CN103691952A - Preparation method of functional gradient performance coil - Google Patents
Preparation method of functional gradient performance coil Download PDFInfo
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- CN103691952A CN103691952A CN201410005281.XA CN201410005281A CN103691952A CN 103691952 A CN103691952 A CN 103691952A CN 201410005281 A CN201410005281 A CN 201410005281A CN 103691952 A CN103691952 A CN 103691952A
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Abstract
The invention provides a preparation method of a functional gradient performance coil and belongs to the technical field of rapidly freezing powder metallurgy superalloys. According to the preparation method provided by the invention, powders with different particle sizes are adopted at different parts of a turbine disk to carry out direct hot isostatic pressing formation, and a coil after heat treatment acquires gradient grain structures with different grain sizes along the radial direction and has different gradient performances along the radial direction. With the adoption of the preparation method, a hub is strong in the tensile strength and excellent in the low-cycle fatigue performance, the mechanical property between the hub and a rim is good in transition, the rim has strong durability and strong creep resistance, and the requirements of the functional gradient performance coil are satisfied.
Description
Technical field
The invention belongs to Rapid Solidification Powder metallurgy high temperature alloy technology field, a kind of preparation method of functionally gradient performance diskware is particularly provided.
Background technology
The turbine disk is the hot junction core component of aero-engine.The condition of work of modern high performance aero-engine turbine disk is very harsh, and the turbine disk meets with stresses and the superposition in temperature field; The stress that the centrifugal force producing when stress is included in High Rotation Speed and oscillating load cause; Along the turbine disk radially, stress is increased to wheel hub (core position) gradually by wheel rim (the cylindrical position of dish), forms stress gradient, and temperature is increased to wheel rim gradually by wheel hub, formation temperature gradient.Wheel rim stands higher temperature and lower stress, and wheel hub stands lower temperature and higher stress.For meeting the turbine disk requirement of mechanical property under condition under arms, must guarantee that wheel hub has high hot strength and excellent low cycle fatigue property, wheel rim has high enduring quality, creep-resistant property and Crack Extension drag.
The diskware of single alloy homogeneous tissue cannot meet the requirement of above-mentioned performance.For making turbine disk different parts there is different performances, can realize by two kinds of approach: the one, diskware different parts adopts different alloys, be bi-metal plate (US5100050, 1992.03.31, US5106012, 1992.04.21, US5143563, 1992.09.01, US5161950, 1992.11.10, US7537725B2, 2009.05.26), the 2nd, adopt a kind of alloy, diskware different parts obtains different grain structure (US4820358, 1989.04.11, US5312497, 1994.05.17, US5527402, 1996.01.18, US5527020, 1996.06.18, US6478896B1, 2002.11.12, US6660110B1, 2003.12.09).The weak point of bi-metal plate is not solve compromise heat treatment and the transition region stress problem of two kinds of alloys.Single alloy diskware different parts obtains different grain structures and comprises gradient thermal deformation and two two kinds of techniques of microscopic structure heat treatment (gradient heat treatment).Gradient thermal deformation technique is at wheel hub position, to adopt aximal deformation value to forge, and obtains fine grained texture, adopts small deformation amount to forge at wheel rim position, obtains open grain structure.The weak point of this technique is that the selection of heat treating regime is very complicated.Two microscopic structure Technologies for Heating Processing are to make whole diskware obtain uniform fine grained texture by thermal deformation, then diskware is radially set up temperature gradient field when solution treatment, different parts at diskware obtains different grain structures, at wheel hub position, adopted solution treatment (temperature is higher than γ ' phased soln temperature), γ ' dissolves mutually completely, crystal grain is grown up, wheel hub obtains fine grained texture, at wheel rim position, adopt sub-solution treatment (temperature is lower than γ ' phased soln temperature), γ ' is partly dissolved mutually, remaining γ ' hinders grain growth mutually, wheel rim keeps fine grained texture.The weak point of this technique is that controllability and the repeatability of temperature gradient field under long-time heating heat-retaining condition is lower.
