CN111020290A - Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof - Google Patents
Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof Download PDFInfo
- Publication number
- CN111020290A CN111020290A CN201911328471.4A CN201911328471A CN111020290A CN 111020290 A CN111020290 A CN 111020290A CN 201911328471 A CN201911328471 A CN 201911328471A CN 111020290 A CN111020290 A CN 111020290A
- Authority
- CN
- China
- Prior art keywords
- alloy
- casting
- cast
- titanium alloy
- alloy material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D1/00—Straightening, restoring form or removing local distortions of sheet metal or specific articles made therefrom; Stretching sheet metal combined with rolling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention relates to a casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and a preparation method thereof, wherein the alloy component of the material is Ti-Al-Zr-Nb-Mo-Si, and the specific chemical components comprise the following components in percentage by mass: al: 5.0% -7.5%, Zr: 3.0% -5.5%, Nb: 0.5% -3.0%, Mo: 0.2% -2.0%, Si: 0.1 to 0.6 percent of the total weight of the alloy, less than or equal to 0.15 percent of O, and the balance of Ti and inevitable impurity elements; during preparation, the raw materials are selected from ultra-0A small-particle sponge titanium, and alloy elements Nb, Mo and Si are added in a form of intermediate alloy; zr is added in the form of sponge zirconium; the Al part is brought in by the intermediate alloy, and the insufficient part is added by pure aluminum; preparing and mixing the intermediate alloy and the sponge titanium, and pressing into an electrode; after electrode welding, smelting to prepare alloy cast ingots, then casting to prepare alloy castings, and after hot isostatic pressing treatment, removing internal shrinkage cavities to prepare finished products. The invention has good room temperature and 650-750 ℃ high-temperature mechanical properties, the 650-750 ℃ high-temperature creep property and the durability can also meet the design requirements, and the invention has good casting and welding properties and meets the use requirements of the key structural members of the aerospace engine.
Description
Technical Field
The invention belongs to the technical field of titanium alloy materials, and relates to a titanium alloy casting material suitable for high temperature of 650-.
Background
With the continuous development of aerospace technology, hypersonic aircrafts become the mainstream direction for strengthening the military competitiveness of countries in the world. The aeroengine is used as a core component of the hypersonic aircraft, and the service material is required to have good matching of room-temperature and high-temperature mechanical properties, high-temperature lasting creep property, thermal stability, fatigue property, fracture toughness and the like. And the performance improvement of the engine depends greatly on the improvement of the high-temperature performance of the used materials. Under the background, various high-temperature titanium alloy materials suitable for 600 ℃ are developed in countries all over the world, typical alloys are BT18Y and BT36 in Russia, Ti6242S and Ti1100 in America and IMI834 in British, and the alloys mainly comprise Ti60 and Ti55 in China. But still can not meet the requirement that the aerospace engine urgently needs the 650-750 ℃ high-temperature titanium alloy.
At present, a typical representative of titanium alloys for 700 ℃ is Ti3Al-based intermetallic compounds are characterized by high specific strength, high specific modulus and resistance to combustion, but low room temperature plasticity and fracture toughness. The thermal stability of the titanium alloy between 600 ℃ and 700 ℃ is mainly related to brittle phase Ti3X (X = Al, Ge, In, Sn, etc.), and generally Ti, which is likely to cause a brittle phase, is used by optimizing the alloy content to increase the alloy use temperature3X precipitates, thereby reducing the thermal stability of the alloy. Therefore, the kind and content of the alloying elements should be controlled to avoid the deterioration of thermal stability.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a novel high-temperature titanium alloy material with the use temperature of 650-750 ℃; the material has good room temperature and 650-750 ℃ high-temperature mechanical properties, the 650-750 ℃ high-temperature creep property and the durability can meet the design requirements, and meanwhile, the material has good casting and welding properties, so that the use requirements of the key structural members of the aerospace engine are met.
