CN103695702A - Rolled alloy rod used in aerospace field, and manufacturing method thereof - Google Patents
Rolled alloy rod used in aerospace field, and manufacturing method thereof Download PDFInfo
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Abstract
The present invention provides a rolled alloy rod used in the aerospace field, and a manufacturing method thereof. The alloy rod comprises, by weight, 11-18% of nickel, 1-3% of tin, 5-8% of aluminum, 0.05-0.3% of manganese, 0.05-0.1% of titanium, 0.05-0.1% of silver, and the balance of copper. According to the present invention, complete fusion of the copper-nickel alloy and the aluminum-tin alloy is utilized, the formed multi-element alloy can achieve the required strength so as to replace the beryllium-copper alloy, and performances of the alloy material are improved.
Description
Technical field
The present invention relates to alloy bar and manufacture field, particularly relate to alloy bar and manufacture method thereof that a kind of aerospace field of rolling is used.
Background technology
At present, the berylliumbronze that beryllium copper fusion forms has superior performance, such as its yield strength can be higher than 965MPa, and the high-end product components such as lining of therefore being used by extensive aerospace field.Yet the usage quantity of beryllium is appealed to reduce by U.S. Occupational Safety and Health Administration, because beryllium has certain toxicity, once human body sucks the beryllium dust of corresponding dosage, will cause fatefulue pulmonary disorder.In the middle of industrial production, existing different materials is such as the yield strength 431MPa of xantal, copper-nickel-tin alloy yield strength 724MPa, and its performance all can not reach the degree of berylliumbronze, can not be accepted completely always.Therefore, use can replace will the be following a kind of trend of the material of berylliumbronze completely and can in market, occupy advantage.
Summary of the invention
For solving the problems of the technologies described above, the invention provides a kind of alloy bar and manufacture method thereof of utilizing cupronickel and Sn-Al alloy to merge to substitute beryllium copper completely.
In order to realize foregoing invention object, the technical solution used in the present invention is as follows:
The alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 11-18%, and tin: 1-3%, aluminium: 5-8%, manganese: 0.05-0.3%, titanium: 0.05-0.1%, silver: 0.05-0.1%, surplus is copper.
Preferably, the alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 12-17%, tin: 1.25-2.75%, aluminium: 5.5-7.5%, manganese: 0.1-0.25%, titanium: 0.063-0.088%, silver: 0.063-0.088%, surplus is copper.
Preferably, the alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 13-16%, and tin: 1.5-2.5%, aluminium: 6-7%, manganese: 0.15-0.2%, titanium: 0.068-0.083%, silver: 0.068-0.083%, surplus is copper.
Preferably, the alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 14.5%, and tin: 2%, aluminium: 6.5%, manganese: 0.175%, titanium: 0.075%, silver: 0.075%, surplus is copper.
The manufacture method of the alloy bar that the aerospace field of above-mentioned rolling provided by the invention is used, comprises the steps:
Step 1: manufactured copper nickelalloy: according to weight proportion, electricity Xie Tong ﹑ Nie ﹑ tin is placed in main frequency furnace, is heated to 900 degree-950 degree, melting 1-1.5 hour, is incubated until completely melted to 850 degree, and soaking time is 0.5-1 hour;
Step 2: manufacture Sn-Al alloy: according to weight proportion, Lv ﹑ tin is placed in main frequency furnace, is heated to 660 degree-700 degree, melting 1-1.5 hour, is incubated until completely melted to 550 degree, and soaking time is 0.5-1 hour;
Step 3: the Sn-Al alloy liquation that insulation is completed adds in the middle of cupronickel liquation, is warming up to 1000 degree after stirring with graphite rod;
Step 4: adopt the mode of grinding to carry out powdered processing manganese, titanium, silver material, the powder diameter after processing is at 300-500 micron;
Step 5: the manganese that grinding is completed, titanium, silver adds in the middle of alloy liquid according to part by weight, reuses graphite rod and stirs, and it is distributed in the middle of alloy liquid completely, then main frequency furnace is incubated to 900 degree, and soaking time is 30 minutes.