For overcoming above deficiency, the invention provides a kind of design principle of functionally gradient performance diskware.The design principle of gradient performance diskware is to use respectively varigrained quick solidifying high-temp alloy powder at the wheel hub of turbine diskware, disc and wheel rim, make turbine disk different parts there is different grain structures and mechanical property, meet High Performance Aeroengine turbine disk performance requirement under harsh working condition.This gradient performance characteristic of diskware had both met the features of the turbine disk, can give full play to again the potentiality of material, be conducive to simultaneously turbine disc structure optimal design, alleviate the weight of diskware, improve the thrust-weight ratio of engine.
Summary of the invention
The preparation method who the object of the present invention is to provide a kind of functionally gradient performance diskware, can obtain the diskware with gradient grain structure; Make turbine disk different parts there is different grain structures and mechanical property.
Foundation of the present invention is after varigrained powder consolidation, can obtain the tissue of various grain sizes while there is perfect recrystallization.Core of the present invention is: the different parts of the turbine disk adopts varigrained powder, radially obtains the gradient grain structure with various grain sizes at diskware, makes diskware radially have the gradient performance of different performance.Concrete technology step is as follows:
(1) wheel hub adopts fine powder, and powder size, for being less than 50 μ m, obtains fine grain structure after high temperature insostatic pressing (HIP), and wheel hub has high hot strength and excellent low cycle fatigue property;
(2) disc (wheel hub and wheel rim transition region) adopts middle-sized powder, powder size is 50-100 μ m, after high temperature insostatic pressing (HIP), obtain the middle-sized grain structure between wheel hub and wheel rim, thereby make grain structure and mechanical property between wheel hub and wheel rim there is good transition.
(3) wheel rim adopts meal, and powder size, for being greater than 100～being less than or equal to 200 μ m, obtains coarse grain tissue after high temperature insostatic pressing (HIP), with meet high lasting, the high creep resistance of wheel rim can requirement;
(4) diskware after high temperature insostatic pressing (HIP) is heat-treated.
Turbine disk hip temperature is 1170 ℃～1200 ℃, and turbine disk heat treatment solid solubility temperature is 1130 ℃～1150 ℃;
Turbine disk hip temperature is t
γ '+ 10 ℃～t
γ '+ 40 ℃ of (t
γ 'for γ ' phase solid solubility temperature in alloy);
Turbine disk heat treatment solid solubility temperature is t
γ '-30 ℃～t
γ '-10 ℃ of (t
γ 'for γ ' phase solid solubility temperature in alloy).
Accompanying drawing explanation
Fig. 1 is metallographic structure after ingot blank A1 high temperature insostatic pressing (HIP).
Fig. 2 is metallographic structure after ingot blank B1 high temperature insostatic pressing (HIP).
Fig. 3 is metallographic structure after ingot blank C1 high temperature insostatic pressing (HIP).
The specific embodiment
The specific embodiment of the present invention is as follows:
Embodiment 1
Adopt FGH95 alloy, (mass fraction, is %) main chemical compositions: Co8.1, Cr13.1; W3.4, Mo3.4, Al3.4, Ti2.4, Nb3.4, C0.06, Ni surplus.The wheel hub of diskware, disc and wheel rim adopt respectively the granularity of powder to be respectively to be less than 50 μ m, 50-100 μ m and be greater than 100～be less than or equal to 200 μ m.The powder of above three kinds of granularities is respectively charged into carbon steel jacket and carries out simulated experiment, jacket is of a size of Φ 100 * 110mm, jacket after dress powder carries out high temperature insostatic pressing (HIP), hip temperature dissolves mutually completely higher than γ ', make alloy generation perfect recrystallization, (hip temperature is 1200 ℃ to the thin crystalline substance of the axles such as acquisition, pressure is not less than 100MPa, the heat-insulation pressure keeping time is not less than 2h), jacket after high temperature insostatic pressing (HIP) strips off the skin, (ingot blank A1 powder size is for being less than 50 μ m for the ingot blank obtaining, ingot blank B1 powder size is 50-100 μ m, ingot blank C1 powder size for being greater than 100～be less than or equal to 200 μ m) heat-treat, comprise solution treatment and two-stage timeliness, solid solution temperature dissolves mutually completely lower than γ ', crystal grain is no longer grown up, guarantee (the solution treatment: 1130 ℃ * 1.5h salt hardening of high temperature insostatic pressing (HIP) state fine grained texture, a timeliness: 870 ℃ * 1.5h, air cooling, secondary ageing: 650 ℃ * 24h, air cooling).After heat treatment, as shown in Figure 1, the average grain size of ingot blank is as shown in table 1 in the metallographic structure of ingot blank, after heat treatment the mechanical property of ingot blank respectively in Table 2, table 3, table 4, table 5, table 6 and table 7.
Embodiment 2
Adopt FGH95 alloy, (mass fraction, is %) main chemical compositions: Co8.1, Cr13.1; W3.4, Mo3.4, Al3.4, Ti2.4, Nb3.4, C0.06, Ni surplus.The wheel hub of diskware, disc and wheel rim adopt respectively the granularity of powder to be respectively to be less than 50 μ m, 50-100 μ m and be greater than 100～be less than or equal to 200 μ m.The powder of above three kinds of granularities is respectively charged into carbon steel jacket and carries out simulated experiment, jacket is of a size of Φ 100 * 110mm, jacket after dress powder carries out high temperature insostatic pressing (HIP), hip temperature dissolves mutually completely higher than γ ', make alloy generation perfect recrystallization, (hip temperature is 1170 ℃ to the thin crystalline substance of the axles such as acquisition, pressure is not less than 100MPa, the heat-insulation pressure keeping time is not less than 2h), jacket after high temperature insostatic pressing (HIP) strips off the skin, (ingot blank A2 powder size is for being less than 50 μ m for the ingot blank obtaining, ingot blank B2 powder size is 50-100 μ m, ingot blank C2 powder size for being greater than 100～be less than or equal to 200 μ m) heat-treat, comprise solution treatment and two-stage timeliness, solid solution temperature dissolves mutually completely lower than γ ', crystal grain is no longer grown up, guarantee (the solution treatment: 1150 ℃ * 1.5h salt hardening of high temperature insostatic pressing (HIP) state fine grained texture, a timeliness: 870 ℃ * 1.5h, air cooling, secondary ageing: 650 ℃ * 24h, air cooling).After heat treatment, the metallographic structure of ingot blank is with similar as shown in Figure 1, a γ ' negligible amounts just, the average grain size of ingot blank is as shown in table 1, after heat treatment the mechanical property of ingot blank respectively in Table 2, table 3, table 4, table 5, table 6 and table 7.
Table 1 average grain size
| Ingot blank numbering | A1B1 | C1 | A2 | B2 | C2 |
| Average grain size/μ m | 2035 | 50 | 20 | 35 | 50 |
Table 2 room temperature tensile
| Ingot blank numbering σ b/MPa | σ 0.2/MPa | δ/％ | Ψ/％ |
| A11620 | 1280 | 14 | 18 |
| A21620 | 1290 | 13 | 17 |
| B11595 | 1218 | 16 | 19 |
| B21590 | 1220 | 16 | 18 |
| C11510 | 1170 | 13 | 14 |
| C21515 | 1180 | 12 | 15 |
Table 3450 ℃ stretching
| Ingot blank numbering | σ b/MPa | σ 0.2/MPa | δ/％ | Ψ/％ |
| A1 | 1600 | 1270 | 13 | 15 |
| A2 | 1600 | 1265 | 13 | 15 |
| B1 | 1530 | 1210 | 12 | 14 |
| B2 | 1520 | 1215 | 12 | 15 |
| C1 | 1490 | 1160 | 12 | 13 |
| C2 | 1480 | 1170 | 12 | 14 |
Table 4650 ℃ stretching
| Ingot blank numbering | σ b/MPa | σ 0.2/MPa | δ/％ | Ψ/％ |
| A | 1560 | 1200 | 11 | 13 |
| A1 | 1565 | 1210 | 10 | 14 |
| B | 1513 | 1160 | 10 | 13 |
| B1 | 1510 | 1165 | 10 | 14 |
| C | 1476 | 1100 | 11 | 13 |
| C1 | 1480 | 1120 | 11 | 14 |
Table 5750 ℃ stretching
| Ingot blank numbering | σ b/MPa | σ 0.2/MPa | δ/％ | Ψ/％ |
| A1 | 1330 | 1170 | 9 | 11 |
| A2 | 1335 | 1180 | 11 | 12 |
| B1 | 1300 | 1150 | 7 | 10 |
| B2 | 1290 | 1145 | 6 | 11 |
| C1 | 1260 | 1080 | 6 | 9 |
| C2 | 1255 | 1085 | 7 | 10 |
Table 6 enduring quality
Table 7650 ℃/1020MPa low cycle fatigue property
| Ingot blank numbering | A1 | B1 | C1A2B2 | C2 |
| Cycle-index N f/ (cycle) | 18570 | 77505 | 524341954287522 | 65420 |
Therefore, by simulated experiment, to find out, the method for designing that a kind of functionally gradient performance diskware is provided of the present invention, can make the turbine disk have different grain structures and the object of mechanical property.
Claims (3)
1. a preparation method for functionally gradient performance diskware, is characterized in that, processing step is as follows:
(1) wheel hub adopts fine powder, and powder size, for being less than 50 μ m, obtains fine grain structure after high temperature insostatic pressing (HIP);
(2) disc is that wheel hub and wheel rim transition region adopt middle-sized powder, and powder size is 50-100 μ m, obtains the middle-sized grain structure between wheel hub and wheel rim after high temperature insostatic pressing (HIP);
(3) wheel rim adopts meal, and powder size, for being greater than 100～being less than or equal to 200 μ m, obtains coarse grain tissue after high temperature insostatic pressing (HIP), and to meet, wheel rim is high lastingly, the requirement of high creep resistance energy;
(4) diskware after high temperature insostatic pressing (HIP) is heat-treated: turbine disk hip temperature is 1170 ℃～1200 ℃, and turbine disk heat treatment solid solubility temperature is 1130 ℃～1150 ℃.
2. method according to claim 1, is characterized in that, turbine disk hip temperature is t
γ '+ 10 ℃～t
γ '+ 40 ℃, t
γ 'for γ ' phase solid solubility temperature in alloy.
3. method according to claim 1, is characterized in that, turbine disk heat treatment solid solubility temperature is t
γ '-30 ℃～t
γ '-10 ℃, t
γ 'for γ ' phase solid solubility temperature in alloy.
