CN116079345A - Method for preparing bar material containing titanium alloy mixed with by combining interface roughness control and hot isostatic pressing technology and bar material - Google Patents

Method for preparing bar material containing titanium alloy mixed with by combining interface roughness control and hot isostatic pressing technology and bar material Download PDF

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Publication number
CN116079345A
CN116079345A CN202310060941.3A CN202310060941A CN116079345A CN 116079345 A CN116079345 A CN 116079345A CN 202310060941 A CN202310060941 A CN 202310060941A CN 116079345 A CN116079345 A CN 116079345A
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titanium alloy
isostatic pressing
hot isostatic
bar
inclusion
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CN202310060941.3A
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Chinese (zh)
Inventor
蔡雨升
张洺川
吉海宾
任德春
雷家峰
杨锐
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Institute of Metal Research of CAS
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Institute of Metal Research of CAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K15/00—Electron-beam welding or cutting
    • B23K15/0046—Welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Forging (AREA)

Abstract

The invention belongs to the technical field of titanium alloy manufacturing, and discloses a method for preparing a bar material containing titanium alloy mixed with impurities by combining interface roughness control and hot isostatic pressing technology and the bar material. The method comprises the following steps: cutting the titanium alloy bar into two sections along the length direction, and ensuring that the surface roughness of the two sections of bars is less than 0.1 mu m; punching holes at preset positions of the end surfaces of the two sections of bars, ensuring that inclusions are completely implanted into the holes, and sealing and welding corresponding cutting surfaces of the two sections of bars by adopting electron beam welding; and carrying out hot isostatic pressing treatment and machining on the bar subjected to the seal welding treatment to obtain the bar containing the titanium alloy inclusion. The bar with the defects prepared by the method can be applied to systematic research on the change rules of the form and the size of the hard alpha inclusions in the forging process, and provides important technical support for the airworthiness evidence collection of the engine.

