CN101701555A - Anti-fatigue corrosion-resisting body for hot air engine - Google Patents
Anti-fatigue corrosion-resisting body for hot air engine Download PDFInfo
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- CN101701555A CN101701555A CN200910201749A CN200910201749A CN101701555A CN 101701555 A CN101701555 A CN 101701555A CN 200910201749 A CN200910201749 A CN 200910201749A CN 200910201749 A CN200910201749 A CN 200910201749A CN 101701555 A CN101701555 A CN 101701555A
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Abstract
The invention discloses an anti-fatigue corrosion-resisting body for a hot air engine; the material of the anti-fatigue corrosion-resisting body is duplex stainless steel with half ferrite and half austenite in a solution treatment structure; the body blank is manufactured by forging, and then is machined integrally; after the blank is manufactured, first solution treatment is carried out, and then rough machining is carried out, second solution treatment is carried out next, and finally, the finish-machining product is manufactured; the anti-fatigue corrosion-resisting body has the advantages of good corrosion resistance, strong anti-fatigue performance and good processability, and the service life and the reliability of the body are remarkably improved.
Description
Technical field
The present invention relates to fuselage, especially a kind of heat engine antifatigue corrosion-resisting body.
Background technique
Fuselage is one of heat engine key components and parts, also is to constitute one of heat engine Stirling circuit core component.Usually, fuselage is equipped with heater block, crankcase components and external combustion systems as the matrix of heat engine on it, and external combustion systems, the heat exchange series transmission system of unifying connect is constituted heat engine integral body.Simultaneously, also be furnished with heat engine cylinder sleeve, cooler parts in fuselage interior, and cooling water runner, working medium runner etc., structure is very complicated, and difficulty of processing is big, the processing cost height.The heat engine heater adopts usually with fuselage and is threaded.Because Stirling engine is a kind of external-combustion engine, by continuing high-intensity combustion in external combustion system, heat is passed to the heat engine internal working medium by heater, working medium circulates in circular work in the heat engine with Stirling, promote reciprocating motion of the pistons, the working medium maximum pressure can reach 18～20MPa, therefore, when fuselage was worked at heat engine, very big alternation mechanical load and heat load were born in the screw thread position that fuselage is connected with heater.Because heat engine is a fuel with fuel oil, rock gas usually, products of combustion is mainly carbon dioxide and water, but also can contain mordant sulphide, carbonic acid, oxalic acid, silicate etc. usually.In addition, heat engine is equipped with cooler, also needs with the cooling water of big flow working medium to be cooled off.Therefore, fuselage with the heater point of attachment, not only bear bigger alternation heat load, mechanical load, also need bear washing away from external combustion systems corrosivity products of combustion, and the mobile corrosion of the big flow cooling water of inner cooling water runner, operating conditions is very abominable, and fuselage is fatigue corrosion very easily.
Heat engine fuselage function class is similar to internal combustion (IC) engine cylinder block.Internal combustion (IC) engine cylinder block adopts the mode of casting to process usually, and general material is a spheroidal graphite cast iron, gray cast iron, and low-alloy cast iron, and cast aluminium alloy etc.Because not only intensity is lower for cast iron class and cast aluminium alloy class material, and decay resistance is relatively poor, and cavitation pitting and stress corrosion cracking take place easily.The operating conditions of heat engine fuselage wants abominable many than internal combustion (IC) engine cylinder block, so cast iron class and cast aluminium alloy class material are not suitable for the heat engine fuselage.For this reason, the heat engine fuselage adopts usually that intensity is higher, corrosion resistance martensite stainless steel material preferably, is the stainless steel of 0Cr17Ni4Cu4Nb as the trade mark.But above-mentioned fuselage, though having had, life-span and reliability significantly improve, but the life-span still is difficult to satisfy the heat engine reliability requirement that improves constantly, and its difficulty of processing is big, poor reliability, particularly in use for some time, fatigue corrosion crack very easily takes place in fuselage and heater connection part, causes refrigerant leakage and loses efficacy, and service time is short, poor reliability is generally about 500h.
Summary of the invention
The object of the present invention is to provide a kind of heat engine antifatigue corrosion-resisting body, solve existing heat engine fuselage fatigue corrosion crack takes place easily, working life weak point, poor reliability, technical problem that difficulty of processing is big.
The objective of the invention is to solve by following technological scheme:
A kind of heat engine antifatigue corrosion-resisting body, its material are the two phase stainless steel that ferrite and austenite respectively account for half in the Solid Solution Microstructure; Earlier process the fuselage blank, carry out the solution treatment first time, carry out roughing again, carry out the solution treatment second time after the roughing, be finish-machined to finished product at last with forging method.
Above-mentioned heat engine antifatigue corrosion-resisting body, described fuselage material are that the trade mark is 00G18Ni5Mo3Si2, or 00Cr18Ni5Mo3Si2Nb, or 00Cr22Ni5Mo3N, or the two phase stainless steel of 00Cr25Ni6Mo2N.
