CN104028692B - The forging method of engine pairing gold wheel disc - Google Patents
The forging method of engine pairing gold wheel disc Download PDFInfo
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- CN104028692B CN104028692B CN201410257553.5A CN201410257553A CN104028692B CN 104028692 B CN104028692 B CN 104028692B CN 201410257553 A CN201410257553 A CN 201410257553A CN 104028692 B CN104028692 B CN 104028692B
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Abstract
The invention discloses the forging method of a kind of engine pairing gold wheel disc, for solving the low technical problem of the shaping turbine engine disk hot strength of available engine wheel disc forging method.Technical scheme first selectes the two kinds of alloys meeting two alloy disc working environments, then dish is welded into, according to recrystallization initial temperature and the malleability of selected two kinds of alloys, when selecting to have the recrystallization initial temperature of high recrystallization initial temperature material or conventional forging, distortion is more than or equal to the final forging temperature of 20% indehiscent minimum temperature as the different alloys blank of welding, and the pairing of welding gold wheel disc is carried out isothermal forging according to the smithing technological parameter determined on isothermal forging equipment.The method can make different alloys joint made by flame welding solidified structure change over Deformation structure, namely thick column crystal be changed to after distortion tiny equiax crystal or strip phase with etc. the line and staff control of axle phase composition, and weld blowhole is closed in forging, improves the hot strength of turbine engine disk welding point.
Description
Technical field
The present invention relates to a kind of forging method of turbine engine disk, particularly relate to the forging method of a kind of engine pairing gold wheel disc.
Background technology
The compressor disc of engine subjects the acting in conjunction of the thermal stress caused by mechanical stress and the temperature difference under arms in process.Dish like members centre is stressed different with heating status, thus also different to the performance requirement at each position with dish position, edge.Divide in dish edge, due to the flow at high speed friction with air-flow, the temperature of dish suffered by edge is higher, but dish edge bears less centrifugal stress; Thus coil position, edge and must have the performances such as good resistance to high temperature oxidation, high temperature creep-resisting and fatigue crack expansion.Comparatively speaking, the temperature of the operating core of dish is relatively low, but subjects larger centrifugal stress; Therefore, the centre of diskware must have high yield strength, maximum tensile strength and good low cycle fatigue property.In order to adapt to the working environment of the large thermograde of turbine engine disk and stress gradient, make the different two tissue dishes of crystal particle scale primarily of single alloy at present, or make two alloy disc with different-alloy and make wheel rim and spoke bear different temperature load and different stress loads.
It is a kind of approach that intermetallic compound and conventional titanium alloy welding make two alloy disc.Such as, document 1 " HongtaoZhang; PengHe; JicaiFeng; HuiqiangWu.Interfacialmicrostructureandstrengthofthediss imilarjointTi3Al/TC4weldedbytheelectronbeamprocess [J] .MaterialsScienceandEngineeringA; 2006,425:255-259 " have studied the tissue of linkage interface and the tensile property of weldment after the electron beam welding of Ti3Al and TC4 titanium alloy vacuum.Point out to weld in rear weld seam the column crystal and equiax crystal that are mainly and solidify in document, the tensile property impact of size on weldment of crystal grain is comparatively large, and ultimate tensile strength reaches 831MPa.Can find out that the weld structure of the weldment of directly welding is thicker, tensile property is lower.