Description

Method for preparing bar material containing titanium alloy mixed with by combining interface roughness control and hot isostatic pressing technology and bar material
Technical Field
The invention belongs to the technical field of titanium alloy manufacturing, and particularly relates to a method for preparing a bar material containing titanium alloy mixed with impurities by combining interface roughness control and hot isostatic pressing technology and the bar material.
Background
With the continuous development and increasing perfection of scientific and technical and management systems, modern aeroengines are developed towards high performance, high reliability and safety. Safety is the core of civil aircraft engines and is also a necessary condition for gaining market admission. Although the design method of 'safe life' can improve the low cycle fatigue life of the component and reduce the failure accident of the aeroengine, nevertheless, the non-inclusive accident still happens occasionally, and many flying accidents have direct relation with the metallurgical quality of the titanium alloy component, mainly caused by the defects introduced into the titanium alloy during smelting, processing and the like, wherein more accidents are caused by the defects of hard alpha inclusions in the titanium alloy, and obviously the defects of the hard alpha inclusions in the titanium alloy have become one of the main factors of the material failure of the titanium alloy component.
Since the end of the 20 th century, foreign researchers have systematically developed theories and methods for probabilistic risk assessment, gradually develop and perfect corresponding risk assessment analysis tools, and the analysis method has gained acceptance of FAA at present and is applied to the airworthiness certification work of novel aeroengines.
The bottleneck problem of airworthiness authentication of the aviation engine technology in China needs to be solved urgently. To develop the defect detection probability and probability risk evaluation research, firstly, the internal inclusion size of the titanium alloy bar and the morphological evolution rule of inclusions in the forging process are obtained. However, at present, no related report is provided for developing a bar material containing hard alpha-inclusion titanium alloy, so that the probability of detecting defects in the titanium alloy and the risk assessment thereof cannot be carried out, and the bar material becomes one of key factors affecting the airworthiness certification of an aeroengine. The most recent report is from CN110295291a, which includes the following steps: (1) Smelting twice by adopting a conventional vacuum consumable smelting technology to obtain a titanium alloy cast ingot; (2) Forging the twice-smelted cast ingot to prepare a bar with a certain specification; (3) Sawing the bar along the middle part, and polishing and grinding the sawing surface; (4) Drilling holes at the cutting surface, and placing the hard alpha inclusions in the holes; (5) And (6) carrying out primary vacuum consumable smelting on the alloyed titanium alloy bar, and forging the obtained cast ingot to prepare the titanium alloy bar containing the hard inclusions.
However, through relevant experiments, the CN110295291A method has obvious preparation defects: (1) Because the preparation is carried out by adopting a smelting method, the position of the defects in the prepared bar is random and uncontrollable due to the flow and boiling of a molten pool in the smelting process, and the subsequent processing can not be carried out so as to carry out research work; (2) After the cast ingot is forged, the internal defect morphology is changed and even broken, so that obvious dispersibility appears in the subsequent experimental result, and the research work of airworthiness certification cannot be supported; (3) Because the two sections of bars are subjected to local seal welding by adopting an argon arc welding technology, the welding parts of the bars are easy to be melted during smelting, so that the bars are broken, and safety accidents are caused; (4) Because the smelting process is faster, the inclusions are not fully diffused with the matrix material to form good metallurgical bonding, so that larger errors are introduced for subsequent experiments.
In summary, the method described in CN110295291a cannot produce inclusion bars for airworthiness certification. Aiming at the problems and the urgent need of airworthiness certification at the present stage, a method for preparing a titanium alloy bar containing TiN inclusion by adopting a mode of combining interface roughness control and hot isostatic pressing technology is provided.
Disclosure of Invention
The invention aims at overcoming the defects of the prior art, and provides a method for preparing a bar material containing titanium alloy mixed with the combination of interface roughness control and hot isostatic pressing technology and the bar material. The bar with the defects prepared by the method can be applied to systematic research on the change rules of the form and the size of the hard alpha inclusions in the forging process, and provides important technical support for the airworthiness evidence collection of the engine.
In order to achieve the above object, in one aspect, the present invention provides a method for preparing a titanium alloy bar with inclusions in combination with an interface roughness control and a hot isostatic pressing technique, the method comprising the steps of:
s1: cutting the titanium alloy bar into two sections along the length direction, and ensuring that the surface roughness of the two sections of bars is less than 0.1 mu m;
s2: punching is carried out at the preset position of the end surfaces of the two sections of bars, so that the inclusions are completely implanted into the bars, as shown in figure 1;
s3: sealing and welding the corresponding cutting surfaces of the two sections of bars by adopting electron beam welding;
s4: and carrying out hot isostatic pressing treatment and machining (removing the structure of the sealing part) on the bar subjected to the sealing treatment to obtain the bar containing the titanium alloy inclusions.
In the invention, the titanium alloy bar is cut into two sections along the length direction, and the surface roughness of the bar is optimized, so that the surface roughness of the two sections of bars is ensured to be less than 0.1 mu m, and if the surface roughness is higher than 0.1 mu m, the performance at the interface can not meet the requirement of the subsequent experiment.
According to the invention, preferably, the titanium alloy bar is a TC4 titanium alloy bar and/or a Ti60 titanium alloy bar.
According to the present invention, it is preferable that the hole size obtained by punching in step S2 is in the range of 0.5 to 5.0mm and the hole depth is in the range of 1.0 to 5.0mm.
According to the present invention, preferably, the welding depth of the seal welding treatment is less than 3% of the diameter of the bar.
According to the present invention, preferably, the inclusions are hard α inclusions.
According to the present invention, preferably, the hard alpha inclusions are TiN and/or TiO 2 。
According to the present invention, preferably, the temperature of the hot isostatic pressing treatment is a temperature of + -30 ℃ at which the hard alpha inclusions are transformed into beta-Ti.
According to the invention, the hot isostatic pressure of the hot isostatic pressing treatment is preferably 150-200Mpa.
According to the invention, the hot isostatic pressing treatment preferably has a hot isostatic pressing time of 1-2h.
The invention also provides the inclusion titanium alloy bar prepared by the method for preparing the inclusion titanium alloy bar by combining the interface roughness control and the hot isostatic pressing technology.
The technical scheme of the invention has the following beneficial effects:
(1) The method prepares the titanium alloy bar containing TiN inclusion by combining interface roughness control and hot isostatic pressing technology, lays a material foundation for researching defect morphology change rules and defect detection probability, and provides technical support for aero-engine airworthiness certification.
(2) The invention is not limited by titanium alloy materials and inclusion types, and can be applied to the preparation of various brands of titanium alloy inclusion bars related to aeroengines according to the requirements of airworthiness certification.
(3) The invention overcomes all the defects of CN110295291A, and the invention carries out hot isostatic pressing treatment and machining on the bar after the seal welding treatment, and does not have the smelting and forging processes of step (6) of CN110295291A, thereby ensuring the internal defect form of the bar, the accuracy of the subsequent experimental result and the smooth progress of relevant researches of airworthiness certification.
(4) The method can prepare the titanium alloy bar with inclusions without losing the bar strength, and the performance of the bar interface can not influence the subsequent experiment.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.
FIGS. 1 (a) - (b) are schematic illustrations of the method of preparing a titanium alloy rod with inclusions using the combination of interface roughness control and hot isostatic pressing techniques provided in example 1 of the present invention, wherein inclusions are fully implanted into the end surfaces of two sections of the rod. ( Wherein: (a) is an implantation procedure; (b) Is a machined bar material containing titanium alloy mixed with )
Fig. 2 shows a sample of a titanium alloy containing defects TC4 prepared by the method of example 1 of the present invention for preparing a bar of titanium alloy containing inclusions by combining the control of interface roughness with the hot isostatic pressing technique.
FIG. 3 shows performance test specimens and test results of WZ-16 engine specimen and component levels carried out using the titanium alloy bar containing defects obtained in example 1. (in the figure, the abscissa N represents the cycle number (cycles) of fatigue and the ordinate σmax represents the load intensity (MPa). Wherein, the number 1:No cycle, R 0 =0.5, representing the test result at a stress ratio of 0.5; sequence number 2: no inclusion, R 0 =0.1, representing the test result at a stress ratio of 0.1; serial number 3: no inclusion, R 0 -1, representing the test results when the stress ratio is-1 (the above three data are from the titanium alloy materials handbook); serial number 4: no inclusion, R 0 -1, representing the result when the actual measured stress ratio is-1; sequence number 5: burid inclusion, R 0 -1, which represents the test result of internal defects when the stress ratio is-1; serial number 6: surface inclusion R 0 -1, representing the test result of surface defects with a stress ratio of-1
FIG. 4 shows a defective TC4 titanium alloy disk for WZ-16 engine airworthiness certification life assessment prepared using the defective titanium alloy bar obtained in example 1.
The reference numerals are explained as follows:
1-titanium alloy bar; 2-inclusion.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
Example 1
The embodiment provides a method for preparing a TC4 titanium alloy bar containing TiN inclusion by combining interface roughness control and hot isostatic pressing technology, which comprises the following steps:
s1: cutting the titanium alloy bar into two sections along the length direction, and carrying out surface roughness optimization treatment on the surface of the bar to ensure that the surface roughness Ra of the two sections of bars is 0.05 mu m;
s2: punching is carried out at the preset position of the end surfaces of the two sections of bars, so that the inclusions are completely implanted into the bars, as shown in figure 1;
s3: sealing and welding the corresponding cutting surfaces of the two sections of bars by adopting electron beam welding, wherein the welding depth is 5mm (the diameter of the bar is 170 mm);
s4: and carrying out hot isostatic pressing treatment and machining (removing the structure of the sealing part) on the bar subjected to the sealing welding treatment to obtain the titanium alloy bar with inclusions, as shown in figure 2. The temperature of the hot isostatic pressing treatment is 960 ℃, the hot isostatic pressing pressure is 170Mpa, and the hot isostatic pressing time is 1h.
The tensile strength of the bar material containing the titanium alloy inclusions is 973MPa, the elongation is 16.3%, and the preparation requirement of the bar material containing the defects for airworthiness certification is met.
As shown in fig. 3, the titanium alloy bar containing defects obtained by adopting the embodiment develops performance test samples and test results of the sample level and the component level of the WZ-16 engine, and the rule of influence of the defects on the mechanical properties of the samples is clarified as follows: when the load is fixed, the fatigue life of the surface defect is about 5 ten thousand times lower than that of the internal defect by 9 ten thousand times; when the fatigue life is constant, the surface defect load is only 240MPa, and the internal defect sample load is 300MPa. FIG. 4 is a prepared WZ-16 engine airworthiness certification life evaluation of a disc of a titanium alloy containing defect TC 4.
Example 2
The present embodiment provides a method for preparing a Ti60 titanium alloy bar containing TiN inclusions by combining interface roughness control and hot isostatic pressing, and the difference between the present embodiment and embodiment 1 is that:
the surface roughness Ra of the two sections of bars is 0.037 mu m;
sealing and welding the corresponding cutting surfaces of the two sections of bars by adopting electron beam welding, wherein the welding depth is 2mm (the diameter of the bar is 80 mm);
the temperature of the hot isostatic pressing treatment is 1020 ℃, the hot isostatic pressing pressure is 150Mpa, and the hot isostatic pressing time is 2h.
The tensile strength of the bar material containing the titanium alloy is 1013MPa, the elongation is 13.5%, and the preparation requirement of the bar material containing the defects for airworthiness certification is met.
Comparative example 1
This comparative example provides a method for preparing a titanium alloy bar containing TiN inclusions TC4 by combining interface roughness control with hot isostatic pressing technology, and differs from example 1 only in that:
the surface roughness Ra of the two sections of bars is 1.6 mu m;
sealing and welding the corresponding cutting surfaces of the two sections of bars by adopting electron beam welding, wherein the welding depth is 3mm (the diameter of the bar is 100 mm);
the temperature of the hot isostatic pressing treatment is 970 ℃, the hot isostatic pressing pressure is 180Mpa, and the hot isostatic pressing time is 1.5h.
The tensile strength of the bar material containing the titanium alloy inclusions is 935MPa, the elongation is 5.7%, and the preparation requirement of the bar material containing the defects for airworthiness certification is not met.
The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.

