CN103240382A - Post-forging treatment method for TC11 titanium alloy miniature precisely forged blade - Google Patents
Post-forging treatment method for TC11 titanium alloy miniature precisely forged blade Download PDFInfo
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- CN103240382A CN103240382A CN2013101702276A CN201310170227A CN103240382A CN 103240382 A CN103240382 A CN 103240382A CN 2013101702276 A CN2013101702276 A CN 2013101702276A CN 201310170227 A CN201310170227 A CN 201310170227A CN 103240382 A CN103240382 A CN 103240382A
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Abstract
The invention belongs to the titanium alloy forging manufacturing technique, relates to improvement for a precision forging method for a TC11 titanium alloy miniature precisely forged blade, and discloses a post-forging treatment method for a TC11 titanium alloy miniature precisely forged blade. The post-forging treatment method is characterized by comprising precision forging steps of primary annealing, cold trimming, thermal calibration and secondary annealing. The post-forging treatment method has the advantages that the bending degree and torsional deformation of a profile of a blade body are reduced, the yield of products is increased, and the manufacturing cost is lowered.
Description
Technical field
The invention belongs to the titanium alloy forging technology, relate to the improvement of TC11 Ti alloy miniature finish forge blade being forged post-processing approach.
Background technology
A kind of TC11 Ti alloy miniature finish forge blade is characterized in that size is little, and generally about 8～50mm, the blade profile is thin for blade length, and inlet and outlet edge minimum thickness has only about 0.08mm.Present forging post-processing approach is made up of annealing for the first time, annealing for the second time, cold-trim(ming) and four operations of thermal recalibration, and the order of four operations is: annealing for the first time, annealing for the second time, cold-trim(ming) and thermal recalibration.Adopt the cooling in heap mode in the cooling work step of annealing for the first time, Ti alloy miniature finish forge blade stacking is cold in the enterprising line space of support.The shortcoming of above-mentioned forging post-processing approach is: the bending of blade profile, torsional deflection are bigger, cause blade dimensions overproof, and product percent of pass is low, the manufacturing cost height.
Summary of the invention
The objective of the invention is: provide a kind of TC11 Ti alloy miniature finish forge blade that can reduce deformable blade to forge post-processing approach, to reduce the bending of blade profile, torsional deflection, avoid blade dimensions overproof, improve product percent of pass, reduce manufacturing cost.
Technical scheme of the present invention is: a kind of TC11 Ti alloy miniature finish forge blade is forged post-processing approach, the blade length of handled miniature finish forge blade is not more than 50mm, forging post processing is made up of annealing for the first time, annealing for the second time, cold-trim(ming) and four operations of thermal recalibration, it is characterized in that, the order of four operations is: annealing for the first time, cold-trim(ming), thermal recalibration and annealing for the second time;
1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat-treat in vacuum drying oven, are warming up to 650 ℃～700 ℃ by room temperature, insulation 10min～20min, be warming up to 940 ℃～960 ℃ again, insulation 60min～90min feeds argon gas then in the stove and cools to room temperature with the furnace;
2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
3, thermal recalibration: miniature finish forge blade is put into heating furnace be heated to 450 ℃～480 ℃, insulation 5min～20min puts into straightening die then and proofreaies and correct, pressurize 3min～5min;
4, annealing for the second time:: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 520 ℃～550 ℃, insulation 350min～400min feeds argon gas then in the stove and cools to room temperature with the furnace.
Advantage of the present invention is: provide a kind of TC11 Ti alloy miniature finish forge blade that can reduce deformable blade to forge post-processing approach, reduced the bending of blade profile, torsional deflection, avoided blade dimensions overproof, improved product percent of pass, reduced manufacturing cost.Evidence, behind employing the present invention, the qualification rate of the miniature finish forge blade of certain Type Titanium Alloy has improved more than 30%.
The specific embodiment
Below the present invention is described in further details.A kind of TC11 Ti alloy miniature finish forge blade is forged post-processing approach, the blade length of handled miniature finish forge blade is not more than 50mm, forging post processing is made up of annealing for the first time, annealing for the second time, cold-trim(ming) and four operations of thermal recalibration, it is characterized in that, the order of four operations is: annealing for the first time, cold-trim(ming), thermal recalibration and annealing for the second time;
1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat-treat in vacuum drying oven, are warming up to 650 ℃～700 ℃ by room temperature, insulation 10min～20min, be warming up to 940 ℃～960 ℃ again, insulation 60min～90min feeds argon gas then in the stove and cools to room temperature with the furnace;
2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
3, thermal recalibration: miniature finish forge blade is put into heating furnace be heated to 450 ℃～480 ℃, insulation 5min～20min puts into straightening die then and proofreaies and correct, pressurize 3min～5min;
4, annealing for the second time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 520 ℃～550 ℃, insulation 350min～400min feeds argon gas then in the stove and cools to room temperature with the furnace.
Embodiment 1, handles certain type TC11 titanium alloy guided missile fan primary rotor blade, this blade length 35.8mm, and blade profile exhaust edge minimum thickness has only 0.056mm.
1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neat compact side direction is placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, and heat treatment in vacuum drying oven is warming up to 680 ℃ of insulations by room temperature, insulation 15min, be warming up to 950 ℃ again, insulation 70min feeds argon gas then in the stove and cools to room temperature with the furnace;
2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
3, thermal recalibration: miniature finish forge blade is put into heating furnace be heated to 460 ℃, insulation 18min puts into straightening die pressurize 3min then;
4, annealing for the second time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 530 ℃, insulation 360min feeds argon gas then in the stove and cools to room temperature with the furnace.