Step 6: with direct-reading spectrometer, the sample taking out is carried out to 3-6 composition check in stove, to determine that its alloying constituent is within specialized range;
Step 7: adopt the mode of continuous casting that alloy liquid is cast as to ingot, then alloy pig is rolled into the diameter needing with 4 roller mills.In van-type annealing furnace, carry out tempering, tempering temperature is 400-450 degree, and the time is 2-2.5 hour; It is stand-by to make product that the material that tempering is completed carries out carrying out after naturally cooling corresponding mechanical workout;
Step 8: the alloy bar after rolling is completed is placed in van-type annealing furnace heat-treats, and treatment temp is 300-350 degree, and the time is 1.5-2 hour; Then the bar after finishing dealing with is put into concentration and is 5% salt solution cooling;
Step 9: the alloy bar after cooling completing is just detected a flaw and aligned, and warehouse-in is cut and packed to length as required.
Adopt the beneficial effect of technique scheme to be:
Adopt cupronickel and Sn-Al alloy to merge completely, can make corresponding multicomponent alloy reach the intensity needing, to realize the object that replaces beryllium copper.In alloy, add other trace elements, thereby utilize the effect of a plurality of trace elements in conjunction with corresponding rolling and brine quenching technique, to realize the performance of final alloy material brilliance, the yield strength of this material is greater than 1000MPa simultaneously.When realizing alternative poisonous beryllium element, improved again the performance of alloy material, thereby realized the target that replaces berylliumbronze completely.And the alloy pipe of producing is convenient to be processed into axle sleeve, compare and saved material with solid bar, improved production efficiency, reduced cost.
Embodiment
In order to make object of the present invention, technical scheme and advantage clearer, below in conjunction with embodiment, the present invention is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain the present invention, is not intended to limit the present invention.
Embodiment 1
The alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 11%, and tin: 1%, aluminium: 5%, manganese: 0.05%, titanium: 0.05%, silver: 0.05%, copper: 82.85%.
Its manufacture method comprises the steps:
1. manufactured copper nickelalloy: according to weight proportion, electricity Xie Tong ﹑ Nie ﹑ tin is placed in main frequency furnace, is heated to 900 degree-950 degree, melting 1-1.5 hour, is incubated until completely melted to 850 degree, and soaking time is 0.5-1 hour.
2. manufacture Sn-Al alloy: according to weight proportion, Lv ﹑ tin is placed in main frequency furnace, is heated to 660 degree-700 degree, melting 1-1.5 hour, is incubated until completely melted to 550 degree, and soaking time is 0.5-1 hour.
3. Sn-Al alloy liquation insulation being completed adds in the middle of cupronickel liquation, after stirring, is warming up to 1000 degree with graphite rod.
4. adopt the mode of grinding to carry out powdered processing manganese, titanium and silver, the powder diameter after processing is at 300-500 micron.
5. manganese grinding being completed, titanium, silver powder adds to according to weight in the middle of alloy liquid, reuses graphite rod and stirs, and it is distributed in the middle of alloy liquid completely.Then main frequency furnace is incubated to 900 degree.Soaking time is 30 minutes.
6. with German import Spike direct-reading spectrometer, the sample taking out is carried out to 3-6 composition check in stove, to determine that its alloying constituent is within specialized range.
7. adopt the mode of continuous casting that alloy liquid is cast as to ingot, then alloy pig is rolled into the diameter needing with 4 roller mills.In van-type annealing furnace, carry out tempering, tempering temperature is 400-450 degree, and the time is 2-2.5 hour; It is stand-by to make product that the material that tempering is completed carries out carrying out after naturally cooling corresponding mechanical workout.
8. the alloy bar after rolling being completed is placed in van-type annealing furnace heat-treats, and treatment temp is 300-350 degree, and the time is 1.5-2 hour; Then the bar after finishing dealing with is put into concentration and is 5% salt solution cooling.