Summary of the invention
In order to overcome the low deficiency of the shaping turbine engine disk hot strength of available engine wheel disc forging method, the invention provides the forging method of a kind of engine pairing gold wheel disc.The method selectes that chemical composition is compatible, elastic modelling quantity is compatible and linear expansion coefficient is compatible, hold two kinds of alloys that warm bearing capacity meets two alloy disc working environment, then dish is welded into, according to recrystallization initial temperature and the malleability of selected two kinds of alloys, when selecting to have the recrystallization initial temperature of high recrystallization initial temperature material or conventional forging, distortion is more than or equal to the final forging temperature of 20% indehiscent minimum temperature as the different alloys blank of welding, and the pairing of welding gold wheel disc is carried out isothermal forging according to the smithing technological parameter determined on isothermal forging equipment.The method can make different alloys joint made by flame welding solidified structure change over Deformation structure, and namely thick column crystal is changed to tiny equiax crystal or strip phase and the line and staff control waiting axle phase composition after distortion, and forging conjunction weld blowhole; The room temperature of welding point and high-temperature behavior are brought up to be equal to or greater than select more low-alloyed intensity, plasticity in two kinds of alloys.
The technical solution adopted for the present invention to solve the technical problems is: a kind of forging method of engine pairing gold wheel disc, is characterized in adopting following steps:
Step one, selected chemical composition is compatible, elastic modelling quantity is compatible and linear expansion coefficient is compatible, holds two kinds of alloys that warm bearing capacity meets two alloy disc working environment.
Step 2, front heat treatment is welded to two kinds of selected alloys, be then machined into annular element and dish that turbine engine disk needs, annular element and dish are welded into engine pairing gold wheel disc by vacuum electron beam welding machine.
Step 3, to two kinds of selected alloys in strain rate 10
-2/ s, 10
-3/ s or 10
-4under/s condition, carry out the superplastic tension experiment of different temperatures, and determine the percentage elongation obtained when alloy stretches under differently strained speed and temperature combination condition, determine that alloy has superplastic strain rate and temperature range.
The recrystallization initial temperature of two kinds of alloys that step 4, basis are selected and malleability, select to be out of shape when having the recrystallization initial temperature of high recrystallization initial temperature alloy or conventional forging to be more than or equal to the final forging temperature of 20% indehiscent minimum temperature as two kinds of alloy blanks of welding.Again according to the transition temperature that there is phase of these two kinds of alloys, by the phase transition temperature of material with lower phase transition temperature, choose lower than the initial forging temperature of this temperature 20 ~ 30 DEG C as two kinds of alloy blanks of welding.The temperature range that integrating step three is determined, comprehensively determines temperature and the strain rate scope of pairing gold wheel disc isothermal or near isothermal forging.
Step 5, by the pairing welded gold wheel disc on isothermal forging equipment, carry out isothermal or near isothermal forging according to the smithing technological parameter determined.
The invention has the beneficial effects as follows: compatible by selected chemical composition, elastic modelling quantity is compatible and linear expansion coefficient is compatible, hold two kinds of alloys that warm bearing capacity meets two alloy disc working environment, then dish is welded into, according to recrystallization initial temperature and the malleability of selected two kinds of alloys, when selecting to have the recrystallization initial temperature of high recrystallization initial temperature material or conventional forging, distortion is more than or equal to the final forging temperature of 20% indehiscent minimum temperature as the different alloys blank of welding, the pairing of welding gold wheel disc is carried out isothermal forging according to the smithing technological parameter determined on isothermal forging equipment.The method can make different alloys joint made by flame welding solidified structure change over Deformation structure, and namely thick column crystal is changed to tiny equiax crystal or strip phase and the line and staff control waiting axle phase composition after distortion, and forging conjunction weld blowhole; The room temperature of welding point and high-temperature behavior are brought up to be equal to or greater than select more low-alloyed intensity, plasticity in two kinds of alloys.After tested, the hot strength of the turbine engine disk welding point of the inventive method forging improves more than 18% compared with background technology.
Below in conjunction with the drawings and specific embodiments, the present invention is elaborated.
Accompanying drawing explanation
Fig. 1 is the inventive method embodiment Ti-24Al-15Nb-1.5Mo/TC11 pairing gold solder Jie Hou connector area columanar structure photo;
Fig. 2 is after the inventive method embodiment Ti-24Al-15Nb-1.5Mo/TC11 two kinds of alloy welding, at 960 DEG C with 10
-3s
-1deng the microstructure picture of connector area after warm deformation 40%.