In order to achieve the purpose, the invention adopts the technical scheme that: a titanium alloy material suitable for 650-plus-750 ℃ high temperature casting comprises the following alloy components in percentage by mass: al: 5.0% -7.5%, Zr: 3.0% -5.5%, Nb: 0.5% -3.0%, Mo: 0.2% -2.0%, Si: 0.1 to 0.6 percent of the total weight of the alloy, less than or equal to 0.15 percent of O, and the balance of Ti and inevitable impurity elements.
Wherein the contents of Mo element and Si element in the alloy are relative: when the Mo content is 1.0-2.0%, the Si content is 0.1-0.25%; when the Mo content is 0.2-1.0%, the Si content is 0.25-0.5%.
A preparation method of a casting titanium alloy material is used for preparing the casting titanium alloy material suitable for the high temperature of 650-750 ℃, the raw material adopts super 0A-0A small-particle sponge titanium, and alloy elements Nb, Mo and Si are added in a form of intermediate alloy; zr is added in the form of sponge zirconium; the Al part is brought in by the intermediate alloy, and the insufficient part is added by pure aluminum beans or aluminum foil; the intermediate alloy and the sponge titanium are mixed and pressed into an electrode by a press machine; welding the electrodes together, and smelting to prepare an alloy ingot; and casting the alloy cast ingot into an alloy casting, and performing hot isostatic pressing treatment to remove internal shrinkage cavities to obtain a finished cast titanium alloy material.
And smelting the assembled and welded electrodes in a vacuum consumable arc furnace or a vacuum induction furnace for 2-3 times to prepare alloy ingots.
And carrying out vacuum pouring on the alloy cast ingot through a vacuum consumable arc casting furnace or a vacuum induction casting furnace to obtain an alloy casting.
The hot isostatic pressing treatment method of the alloy casting comprises the following steps: heating at 920 ℃, keeping the pressure of argon at 120MPa for 2.5 hours, cooling to below 300 ℃ with the furnace, and discharging.
The cast titanium alloy material provided by the invention can meet the use requirements of high-temperature parts of an aerospace engine through the tensile strength, plasticity, durability and creep property at room temperature and 650-750 ℃ through casting and hot isostatic pressing treatment, and has good casting and welding properties.
The invention has the following effects and advantages: (1) the 650-750 ℃ high temperature performance is good, and the design and use requirements can be met; (2) the casting performance of the material is good, and the casting fluidity is slightly lower than that of the commonly used casting titanium alloy ZTC4 through tests; (3) the material has good welding performance, and the casting defect can be completely eliminated by 1-2 times of repair welding.
Detailed Description
The present invention is further illustrated by the following examples, which are not to be construed as limiting the invention in any way.
Feeding components: specific charging components of examples 1 and 2 are shown in table 1, and the table shows the mass percentages of the components.
The preparation process comprises the following steps: the raw material adopts ultra-0A-grade small-particle sponge titanium, and alloy elements Nb, Mo and Si are added in the form of AlNb, AlMo and AlSi intermediate alloys respectively; adding Zr sponge zirconium; the Al part is added by the intermediate alloy, and the insufficient part is added by pure Al; the intermediate alloy and the sponge titanium are mixed and pressed into an electrode by a press machine; smelting the electrode in a vacuum induction furnace for 2 times to prepare an alloy ingot; casting a graphite casting test bar or a test plate mold on the alloy cast ingot through a vacuum consumable electric arc furnace to finally obtain a casting test bar or a test plate; and (3) carrying out hot isostatic pressing treatment on the cast test bar or test plate (heating temperature of 920 ℃, argon pressure of 120MPa, heat preservation time of 2.5 hours, furnace cooling to below 300 ℃, discharging, and removing internal shrinkage cavity.
And (3) carrying out mechanical property test, high-temperature creep and endurance performance test, fluidity test and material repair welding performance test on the obtained test bar or test plate.
(1) The results of the mechanical property tests are shown in Table 2, and the test results show that the cast titanium alloy material prepared by the invention meets the requirements of use at high temperature of 650-.