9. the alloy bar after cooling completing is just detected a flaw and aligns, and warehouse-in is cut and packed to length as required.
The alloy bar yield strength that the present embodiment obtains is after testing 973MPa, is greater than the yield strength of berylliumbronze.Realize when substituting poisonous beryllium element, also improved the performance of alloy material, thereby realize the target that replaces berylliumbronze completely.
Embodiment 2
The alloy bar that the aerospace field of rolling is used, is comprised of following weight percentage component: nickel: 18%, and tin: 3%, aluminium: 8%, manganese: 0.3%, titanium: 0.1%, silver: 0.1%, copper: 70.5%.
Its manufacture method comprises the steps:
1. manufactured copper nickelalloy: according to weight proportion, electricity Xie Tong ﹑ Nie ﹑ tin is placed in main frequency furnace, is heated to 900 degree-950 degree, melting 1-1.5 hour, is incubated until completely melted to 850 degree, and soaking time is 0.5-1 hour.
2. manufacture Sn-Al alloy: according to weight proportion, Lv ﹑ tin is placed in main frequency furnace, is heated to 660 degree-700 degree, melting 1-1.5 hour, is incubated until completely melted to 550 degree, and soaking time is 0.5-1 hour.
3. Sn-Al alloy liquation insulation being completed adds in the middle of cupronickel liquation, after stirring, is warming up to 1000 degree with graphite rod.
4. by manganese, titanium and silver adopt the mode of grinding to carry out powdered processing, and the powder diameter after processing is at 300-500 micron.
5. manganese grinding being completed, titanium, silver powder adds to according to weight in the middle of alloy liquid, reuses graphite rod and stirs, and it is distributed in the middle of alloy liquid completely.Then main frequency furnace is incubated to 900 degree.Soaking time is 30 minutes.
6. with German import Spike direct-reading spectrometer, the sample taking out is carried out to 3-6 composition check in stove, to determine that its alloying constituent is within specialized range.
7. adopt the mode of continuous casting that alloy liquid is cast as to ingot, then alloy pig is rolled into the diameter needing with 4 roller mills.In van-type annealing furnace, carry out tempering, tempering temperature is 400-450 degree, and the time is 2-2.5 hour; It is stand-by to make product that the material that tempering is completed carries out carrying out after naturally cooling corresponding mechanical workout.
8. the alloy bar after rolling being completed is placed in van-type annealing furnace heat-treats, and treatment temp is 300-350 degree, and the time is 1.5-2 hour; Then the bar after finishing dealing with is put into concentration and is 5% salt solution cooling.
9. the alloy bar after cooling completing is just detected a flaw and aligns, and warehouse-in is cut and packed to length as required.
The alloy bar yield strength that the present embodiment obtains is after testing greater than 986MPa, is greater than equally the yield strength of berylliumbronze.Realize when substituting poisonous beryllium element, improved the performance of alloy material, thereby realize the target that replaces berylliumbronze completely.
Embodiment 3
An alloy bar that substitutes berylliumbronze for the aerospace field of rolling, is comprised of following weight percentage component: nickel: 14.5%, and tin: 2%, aluminium: 6.5%, manganese: 0.175%, titanium: 0.075%, silver: 0.075%, copper: 76.675%.
