CN103212958A - Processing method of connecting piece for aircraft engine - Google Patents
Processing method of connecting piece for aircraft engine Download PDFInfo
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- CN103212958A CN103212958A CN2013101709769A CN201310170976A CN103212958A CN 103212958 A CN103212958 A CN 103212958A CN 2013101709769 A CN2013101709769 A CN 2013101709769A CN 201310170976 A CN201310170976 A CN 201310170976A CN 103212958 A CN103212958 A CN 103212958A
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- processing method
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- connector
- cold working
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Abstract
The invention provides a processing method of a connecting piece for an aircraft engine, which aims to overcome the defect that the mechanical performance of a whole aircraft engine connecting piece is influenced when a metal flow line breaks in deformation. The processing method comprises the following steps of: (1) performing cold machining on a blank, wherein the primary cold machining is used for guaranteeing that the sizes of a thread and a pole at the connecting part can achieve 40% of designed sizes, and the secondary cold machining is used for guaranteeing that the sizes of the thread and the pole at the connecting part can achieve 85% of the designed sizes; (2) heating the cold machined material to 750-780 DEG.C, and inletting argon for protection to perform primary thermal forming; (3) continuously heating the material to 1200-1250 DEG.C, and inletting argon for protection to perform secondary thermal forming; (4) slowly cooling the material to the room temperature in an insulation can after the secondary thermal forming; and (5) performing surface mechanical strengthening and antiseptic treatment. The processing method is used for producing the aircraft connecting piece.
Description
Technical field:
The present invention relates to a kind of processing technology of connector, a kind of aero-engine of specific design processing method of connector.
Background technology:
The various piece of engine all is just to connect into as a whole by finding, the reliability of finding is directly connected to the just too service life of engine, performance and security, use development along with modern fighter plane, the condition of work of engine becomes more abominable, most of findings all are operated under the high temperature and high pressure environment, except selection itself has certain requirement, what the aviation connector at first will solve in process is the problem of metal streamline in the head forming process, generally in process of production, because distortion of materials causes the direction uniformity difference of metal streamline, just can cause the difference of mechanical performance, this is fatal defective for aviation company's fitting, because metal streamline produces the mechanical performance that fracture will influence entire product in distortion.Common connector at first will carry out thermo forming in the process of processing, material is when heating, structure can change, and the putting more effort of leading edge deformation, and so more is easy to generate the fracture of metal streamline and the texture of metal streamline occurs staggered.Cause it that fracture of streamline in use takes place easily.
Summary of the invention:
The objective of the invention is provides the processing method of a kind of aero-engine with connector at the problem of above-mentioned existence, it is staggered to avoid connector that the texture of the fracture of metal streamline and metal streamline takes place in the process of moulding, guarantee the security of aero-engine, prolong the service life of aero-engine.
Above-mentioned purpose realizes by following technical scheme:
The aero-engine processing method of connector, this method comprises the steps:
(1) blank is carried out cold working, a cold working guarantees that earlier coupling part screw thread and bar portion size reach 40% of design size, and secondary cold working guarantees that coupling part screw thread and bar portion size reach design size 85%;
(2) material after the cold working is heated to 750 ℃-780 ℃, feeds argon shield, carry out one-step hot moulding;
(3) continue to be heated to 1200 ℃-1250 ℃, feed argon shield, carry out the secondary thermoforming;
(4) in incubator, carry out slow cool to room temperature after the secondary thermoforming;
(5) carry out surperficial mechanical enhancer and preservative treatment.
Described aero-engine is with the processing method of connector, and the slow cool to room temperature that carries out in incubator described in the step (4) is meant from the time of 1200 ℃ of-1250 ℃ of slow cool to room temperature and is no less than 3 hours.
Described aero-engine is with the processing method of connector, and carry out surperficial mechanical enhancer and preservative treatment described in the step (5) are meant and earlier connector are carried out Shot Blasting, and then carry out surface blackening and handle.
Beneficial effect:
The present invention at first adopts cold working, because because of cold working does not have variations in temperature, basic change does not take place in the metallographic structure of material, molecular structure also with raw-material put in order consistent.Preliminary so preformed resultant metal streamline is consistent with raw-material metal streamline.And reach design size 85% through coupling part screw thread after twice cold working and bar portion size; hot worked deflection will dwindle; in the process of thermoforming; through test of many times; the present invention adopts preheat 750 ℃-780 ℃ early stage; make material not produce phase transformation in the phase transition temperature critical point; and append atmosphere protection, and carry out one-shot forming, continue simultaneously to heat to material; feed more protective atmosphere; when being heated to 1200 ℃-1250 ℃, carry out post forming, the product after the moulding; need be kept in the insulating box; allow product cool off naturally, so both guaranteed that the product heat distortion amount is very little, guarantee that again metal phase change process molecular structure reverts to original putting in order; the metal streamline that has guaranteed head does not have the fracture of streamline with original consistent.
The specific embodiment:
Embodiment 1:
The aero-engine processing method of connector, this method comprises the steps:
(1) blank is carried out cold working, a cold working guarantees that earlier coupling part screw thread and bar portion size reach 40% of design size, and secondary cold working guarantees that coupling part screw thread and bar portion size reach design size 85%;
(2) material after the cold working is heated to 780 ℃, feeds argon shield, carry out one-step hot moulding;
(3) continue to be heated to 1250 ℃, feed argon shield, carry out the secondary thermoforming;
(4) in incubator, carry out slow cool to room temperature after the secondary thermoforming;
(5) carry out surperficial mechanical enhancer and preservative treatment.