(2) In the cast titanium alloy material prepared in example 1, after two test bars are taken as a group and subjected to high-temperature creep and endurance tests at different temperatures, the test results are shown in table 3, and the results show that the cast titanium alloy prepared by the method can meet the requirement of an aeroengine on the high-temperature endurance creep performance of the material.
(3) In the cast titanium alloy material prepared in example 2, after two test bars are taken as a group and subjected to high-temperature creep and endurance tests at different temperatures, the test results are shown in table 4, and the results show that the cast titanium alloy prepared by the method can meet the requirement of an aeroengine on the high-temperature endurance creep performance of the material.
(4) The flowability test is respectively carried out on example 1, example 2 and the conventional titanium alloy TC4, and the results are shown in Table 5, and the test shows that the flowability of the cast titanium alloy material prepared by the invention is slightly lower than that of the conventional TC4 in the field, and the cast titanium alloy material has better casting performance.
(5) Testing the repair welding performance of the material: the components of the examples 1 and 2 are respectively cast with casting test plates, and are subjected to hot isostatic pressing and flaw detection treatment to remove defects for repair welding, and the repair welding effect is as follows:
the test panel of example 1 was hot isostatically pressed and then subjected to radiographic testing for 5 defects. After 1 time of repair welding by adopting a special welding wire of ZTi700SR, the defects are completely removed.
The test panel of example 2 was hot isostatically pressed and then subjected to radiographic inspection to have 3 defects. After 1 time of repair welding by adopting the special welding wire for ZTi700SR, 1 defect is remained as a weld crack, and the defect is completely removed after 2 times of repair welding.
Therefore, the material prepared by the invention has good welding performance, and the casting defect can be completely eliminated by 1-2 times of repair welding.
Sample preparation: the components of the embodiments 1 and 2 are used for preparing the cast titanium alloy material, cylindrical samples are respectively cast, and after hot isostatic pressing sand blasting treatment, the inner surface and the outer surface of the cast castings of the materials of the embodiments 1 and 2 are good in quality, no obvious crack is visible to naked eyes, a small amount of flow marks and cold shut exist, and the casting quality of the castings is controllable.
Other embodiments of the titanium alloy material suitable for the casting at the high temperature of 650-750 ℃ are as follows:
(1) the alloy comprises the following components in percentage by mass: al: 5.0%, Zr: 3.0%, Nb: 0.5%, Mo: 1.0% -2.0%, Si: 0.1 to 0.25 percent of the total weight of the alloy, less than or equal to 0.15 percent of O, and the balance of Ti and inevitable impurity elements.
(2) The alloy comprises the following components in percentage by mass: al: 7.5%, Zr: 5.5%, Nb: 3.0%, Mo: 0.2% -1.0%, Si: 0.25 to 0.5 percent of the total weight of the alloy, less than or equal to 0.15 percent of O, and the balance of Ti and inevitable impurity elements.
The above embodiments are only intended to illustrate the technical solution of the present invention and not to limit the same, and it should be understood by those of ordinary skill in the art that the specific embodiments of the present invention can be modified or substituted with equivalents with reference to the above embodiments, and any modifications or equivalents without departing from the spirit and scope of the present invention are within the scope of the claims to be appended.
Claims (6)
1. The cast titanium alloy material suitable for 650-plus-750 ℃ high temperature is characterized in that the alloy component is Ti-Al-Zr-Nb-Mo-Si, and the specific chemical components by mass percent are as follows: al: 5.0% -7.5%, Zr: 3.0% -5.5%, Nb: 0.5% -3.0%, Mo: 0.2% -2.0%, Si: 0.1 to 0.6 percent of the total weight of the alloy, less than or equal to 0.15 percent of O, and the balance of Ti and inevitable impurity elements.
2. The cast titanium alloy material suitable for high temperatures of 650-750 ℃ according to claim 1, wherein the contents of the Mo element and the Si element in the alloy are relative: when the Mo content is 1.0-2.0%, the Si content is 0.1-0.25%; when the Mo content is 0.2-1.0%, the Si content is 0.25-0.5%.