Detailed description of the invention
Following examples are with reference to Fig. 1-2.
The present embodiment is the forging method of engine Ti-24Al-15Nb-1.5Mo/TC11 pairing gold wheel disc, be characterized in comprising welding material select, be welded into dish, forging before preparatory technology, the determination of smithing technological parameter, isothermal (or nearly isothermal) forge and structure observation and Mechanics Performance Testing, concrete steps are as follows:
Step 1, welding material is selected: Ti-24Al-15Nb-1.5Mo alloy and TC11 titanium alloy, and Ti-24Al-15Nb-1.5Mo alloy is as dish edge material, and TC11 titanium alloy is as dish core material.
Step 2, is welded into dish: weld front annealing to Ti-24Al-15Nb-1.5Mo alloy and TC11 alloy, homogenising tissue; Then machining, Ti-24Al-15Nb-1.5Mo alloy is processed into annular, and TC11 alloy is processed into dish type.Diskware is become by vacuum electron beam welding.
Step 3, preparatory technology: α before forging
2phase average yardstick is that the Ti-24Al-15Nb-1.5Mo alloy of 6 μm is with lower than 10
-2s
-1during strain rate distortion, at 940 ~ 1020 DEG C, there is superplasticity, and with lower than 10
-3s
-1during strain rate distortion, too there is superplasticity at 900 DEG C, but the superplasticity condition of the best is: T=980 DEG C,
the TC11 titanium alloy that α phase average yardstick is less than 10 μm, with lower than 10
-2s
-1during strain rate distortion, in 800 ~ 970 DEG C of temperature ranges, all present superplasticity, best superplasticity condition is: T=950 DEG C,
Step 4, the determination of smithing technological parameter: Ti-24Al-15Nb-1.5Mo is a kind of intermetallic alloy, and its conventional forging range is 1070 ~ >900 DEG C; The conventional forging range of TC11 alloy is 960 DEG C ~ >800 DEG C, and the forging range that this bi-material crosses is 960 ~ > 900 DEG C.The superplasticity test temperature scope that integrating step 3 obtains, determine that isothermal (or the nearly isothermal) forging range of Ti-24Al-15Nb-1.5Mo/TC11 pairing gold welded disc should be selected in 900 ~ 970 DEG C, strain rate answers≤10
-3s
-1.
Step 5, isothermal (or near isothermal) forging: (forging temperature is 960 DEG C, strain rate is 10 for the smithing technological parameter determined according to step 4 on isothermal forging equipment by two for the Ti-24Al-15Nb-1.5Mo/TC11 of welding gold dish
-3s
-1, deformation extent is 40%) carry out isothermal forging.
Step 6, structure observation and Mechanics Performance Testing: can see from Fig. 1, Fig. 2, as-welded Ti-24Al-15Nb-1.5Mo/TC11 pairing gold connector area microscopic structure is column crystal; And with 10
-3s
-1strain rate after 960 DEG C of isothermal forgings in connector area microscopic structure crystal boundary be broken, have more secondary phase to separate out simultaneously.Diskware after forging is heat-treated and tested mechanical property, its heat treating regime is (gradient heat treatment): 980 DEG C, 1h (Ti-24Al-15Nb-1.5Mo side)/950 DEG C, 1h (TC11 side), AC → 815 DEG C, 1h (Ti-24Al-15Nb-1.5Mo side)/<450 DEG C, 1h (TC11 side), AC → 700 DEG C, 7h (Ti-24Al-15Nb-1.5Mo side)/530 DEG C, 7h (TC11 side), AC.As-welded Ti-24Al-15Nb-1.5Mo/TC11 pairing gold joint mechanical properties and plasticity are σ
bfor 957.5MPa, σ
0.2for 760MPa, δ be 9.5%, Ψ is 18.75%.And by above-mentioned technological parameter through isothermal forging and gradient heat treated Ti-24Al-15Nb-1.5Mo/TC11 pairing gold joint mechanical properties and plasticity be σ
bfor 1130MPa, σ
0.2for 1080MPa, δ be 11.5%, Ψ is 33%, intensity improves 18%, and percentage elongation and the reduction of area at fracture are all improved.