Claims (10)

1. A method for preparing a titanium alloy bar with inclusions by combining interface roughness control and hot isostatic pressing technology, which is characterized by comprising the following steps:
s1: cutting the titanium alloy bar into two sections along the length direction, and ensuring that the surface roughness of the two sections of bars is less than 0.1 mu m;
s2: punching holes at preset positions of the end surfaces of the two sections of bars to ensure that the inclusions are completely implanted in the bars;
s3: sealing and welding the corresponding cutting surfaces of the two sections of bars by adopting electron beam welding;
s4: and carrying out hot isostatic pressing treatment and machining on the bar subjected to the seal welding treatment to obtain the bar containing the titanium alloy inclusion.
2. The method of claim 1, wherein the titanium alloy bar is a TC4 titanium alloy bar and/or a Ti60 titanium alloy bar.
3. The method for preparing an included titanium alloy bar by combining interface roughness control and hot isostatic pressing technology as claimed in claim 1, wherein the pore size range obtained by punching in the step S2 is 0.5-5.0mm, and the pore depth is 1.0-5.0mm.
4. The method of producing an inclusion titanium alloy rod in combination with hot isostatic pressing as claimed in claim 1, wherein the seal welding process has a depth of weld less than 3% of the rod diameter.
5. The method of producing an inclusion titanium alloy bar in combination with hot isostatic pressing techniques of claim 1, wherein the inclusions are hard alpha inclusions.
6. The method for producing an inclusion titanium alloy bar in combination with hot isostatic pressing technique of claim 5, wherein the hard alpha inclusions are TiN and/or TiO 2 。
7. The method for producing an inclusion titanium alloy bar in combination with hot isostatic pressing technique of claim 6, wherein the hot isostatic pressing treatment is at a temperature of ±30 ℃ at which α -Ti of the hard α inclusions is converted to β -Ti.
8. The method for producing an inclusion titanium alloy bar in combination with hot isostatic pressing technique and interface roughness control as claimed in claim 6, wherein the hot isostatic pressing pressure of the hot isostatic pressing treatment is 150-200Mpa.
9. The method for producing an inclusion titanium alloy bar in combination with hot isostatic pressing technique according to claim 6, wherein the hot isostatic pressing treatment has a hot isostatic pressing time of 1-2h.
10. An inclusion titanium alloy bar prepared by a method of preparing an inclusion titanium alloy bar according to any one of claims 1-9 in combination with hot isostatic pressing.
CN202310060941.3A 2023-01-17 2023-01-17 Method for preparing bar material containing titanium alloy mixed with by combining interface roughness control and hot isostatic pressing technology and bar material Pending CN116079345A (en)

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