Above-mentioned heat engine antifatigue corrosion-resisting body, solid solution treatment process is for the second time, slowly heats by the time of 2h～4h earlier, makes temperature reach 1000 ℃～1200 ℃, and insulation 2h～4h, cools off with the oil cooling method again.
Above-mentioned heat engine antifatigue corrosion-resisting body, when carrying out fine finishing, fuselage water channel surface roughness is Ra3.2～6.3, the thread surface roughness that is connected with heater is Ra1.6～Ra3.2.
Above-mentioned heat engine antifatigue corrosion-resisting body, this fuselage employing whole machining mode on the basis of forging blank is made.
Heat engine of the present invention antifatigue corrosion-resisting body, material adopts ferrite and austenite in the Solid Solution Microstructure respectively to account for the two phase stainless steel of half first, whole machining forms on the basis of forging blank, and after roughing, carry out Secondary Solid Solution Treatment, efficiently solve the problem of a solid solution interior tissue composition inequality, obtained significant effect.Beneficial effect of the present invention is as follows:
1, significantly improve the corrosion-resistant and anti-fatigue performance of fuselage under high alternating stress, joined the durable certification test of machine through 2000 hours, respond well.
2, this invention not only can be applied on the heat engine fuselage, can also be applied in other work component of heat engine, and tired connection part in other corrosion working environment.
Description of drawings
Fig. 1 is the structural representation of fuselage of the present invention.
Embodiment
As shown in the figure, construction profile figure for four cylinder double-action heat engine fuselages commonly used, position therebetween, be square and be furnished with four heat engine mounting hole of cylinder sleeve, the heat engine cylinder sleeve, cooler is arranged in this hole, in the fuselage side, is furnished with four cooling water holes, two advance scene 2, external water-cooling tube, the fuselage lower end links to each other with the heat engine crankcase, and the upper end links to each other with the heat engine heater, generally, the Connecting format of fuselage and heater is for being threaded, and screw thread is of a size of M140～M170, and difficulty of processing is big, require height, this place is the key position that influences fuselage life-span and reliability.
Above-mentioned fuselage, its material are ferrite and the about two phase stainless steel that respectively accounts for half of austenite in the solid solution structure, and its technology is as follows:
A) process heat engine fuselage blank with the solid forging method earlier, and carry out the solution treatment first time;
B) carry out roughing by drawing, comprise processing cylinder trepanning, heat engine cooling water hole etc.;
C) after the fuselage roughing, carry out the solution treatment second time, its process parameter is: by the slow heating of 2h～4h, make temperature reach 1000 ℃～1200 ℃ earlier, be incubated 2h～4h again, cool off with the oil cooling method at last;
D) carry out fine finishing by drawing at last, the cooling water channel surface roughness is Ra3.2～6.3, and the thread surface roughness that is connected with heater is Ra1.6～Ra3.2.
The trade mark of above-mentioned fuselage two phase stainless steel can be 00G18Ni5Mo3Si2, or 00Cr18Ni5Mo3Si2Nb, or 00Cr22Ni5Mo3N, or material such as 00Cr25Ni6Mo2N.It adopts the method for solid forging to process blank, and mach again method processes, and has adopted the technology of twice solution treatment.After the solution treatment first time finished, because fuselage mechanism complexity, the blahk structure size was big, wall unevenness, blank is heated inhomogeneous in heat treatment process, causes fuselage core structure and the branch that is organized into all around there are differences, and the fuselage interior constituent is inhomogeneous.For eliminating the problems referred to above, the present invention is after roughing, carried out solution treatment for the second time, improved the uniformity that makes the fuselage tissue, improved cutting ability greatly, improved the quality of processing of fuselage thread surface, avoided causing fatigue crack as tired source owing to processing tool marks and surperficial heterogeneous structure.
According to above-mentioned technology, the inventor processes the heat engine fuselage, carried out joining the machine test, after endurance test in 3000 hours examination, open and inspect discovery, heat engine fuselage, particularly heater connection part working surface flawless, no corrosion phenomenon, respond well, the operating life and the reliability of fuselage are significantly improved.
Above embodiment only is used to the present invention is described and unrestricted technological scheme described in the invention is not limited to above form, the replacement that can also make amendment or be equal to the present invention; Technological scheme and improvement thereof that all do not break away from the spirit and scope of the present invention all will fall into protection scope of the present invention.
Claims (7)
1. heat engine antifatigue corrosion-resisting body is characterized in that: its material is the two phase stainless steel that ferrite and austenite respectively account for half in the Solid Solution Microstructure; Earlier process the fuselage blank, carry out the solution treatment first time, carry out roughing again, carry out the solution treatment second time after the roughing, be finish-machined to finished product at last with forging method.