Claims (1)
1. a forging method for engine pairing gold wheel disc, is characterized in that comprising the following steps:
Step one, selected chemical composition is compatible, elastic modelling quantity is compatible and linear expansion coefficient is compatible, holds two kinds of alloys that warm bearing capacity meets pairing gold wheel disc working environment;
Step 2, front heat treatment is welded to two kinds of selected alloys, be then machined into annular element and dish that pairing gold wheel disc needs, annular element and dish are welded into pairing gold wheel disc by vacuum electron beam welding machine;
Step 3, to two kinds of selected alloys in strain rate 10
-2/ s, 10
-3/ s or 10
-4under/s condition, carry out the superplastic tension experiment of different temperatures, and determine the percentage elongation obtained when alloy stretches under differently strained speed and temperature combination condition, determine that alloy has superplastic strain rate and temperature range;
The recrystallization initial temperature of two kinds of alloys that step 4, basis are selected and malleability, select to be out of shape when having the recrystallization initial temperature of high recrystallization initial temperature alloy or conventional forging to be more than or equal to the final forging temperature of 20% indehiscent minimum temperature as two kinds of alloy blanks of welding; Again according to the transition temperature that there is phase of these two kinds of alloys, by the phase transition temperature of material with lower phase transition temperature, choose lower than the initial forging temperature of this phase transition temperature temperature 20 ~ 30 DEG C as two kinds of alloy blanks of welding; The temperature range that integrating step three is determined, comprehensively determines temperature and the strain rate scope of pairing gold wheel disc isothermal or near isothermal forging;
Step 5, by the pairing welded gold wheel disc on isothermal forging equipment, carry out isothermal or near isothermal forging according to the smithing technological parameter determined;
In described two kinds of alloys, Ti-24Al-15Nb-1.5Mo alloy is as annular element material, and TC11 titanium alloy is as dish material.
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|---|---|---|---|
| CN201410257553.5A CN104028692B (en) | 2014-06-11 | 2014-06-11 | The forging method of engine pairing gold wheel disc |
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|---|---|---|---|
| CN201410257553.5A CN104028692B (en) | 2014-06-11 | 2014-06-11 | The forging method of engine pairing gold wheel disc |
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| CN104028692B true CN104028692B (en) | 2016-01-13 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101412066A (en) * | 2007-10-17 | 2009-04-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Hammer forging technique of GH4169 alloy dish |
| CN101480689A (en) * | 2008-12-25 | 2009-07-15 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of two-phase titanium alloy disk-type forgeable piece |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
| EP2533515A2 (en) * | 2011-06-06 | 2012-12-12 | Sony Corporation | Noise reduction controlling apparatus and method |
| EP2592170A1 (en) * | 2010-06-11 | 2013-05-15 | Showa Denko K.K. | Method for producing al alloy joined body |
-
2014
- 2014-06-11 CN CN201410257553.5A patent/CN104028692B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101412066A (en) * | 2007-10-17 | 2009-04-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Hammer forging technique of GH4169 alloy dish |
| CN101480689A (en) * | 2008-12-25 | 2009-07-15 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of two-phase titanium alloy disk-type forgeable piece |
| EP2592170A1 (en) * | 2010-06-11 | 2013-05-15 | Showa Denko K.K. | Method for producing al alloy joined body |
| EP2533515A2 (en) * | 2011-06-06 | 2012-12-12 | Sony Corporation | Noise reduction controlling apparatus and method |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
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| CN104028692A (en) | 2014-09-10 |
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