Its manufacture method comprises the steps:
1. manufactured copper nickelalloy: according to weight proportion, electricity Xie Tong ﹑ Nie ﹑ tin is placed in main frequency furnace, is heated to 900 degree-950 degree, melting 1-1.5 hour, is incubated until completely melted to 850 degree, and soaking time is 0.5-1 hour;
2. manufacture Sn-Al alloy: according to weight proportion, Lv ﹑ tin is placed in main frequency furnace, is heated to 660 degree-700 degree, melting 1-1.5 hour, is incubated until completely melted to 550 degree, and soaking time is 0.5-1 hour;
3. Sn-Al alloy liquation insulation being completed adds in the middle of cupronickel liquation, after stirring, is warming up to 1000 degree with graphite rod;
4. by manganese, titanium and silver adopt the mode of grinding to carry out powdered processing, and the powder diameter after processing is at 300-500 micron;
5. manganese grinding being completed, titanium, silver powder adds to according to weight in the middle of alloy liquid, reuses graphite rod and stirs, and it is distributed in the middle of alloy liquid completely.Then main frequency furnace is incubated to 900 degree.Soaking time is 30 minutes;
6. with German import Spike direct-reading spectrometer, the sample taking out is carried out to 3-6 composition check in stove, to determine that its alloying constituent is within specialized range;
7. adopt the mode of continuous casting that alloy liquid is cast as to ingot, then alloy pig is rolled into the diameter needing with 4 roller mills.In van-type annealing furnace, carry out tempering, tempering temperature is 400-450 degree, and the time is 2-2.5 hour; It is stand-by to make product that the material that tempering is completed carries out carrying out after naturally cooling corresponding mechanical workout;
8. the alloy bar after rolling being completed is placed in van-type annealing furnace heat-treats, and treatment temp is 300-350 degree, and the time is 1.5-2 hour; Then the bar after finishing dealing with is put into concentration and is 5% salt solution cooling;
9. the alloy bar after cooling completing is just detected a flaw and aligns, and warehouse-in is cut and packed to length as required.
The alloy bar yield strength that the present embodiment obtains is after testing greater than 1100MPa, is not only greater than the yield strength of berylliumbronze, is also greater than the yield strength of above-mentioned two embodiment.Realize when substituting poisonous beryllium element, also improved the performance of alloy material, thereby realize the target that replaces berylliumbronze completely.
The above embodiment has only expressed embodiments of the present invention, and it describes comparatively concrete and detailed, but can not therefore be interpreted as the restriction to the scope of the claims of the present invention.It should be pointed out that for the person of ordinary skill of the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.Therefore, the protection domain of patent of the present invention should be as the criterion with claims.
Claims (5)
1. the alloy bar that the aerospace field of rolling is used, is characterized in that, following weight percentage component, consists of: nickel: 11-18%, and tin: 1-3%, aluminium: 5-8%, manganese: 0.05-0.3%, titanium: 0.05-0.1%, silver: 0.05-0.1%, surplus is copper.
2. the alloy bar that the aerospace field of rolling according to claim 1 is used, it is characterized in that, by following weight percentage component, formed: nickel: 12-17%, tin: 1.25-2.75%, aluminium: 5.5-7.5%, manganese: 0.1-0.25%, titanium: 0.063-0.088%, silver: 0.063-0.088%, surplus is copper.
3. the alloy bar that the aerospace field of rolling according to claim 1 is used, it is characterized in that, by following weight percentage component, formed: nickel: 13-16%, tin: 1.5-2.5%, aluminium: 6-7%, manganese: 0.15-0.2%, titanium: 0.068-0.083%, silver: 0.068-0.083%, surplus is copper.
4. the alloy bar that the aerospace field of rolling according to claim 1 is used, is characterized in that, consists of: nickel: 14.5% following weight percentage component, tin: 2%, aluminium: 6.5%, manganese: 0.175%, titanium: 0.075%, silver: 0.075%, surplus is copper.