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| CN106378456A (en) * | 2016-11-16 | 2017-02-08 | 中国航空工业集团公司北京航空材料研究院 | Rapid densifying method for powder high-temperature alloy component |
| CN106623941A (en) * | 2016-11-16 | 2017-05-10 | 中国航空工业集团公司北京航空材料研究院 | Staged heating, extruding and form-controlling method of powder superalloy component |
| CN110177639A (en) * | 2016-10-27 | 2019-08-27 | 大马钢铁公司 | The method of manufacture patterning clad metal sheet |
| CN110267758A (en) * | 2016-12-31 | 2019-09-20 | 六号元素(英国)有限公司 | Superhard construction and its manufacturing method |
| CN110586948A (en) * | 2019-09-09 | 2019-12-20 | 中国人民解放军第五七一九工厂 | Preparation method of low-cost dual-performance powder turbine disc of aircraft engine |
| CN110695361A (en) * | 2019-10-31 | 2020-01-17 | 西安欧中材料科技有限公司 | Device and method for preparing alloy disc |
| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
| CN112214853A (en) * | 2020-10-22 | 2021-01-12 | 厦门大学 | Mechanical property calculation method for bimetal functional gradient turbine disc |
| CN113500191A (en) * | 2021-09-10 | 2021-10-15 | 西安欧中材料科技有限公司 | Method and device for preparing dual-performance powder turbine disc with continuously-changed crystal grains |
| CN114055076A (en) * | 2020-08-06 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Preparation method of multistage rotor assembly of aircraft engine |
| CN114147233A (en) * | 2022-02-10 | 2022-03-08 | 北京煜鼎增材制造研究院有限公司 | Missile warhead shell and additive manufacturing method thereof |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5527020A (en) * | 1992-03-13 | 1996-06-18 | General Electric Company | Differentially heat treated article, and apparatus and process for the manufacture thereof |
| US20060078455A1 (en) * | 2004-10-08 | 2006-04-13 | Igor Troitski | Method and system for manufacturing of multi-component complex shape parts consisting of monolithic and powder materials working at different performance conditions |
| CN102251984A (en) * | 2010-05-18 | 2011-11-23 | 诺沃皮尼奥内有限公司 | Jacket impeller with functional graded material and method |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
| CN102962453A (en) * | 2011-05-24 | 2013-03-13 | 电力研究所有限公司 | Method of manufacturing a weld-free apparatus for connection of dissimilar metals using functionally graded compositionally control powder metallurgy and hot isostatic processing methods |
-
2014
- 2014-01-06 CN CN201410005281.XA patent/CN103691952B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5527020A (en) * | 1992-03-13 | 1996-06-18 | General Electric Company | Differentially heat treated article, and apparatus and process for the manufacture thereof |
| US6478896B1 (en) * | 1992-03-13 | 2002-11-12 | General Electric Company | Differentially heat treated article, and apparatus and process for the manufacture thereof |
| US20060078455A1 (en) * | 2004-10-08 | 2006-04-13 | Igor Troitski | Method and system for manufacturing of multi-component complex shape parts consisting of monolithic and powder materials working at different performance conditions |
| CN102251984A (en) * | 2010-05-18 | 2011-11-23 | 诺沃皮尼奥内有限公司 | Jacket impeller with functional graded material and method |
| CN102962453A (en) * | 2011-05-24 | 2013-03-13 | 电力研究所有限公司 | Method of manufacturing a weld-free apparatus for connection of dissimilar metals using functionally graded compositionally control powder metallurgy and hot isostatic processing methods |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
Non-Patent Citations (2)
| Title |
|---|
| 胡本芙等: "双性能粉末高温合金涡轮盘的研究进展", 《航空材料学报》, vol. 24, no. 04, 1 August 2007 (2007-08-01), pages 80 - 84 * |
| 贾建等: "第三代粉末冶金高温合金René104的研究进展", 《粉末冶金工业》, vol. 17, no. 03, 10 June 2007 (2007-06-10), pages 36 - 43 * |
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| CN110177639A (en) * | 2016-10-27 | 2019-08-27 | 大马钢铁公司 | The method of manufacture patterning clad metal sheet |
| US11446736B2 (en) | 2016-10-27 | 2022-09-20 | Damasteel Ab | Method of making a patterned composite metal plate |
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| CN110267758A (en) * | 2016-12-31 | 2019-09-20 | 六号元素(英国)有限公司 | Superhard construction and its manufacturing method |
| CN110586948A (en) * | 2019-09-09 | 2019-12-20 | 中国人民解放军第五七一九工厂 | Preparation method of low-cost dual-performance powder turbine disc of aircraft engine |
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