3. A preparation method of a cast titanium alloy material is used for preparing the cast titanium alloy material suitable for the high temperature of 650-750 ℃ as claimed in claim 1, and is characterized in that the raw material is super 0A-0A small-particle sponge titanium, and the alloying elements Nb, Mo and Si are added in the form of intermediate alloy; zr is added in the form of sponge zirconium; the Al part is brought in by the intermediate alloy, and the insufficient part is added by pure aluminum beans or aluminum foil; the intermediate alloy and the sponge titanium are mixed and pressed into an electrode by a press machine; welding the electrodes together, and smelting to prepare an alloy ingot; and casting the alloy cast ingot into an alloy casting, and performing hot isostatic pressing treatment to remove internal shrinkage cavities to obtain a finished cast titanium alloy material.
4. The method for preparing a cast titanium alloy material according to claim 3, wherein the assembled electrode is melted in a vacuum consumable arc furnace or a vacuum induction furnace 2 to 3 times to prepare an alloy ingot.
5. The production method of a cast titanium alloy material according to claim 3, wherein the alloy cast ingot is vacuum-cast in a vacuum consumable arc casting furnace or a vacuum induction casting furnace to obtain an alloy casting.
6. The method of producing a cast titanium alloy material according to claim 3, wherein the hot isostatic pressing treatment of the alloy casting is: heating at 920 ℃, keeping the pressure of argon at 120MPa for 2.5 hours, cooling to below 300 ℃ with the furnace, and discharging.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911328471.4A CN111020290A (en) | 2019-12-20 | 2019-12-20 | Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911328471.4A CN111020290A (en) | 2019-12-20 | 2019-12-20 | Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111020290A true CN111020290A (en) | 2020-04-17 |
Family
ID=70212289
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911328471.4A Pending CN111020290A (en) | 2019-12-20 | 2019-12-20 | Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111020290A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113025844A (en) * | 2021-03-01 | 2021-06-25 | 攀枝花学院 | High-temperature titanium alloy and preparation method thereof |
| CN114774819A (en) * | 2022-04-11 | 2022-07-22 | 中国科学院金属研究所 | Heat treatment process of TC4 alloy casting |
| CN114790533A (en) * | 2022-04-09 | 2022-07-26 | 中国科学院金属研究所 | Heat treatment process of TC11 titanium alloy casting |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0851036A1 (en) * | 1996-12-27 | 1998-07-01 | Daido Steel Company Limited | Titanium alloy and method of producing parts therefrom |
| CN102251145A (en) * | 2011-07-04 | 2011-11-23 | 西安西工大超晶科技发展有限责任公司 | 1100 MPa level thermal strength titanium alloy and preparation method thereof |
| CN104532056A (en) * | 2014-12-08 | 2015-04-22 | 洛阳双瑞精铸钛业有限公司 | High temperature titanium alloy and preparation method thereof |
| WO2015168131A1 (en) * | 2014-04-28 | 2015-11-05 | Rti International Metals, Inc. | Titanium alloy, parts made thereof and method of use |
| CN106555076A (en) * | 2017-01-09 | 2017-04-05 | 北京工业大学 | A kind of resistance to 650 DEG C of high-temperature titanium alloy materials and preparation method thereof |
| CN106994471A (en) * | 2017-03-02 | 2017-08-01 | 中国船舶重工集团公司第七二五研究所 | A kind of 780MPa intensity levels electron beam fuse 3D printing component titanium alloy wire materials |
-
2019
- 2019-12-20 CN CN201911328471.4A patent/CN111020290A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0851036A1 (en) * | 1996-12-27 | 1998-07-01 | Daido Steel Company Limited | Titanium alloy and method of producing parts therefrom |
| CN102251145A (en) * | 2011-07-04 | 2011-11-23 | 西安西工大超晶科技发展有限责任公司 | 1100 MPa level thermal strength titanium alloy and preparation method thereof |