5. the manufacture method of the alloy bar that the aerospace field of a kind of rolling described in claim 1-4 is used, is characterized in that comprising the following steps:
Step 1: manufactured copper nickelalloy: according to weight proportion, electricity Xie Tong ﹑ Nie ﹑ tin is placed in main frequency furnace, is heated to 900 degree-950 degree, melting 1-1.5 hour, is incubated until completely melted to 850 degree, and soaking time is 0.5-1 hour;
Step 2: manufacture Sn-Al alloy: according to weight proportion, Lv ﹑ tin is placed in main frequency furnace, is heated to 660 degree-700 degree, melting 1-1.5 hour, is incubated until completely melted to 550 degree, and soaking time is 0.5-1 hour;
Step 3: the Sn-Al alloy liquation that insulation is completed adds in the middle of cupronickel liquation, is warming up to 1000 degree after stirring with graphite rod;
Step 4: adopt the mode of grinding to carry out powdered processing manganese, titanium, silver material, the powder diameter after processing is at 300-500 micron;
Step 5: the manganese that grinding is completed, titanium, silver powder adds to according to weight in the middle of alloy liquid, reuses graphite rod and stirs, and it is distributed in the middle of alloy liquid completely, then main frequency furnace is incubated to 900 degree, and soaking time is 30 minutes;
Step 6: with direct-reading spectrometer, the sample taking out is carried out to 3-6 composition check in stove, to determine that its alloying constituent is within specialized range;
Step 7: adopt the mode of continuous casting that alloy liquid is cast as to ingot, then alloy pig is rolled into the diameter needing with 4 roller mills.In van-type annealing furnace, carry out tempering, tempering temperature is 400-450 degree, and the time is 2-2.5 hour; It is stand-by to make product that the material that tempering is completed carries out carrying out after naturally cooling corresponding mechanical workout;
Step 8: the alloy bar after rolling is completed is placed in van-type annealing furnace heat-treats, and treatment temp is 300-350 degree, and the time is 1.5-2 hour; Then the bar after finishing dealing with is put into concentration and is 5% salt solution cooling;
Step 9: the alloy bar after cooling completing is just detected a flaw and aligned, and warehouse-in is cut and packed to length as required.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104959838A (en) * | 2015-07-07 | 2015-10-07 | 成都亨通兆业精密机械有限公司 | Automatic smooth-rod production device |
| CN105033659A (en) * | 2015-07-07 | 2015-11-11 | 成都亨通兆业精密机械有限公司 | Full-automatic ring gauge machining equipment |
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| JPS60230949A (en) * | 1984-04-27 | 1985-11-16 | Kobe Steel Ltd | Material for quartz oscillator case |
| JPS63274729A (en) * | 1987-04-30 | 1988-11-11 | Furukawa Electric Co Ltd:The | Copper alloy for electronic and electrical appliance |
| JPS63317636A (en) * | 1987-06-19 | 1988-12-26 | Mitsubishi Electric Corp | Copper alloy for burn-in ic socket of semiconductor device |
| JPH01198440A (en) * | 1988-02-01 | 1989-08-10 | Furukawa Electric Co Ltd:The | Copper alloy for high tensile electric and electronic equipment |
| CN101426961A (en) * | 2006-04-26 | 2009-05-06 | 日矿金属株式会社 | Heat-resistant Sn-plated Cu-Zn alloy strip suppressed in whiskering |
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2013
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB674127A (en) * | 1949-08-12 | 1952-06-18 | William Percival Fentiman | Improvements in or relating to copper base alloys |
| JPS60230949A (en) * | 1984-04-27 | 1985-11-16 | Kobe Steel Ltd | Material for quartz oscillator case |
| JPS63274729A (en) * | 1987-04-30 | 1988-11-11 | Furukawa Electric Co Ltd:The | Copper alloy for electronic and electrical appliance |
| JPS63317636A (en) * | 1987-06-19 | 1988-12-26 | Mitsubishi Electric Corp | Copper alloy for burn-in ic socket of semiconductor device |
| JPH01198440A (en) * | 1988-02-01 | 1989-08-10 | Furukawa Electric Co Ltd:The | Copper alloy for high tensile electric and electronic equipment |
| CN101426961A (en) * | 2006-04-26 | 2009-05-06 | 日矿金属株式会社 | Heat-resistant Sn-plated Cu-Zn alloy strip suppressed in whiskering |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104959838A (en) * | 2015-07-07 | 2015-10-07 | 成都亨通兆业精密机械有限公司 | Automatic smooth-rod production device |
| CN105033659A (en) * | 2015-07-07 | 2015-11-11 | 成都亨通兆业精密机械有限公司 | Full-automatic ring gauge machining equipment |
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