Described aero-engine is with the processing method of connector, and the slow cool to room temperature that carries out in incubator described in the step (4) is meant from the time of 1250 ℃ of slow cool to room temperature and is no less than 3 hours.
Described aero-engine is with the processing method of connector, and carry out surperficial mechanical enhancer and preservative treatment described in the step (5) are meant and earlier connector are carried out Shot Blasting, and then carry out surface blackening and handle.
Embodiment 2:
The difference of present embodiment and embodiment 1 is that the temperature of one-step hot moulding adopts 750 ℃.
Embodiment 3:
The difference of present embodiment and embodiment 1 or embodiment 2 is that the temperature of secondary thermoforming is 1200 ℃.
Embodiment 4:
The difference of present embodiment and embodiment 1 is that the temperature of one-step hot moulding adopts 730 ℃.
Embodiment 5:
The difference of present embodiment and embodiment 1 or embodiment 2 is that the temperature of secondary thermoforming is 1220 ℃.
Below only be most preferred embodiment of the present invention, method of the present invention includes but not limited to the disclosed technical scheme of the foregoing description.Unaccomplished matter of the present invention belongs to those skilled in the art's common practise.
Claims (3)
1. an aero-engine is with the processing method of connector, and it is characterized in that: this method comprises the steps:
(1) blank is carried out cold working, a cold working guarantees that earlier coupling part screw thread and bar portion size reach 40% of design size, and secondary cold working guarantees that coupling part screw thread and bar portion size reach design size 85%;
(2) material after the cold working is heated to 750 ℃-780 ℃, feeds argon shield, carry out one-step hot moulding;
(3) continue to be heated to 1200 ℃-1250 ℃, feed argon shield, carry out the secondary thermoforming;
(4) in incubator, carry out slow cool to room temperature after the secondary thermoforming;
(5) carry out surperficial mechanical enhancer and preservative treatment.
2. aero-engine according to claim 1 is characterized in that with the processing method of connector: the slow cool to room temperature that carries out in incubator described in the step (4) is meant from the time of 1200 ℃ of-1250 ℃ of slow cool to room temperature and is no less than 3 hours.
3. aero-engine according to claim 1 and 2 is characterized in that with the processing method of connector: carry out surperficial mechanical enhancer and preservative treatment described in the step (5) are meant and earlier connector are carried out Shot Blasting, and then carry out surface blackening and handle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101709769A CN103212958A (en) | 2013-05-10 | 2013-05-10 | Processing method of connecting piece for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101709769A CN103212958A (en) | 2013-05-10 | 2013-05-10 | Processing method of connecting piece for aircraft engine |
Publications (1)
| Publication Number | Publication Date |
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| CN103212958A true CN103212958A (en) | 2013-07-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101709769A Pending CN103212958A (en) | 2013-05-10 | 2013-05-10 | Processing method of connecting piece for aircraft engine |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3438118A (en) * | 1965-06-10 | 1969-04-15 | Philips Corp | Method of forming ceramic-to-metal seal |
| US3877281A (en) * | 1972-10-27 | 1975-04-15 | Kobe Steel Ltd | Method for producing a high strength bolt |
| CN101549448A (en) * | 2008-03-31 | 2009-10-07 | 江都狮鹤高强度螺栓有限公司 | Processing technology for high-strength bolt used for steel net frame bolt ball node |
| CN101797685A (en) * | 2010-04-08 | 2010-08-11 | 浙江裕泰紧固件制造有限公司 | Process for manufacturing high-strength bolt |
| CN102990295A (en) * | 2012-09-28 | 2013-03-27 | 江苏永昊高强度螺栓有限公司 | Aviation connecting piece with consistent metal flow and producing method thereof |
| CN103009011A (en) * | 2012-12-28 | 2013-04-03 | 贵州精立航太科技有限公司 | Processing method for stainless steel high-strength bolt |
-
2013
- 2013-05-10 CN CN2013101709769A patent/CN103212958A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3438118A (en) * | 1965-06-10 | 1969-04-15 | Philips Corp | Method of forming ceramic-to-metal seal |
| US3877281A (en) * | 1972-10-27 | 1975-04-15 | Kobe Steel Ltd | Method for producing a high strength bolt |
| CN101549448A (en) * | 2008-03-31 | 2009-10-07 | 江都狮鹤高强度螺栓有限公司 | Processing technology for high-strength bolt used for steel net frame bolt ball node |
| CN101797685A (en) * | 2010-04-08 | 2010-08-11 | 浙江裕泰紧固件制造有限公司 | Process for manufacturing high-strength bolt |
| CN102990295A (en) * | 2012-09-28 | 2013-03-27 | 江苏永昊高强度螺栓有限公司 | Aviation connecting piece with consistent metal flow and producing method thereof |
| CN103009011A (en) * | 2012-12-28 | 2013-04-03 | 贵州精立航太科技有限公司 | Processing method for stainless steel high-strength bolt |
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Application publication date: 20130724 |