| WO2015168131A1 (en) * | 2014-04-28 | 2015-11-05 | Rti International Metals, Inc. | Titanium alloy, parts made thereof and method of use |
| CN104532056A (en) * | 2014-12-08 | 2015-04-22 | 洛阳双瑞精铸钛业有限公司 | High temperature titanium alloy and preparation method thereof |
| CN106555076A (en) * | 2017-01-09 | 2017-04-05 | 北京工业大学 | A kind of resistance to 650 DEG C of high-temperature titanium alloy materials and preparation method thereof |
| CN106994471A (en) * | 2017-03-02 | 2017-08-01 | 中国船舶重工集团公司第七二五研究所 | A kind of 780MPa intensity levels electron beam fuse 3D printing component titanium alloy wire materials |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113025844A (en) * | 2021-03-01 | 2021-06-25 | 攀枝花学院 | High-temperature titanium alloy and preparation method thereof |
| CN114790533A (en) * | 2022-04-09 | 2022-07-26 | 中国科学院金属研究所 | Heat treatment process of TC11 titanium alloy casting |
| CN114774819A (en) * | 2022-04-11 | 2022-07-22 | 中国科学院金属研究所 | Heat treatment process of TC4 alloy casting |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111187946B (en) | Nickel-based wrought superalloy with high aluminum content and preparation method thereof | |
| CN111235434B (en) | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature | |
| CN103602872B (en) | A kind of TiZrNbVMo xhigh-entropy alloy and preparation method thereof | |
| CN111020290A (en) | Casting titanium alloy material suitable for 650-plus-750 ℃ high temperature and preparation method thereof | |
| CN106555076A (en) | A kind of resistance to 650 DEG C of high-temperature titanium alloy materials and preparation method thereof | |
| CN110512116A (en) | A kind of high Nb-TiAl intermetallic compound of multicomponent high-alloying | |
| CN102994835B (en) | Heatproof magnesium alloy | |
| CN109371268A (en) | A kind of preparation method of high temperature, high thermal stability, high creep resistance titanium alloy rod bar | |
| CN111218586A (en) | Scandium-titanium-zirconium-element-containing aluminum alloy for 3D printing | |
| CN113564443B (en) | High-strength high-plasticity cast high-entropy alloy and preparation method thereof | |
| JP7450639B2 (en) | Low stacking fault energy superalloys, structural members and their uses | |
| CN109536775B (en) | A kind of high-temperature titanium alloy and preparation method thereof | |
| EP0855449B1 (en) | Columnar crystalline Ni-base heat-resistant alloy having high resistance to intergranular corrosion at high temperature, method of producing the alloy, large-size article, and method of producing large-size article from the alloy | |
| JP5558050B2 (en) | Nickel-base superalloy for unidirectional solidification with excellent strength and oxidation resistance | |
| CN109536776B (en) | Heat-resistant titanium alloy and preparation method thereof | |
| CN108866378B (en) | High-strength high-conductivity copper alloy for high-temperature environment and preparation method thereof | |
| WO2016177095A1 (en) | Aluminium alloy material and preparation method therefor | |
| CN108531773A (en) | A kind of Ti3Al intermetallic compound high-temperature structural materials | |
| CN117265360A (en) | Composite precipitation strengthening type high-entropy alloy and preparation method thereof | |
| CN110846536A (en) | 550 ℃ casting titanium alloy material and preparation method thereof | |
| CN108165780B (en) | Preparation method of Ni-Cr-Al-Fe high-temperature alloy | |
| CN113073233B (en) | 650-DEG C-resistant micro-nano yttrium oxide-added high-temperature titanium alloy plate and preparation method thereof | |
| CN109136672A (en) | A kind of corrosion-resistant high strength alumin ium alloy and preparation method | |
| CN111254317B (en) | Nickel-based casting alloy and preparation method thereof | |
| CN101824570A (en) | AZ series magnesium-beryllium rare earth alloy material and method for preparing same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200417 |