2. heat engine antifatigue corrosion-resisting body according to claim 1 is characterized in that: described fuselage material is that the trade mark is 00G18Ni5Mo3Si2, or 00Cr18Ni5Mo3Si2Nb, or 00Cr22Ni5Mo3N, or the two phase stainless steel of 00Cr25Ni6Mo2N.
3. heat engine antifatigue corrosion-resisting body according to claim 1 and 2, it is characterized in that: solid solution treatment process is for the second time, slowly heats by the time of 2h～4h earlier, makes temperature reach 1000 ℃～1200 ℃, and insulation 2h～4h, cool off with the oil cooling method again.
4. heat engine antifatigue corrosion-resisting body according to claim 1 and 2 is characterized in that: when carrying out fine finishing, fuselage water channel surface roughness is Ra3.2～6.3, and the thread surface roughness that is connected with heater is Ra1.6～Ra3.2.
5. heat engine antifatigue corrosion-resisting body according to claim 3 is characterized in that: when carrying out fine finishing, fuselage water channel surface roughness is Ra3.2～6.3, and the thread surface roughness that is connected with heater is Ra1.6～Ra3.2.
6. heat engine antifatigue corrosion-resisting body according to claim 1 and 2 is characterized in that: this fuselage employing whole machining mode on the basis of forging blank is made.
7. heat engine antifatigue corrosion-resisting body according to claim 3 is characterized in that: this fuselage employing whole machining mode on the basis of forging blank is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN200910201749A CN101701555A (en) | 2009-11-04 | 2009-11-04 | Anti-fatigue corrosion-resisting body for hot air engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN200910201749A CN101701555A (en) | 2009-11-04 | 2009-11-04 | Anti-fatigue corrosion-resisting body for hot air engine |
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| CN101701555A true CN101701555A (en) | 2010-05-05 |
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Citations (9)
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| CN85106667B (en) * | 1985-09-06 | 1986-10-22 | 冶金工业部钢铁研究总院 | Two-phase ultrahigh-strength aging stainless steel |
| JPH1180901A (en) * | 1986-04-28 | 1999-03-26 | Nkk Corp | Duplex stainless steel excellent in pitting corrosion resistance |
| US6277215B1 (en) * | 1998-10-05 | 2001-08-21 | Sumitomo Metal Industries, Ltd. | Stainless steel fur gaskets |
| CN1558102A (en) * | 2004-01-16 | 2004-12-29 | 上海齐耀动力技术有限公司 | Super corrosion resistant cylinder jacket used for engine |
| CN100999806A (en) * | 2006-12-31 | 2007-07-18 | 许季祥 | High performance corrosion-proof rare earth super strength dual-phase stainless steel and its smelting tech. |
| CN101117689A (en) * | 2007-08-20 | 2008-02-06 | 江阴市江东不锈钢制造有限公司 | 03Cr22Ni4NbN austenite-ferritic stainless steel and production technology therefor |
| CN101205592A (en) * | 2006-12-19 | 2008-06-25 | 中国科学院金属研究所 | Martensitic antibiotic stainless steel and thermal treatment method thereof |
| CN101216001A (en) * | 2007-01-04 | 2008-07-09 | 上海齐耀动力技术有限公司 | Small-sized hot air engine |
| CN101555568A (en) * | 2008-04-08 | 2009-10-14 | 江苏神通阀门股份有限公司 | Two-phase stainless steel |
-
2009
- 2009-11-04 CN CN200910201749A patent/CN101701555A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85106667B (en) * | 1985-09-06 | 1986-10-22 | 冶金工业部钢铁研究总院 | Two-phase ultrahigh-strength aging stainless steel |
| JPH1180901A (en) * | 1986-04-28 | 1999-03-26 | Nkk Corp | Duplex stainless steel excellent in pitting corrosion resistance |
| US6277215B1 (en) * | 1998-10-05 | 2001-08-21 | Sumitomo Metal Industries, Ltd. | Stainless steel fur gaskets |
| CN1558102A (en) * | 2004-01-16 | 2004-12-29 | 上海齐耀动力技术有限公司 | Super corrosion resistant cylinder jacket used for engine |
| CN101205592A (en) * | 2006-12-19 | 2008-06-25 | 中国科学院金属研究所 | Martensitic antibiotic stainless steel and thermal treatment method thereof |
| CN100999806A (en) * | 2006-12-31 | 2007-07-18 | 许季祥 | High performance corrosion-proof rare earth super strength dual-phase stainless steel and its smelting tech. |
| CN101216001A (en) * | 2007-01-04 | 2008-07-09 | 上海齐耀动力技术有限公司 | Small-sized hot air engine |
| CN101117689A (en) * | 2007-08-20 | 2008-02-06 | 江阴市江东不锈钢制造有限公司 | 03Cr22Ni4NbN austenite-ferritic stainless steel and production technology therefor |
| CN101555568A (en) * | 2008-04-08 | 2009-10-14 | 江苏神通阀门股份有限公司 | Two-phase stainless steel |
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Application publication date: 20100505 |