Embodiment 2, handle certain type TC11 titanium alloy guided missile fan secondary rotor blade, this blade length 32.3mm, and blade profile exhaust edge minimum thickness has only 0.066mm.
1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neat compact side direction is placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, and heat treatment in vacuum drying oven is warming up to 690 ℃ of insulations by room temperature, insulation 13min, be warming up to 955 ℃ again, insulation 65min feeds argon gas then in the stove and cools to room temperature with the furnace;
2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
3, thermal recalibration: miniature finish forge blade is put into heating furnace be heated to 465 ℃, insulation 15min puts into straightening die pressurize 4min then;
4, annealing for the second time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 535 ℃, insulation 355min feeds argon gas then in the stove and cools to room temperature with the furnace.
Embodiment 3, handle certain type TC11 titanium alloy guided missile fan one-level stator blade, this blade length 28.0mm, and blade profile exhaust edge minimum thickness has only 0.086mm.
1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neat compact side direction is placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, and heat treatment in vacuum drying oven is warming up to 695 ℃ of insulations by room temperature, insulation 12min, be warming up to 960 ℃ again, insulation 60min feeds argon gas then in the stove and cools to room temperature with the furnace;
2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
3, thermal recalibration: miniature finish forge blade is put into heating furnace be heated to 470 ℃, insulation 12min puts into straightening die pressurize 5min then;
4, annealing for the second time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 540 ℃, insulation 350min feeds argon gas then in the stove and cools to room temperature with the furnace.
Claims (1)
1. a TC11 Ti alloy miniature finish forge blade is forged post-processing approach, the blade length of handled miniature finish forge blade is not more than 50mm, forging post processing is made up of annealing for the first time, annealing for the second time, cold-trim(ming) and four operations of thermal recalibration, it is characterized in that, the order of four operations is: annealing for the first time, cold-trim(ming), thermal recalibration and annealing for the second time;
1.1, annealing for the first time: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat-treat in vacuum drying oven, are warming up to 650 ℃～700 ℃ by room temperature, insulation 10min～20min, be warming up to 940 ℃～960 ℃ again, insulation 60min～90min feeds argon gas then in the stove and cools to room temperature with the furnace;
1.2, cold-trim(ming): miniature finish forge blade forging is put into shaving die, use punch press to carry out cold-trim(ming), the back of cutting edge forms miniature finish forge blade;
1.3, thermal recalibration: miniature finish forge blade is put into heating furnace is heated to 450 ℃～480 ℃, the insulation 5min～20min, put into straightening die then and proofread and correct, pressurize 3min～5min;
1.4, annealing for the second time:: with the leading edge edge of miniature finish forge blade forging downwards, the leaf basin in the same direction, vertically neatly compactly side direction be placed in the bin, mark is capable to be put, the two ends of the blade of putting are supported by bin, heat treatment in vacuum drying oven, be warming up at 520 ℃～550 ℃, insulation 350min～400min feeds argon gas then in the stove and cools to room temperature with the furnace.
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| CN201310170227.6A CN103240382B (en) | 2013-05-10 | 2013-05-10 | Post-forging treatment method for TC11 titanium alloy miniature precisely forged blade |
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| CN201310170227.6A CN103240382B (en) | 2013-05-10 | 2013-05-10 | Post-forging treatment method for TC11 titanium alloy miniature precisely forged blade |
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| CN103240382B CN103240382B (en) | 2015-04-29 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113462872A (en) * | 2021-06-30 | 2021-10-01 | 中国航发动力股份有限公司 | Blade and preparation process thereof |
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| US6754954B1 (en) * | 2003-07-08 | 2004-06-29 | Borgwarner Inc. | Process for manufacturing forged titanium compressor wheel |
| CN101338824A (en) * | 2007-07-11 | 2009-01-07 | 浙江盾安人工环境设备股份有限公司 | Electromagnetic four-way valve main valve seat processing method |
| JP2011137204A (en) * | 2009-12-28 | 2011-07-14 | Daido Steel Co Ltd | Method for manufacturing rod stock made from titanium alloy |
| CN102248116A (en) * | 2011-03-30 | 2011-11-23 | 浙江迪特高强度螺栓有限公司 | Manufacturing process for bolt with high strength of more than phi 30 |
| CN102248118A (en) * | 2011-04-14 | 2011-11-23 | 大连大高阀门有限公司 | Die and process for forging high-speed railway substrate |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6754954B1 (en) * | 2003-07-08 | 2004-06-29 | Borgwarner Inc. | Process for manufacturing forged titanium compressor wheel |
| CN101338824A (en) * | 2007-07-11 | 2009-01-07 | 浙江盾安人工环境设备股份有限公司 | Electromagnetic four-way valve main valve seat processing method |
| JP2011137204A (en) * | 2009-12-28 | 2011-07-14 | Daido Steel Co Ltd | Method for manufacturing rod stock made from titanium alloy |
| CN102248116A (en) * | 2011-03-30 | 2011-11-23 | 浙江迪特高强度螺栓有限公司 | Manufacturing process for bolt with high strength of more than phi 30 |
| CN102248118A (en) * | 2011-04-14 | 2011-11-23 | 大连大高阀门有限公司 | Die and process for forging high-speed railway substrate |
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| 陈思觉: "TC9钛合金模锻叶片热加工变形及校正", 《材料工程》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113462872A (en) * | 2021-06-30 | 2021-10-01 | 中国航发动力股份有限公司 | Blade and preparation process thereof |
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Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |