressure compressor 20, a combustor 22, and a high-pressure turbme 24.
- turbofan engine assembly 10 includes a low-pressure turbme 26 that is disposed axially downstream from core gas turbine engine 18, and a fan assembly 28 that is disposed axially upstream from core gas turbine engine 22.
- Fan assembly 28 includes an array of fan blades 30 extending radially outward from a rotor hub 32.
- turbofan engine assembly 10 includes a first rotor shaft 34 disposed between fan assembly 28 and the low-pressure turbine 26, and a second rotor shaft 36 disposed between high-pressure compressor 20 and high-pressure turbine 24 such that fan assembly 28, high-pressure compressor 20, high-pressure turbine 24, and low- pressure turbine 26 are in serial flow communication and co-axia!ly aligned with respect to central rotational axis 12 of turbofan engine assembly 10,
- Airflow from combustor 22 drives high-pressure turbine 24 and low- pressure turbine 26 prior to exiting turbofan engine assembly 10 through exhaust side 16.
- High-pressure compressor 20, combustor 22, high-pressure turbine 24, and low-pressure turbine 26 each include at least one rotor assembly.
- Rotary or rotor assemblies are generally subjected to different temperatures depending on their relative axial position within turbofan engine assembly 10.
- turbofan engine assembly 10 has generally cooler operating temperatures towards forward, fan assembly 28 and hotter operating temperatures towards aft high -pressure compressor 20.
- rotor components within high- pressure compressor 20 are generally fabricated from materials that are capable of withstanding higher temperatures as compared to fabrication materials for rotor components of fan assembly 28.
- turbofan engine assembly 10 represents one member of the class of rotary machines
- other members include land based gas turbines, turbojeis, turboshaft engines, unducted engines, unducted fans, fixed-wing and propeller rotors, and the li ke, as well as distributed propulsors such as distributed fans or pods, and the like.
- exemplary rotary machine parts include, for example, a disk, blisk, airfoil, blade, vane, integral bladed rotor, frame, fairing, seal, gearbox, case, mount, shaft, and the like.
- a component having an article such as the airfoil 60 of Figure 2
- Example articles may have a thick section, be cast and wrought, or be a structural aerospace casting, or the like.
- Table 3 compares exemplary titanium alloys, both comparison alloys and inventive alloys, with Ti-64:
- Tables 4, 5, and 6 show room temperature, 300 °F, and 600 °F tensile properties as a function of cooling rate from solution heat treatment for some of the alloys listed in Table 3.
- Alloys G (Ti-64 plus Fe, Mo and Si) and J (Ti-64 plus Fe, Mo, Si and Cu) tested at room temperature have slightly lower plastic elongations, but ultimate and 0.2% yield strengths on the order of 25-30 ksi higher.
- Table 7 shows the effect of alloying on tensile modulus properties for in increased room temperature through 600F modulus.
- C Fe and Mo are added in conjunction with Si, there is a smaller increase in tensile modulus at room temperature and 600F.
- C Fe, Mo and Cu are added to the Ti-64 base, there is a small increase in room temperature and 600F tensile modulus.
- Increased modulus results in a potential reduction in airfoil stresses in the case of blisk applications, potentially enabling thinner airfoils to be designed having lower weight and improved performance.
- Table 8 10 A 7 Runout High Cycle Fatigue Stresses for Selected Experimental Alloys from Table 3
- FOD foreign object damage
- Baseline Ti-64 (Alloy A) showed no plugging at approximately 800 ft/s and below. At approximately 1000 ft/s, plugging occurred, but no radial cracks were
- compositions described herein specifically discloses and includes the embodiments wherein the compositions "consist essentially of the named components (i.e., contain the named components and no other components that significantly adversely affect the basic and novel features disclosed), and embodiments wherein the compositions "consist of the named components (i.e., contain only the named components except for contaminants which are naturally and inevitably present in each of the named components).
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EP3453484A1 (en) * | 2017-09-12 | 2019-03-13 | United Technologies Corporation | Process of making integrally bladed rotor |
US10792771B2 (en) | 2017-09-12 | 2020-10-06 | Raytheon Technologies Corporation | Method of making integrally bladed rotor |
CN113604703A (en) * | 2021-07-09 | 2021-11-05 | 宝鸡安钛泽科技金属有限公司 | Manufacturing method of near-alpha type titanium alloy for golf |
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JP2017522449A (en) | 2017-08-10 |
CA2947981C (en) | 2021-10-26 |
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JP7171668B2 (en) | 2022-11-15 |
US20230392247A1 (en) | 2023-12-07 |
JP6772069B2 (en) | 2020-10-21 |
CA2947981A1 (en) | 2016-02-18 |
BR112016024906A2 (en) | 2017-08-15 |
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EP3143171A2 (en) | 2017-03-22 |
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