Forging forming method of fan shaft made of C250 maraging steel

A maraging steel, fan shaft technology, applied in the direction of engine components, mechanical equipment, etc., can solve the problems of unqualified structure and performance, adverse effects of forging structure and performance, etc., achieve uniform structure, eliminate work hardening process, performance high effect

Inactive Publication Date: 2013-10-16
GUIZHOU ANDA AVIATION FORGING
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Problems solved by technology

However, in the process of using this method to forge C250 maraging steel long shaft forgings such as fan shaft forgings, if the forging process parameters such as forging temperature, strain rate, etc. are not properly selected and matched, the forging will not be able to deform It is completely in the dynamic recrystallization area, which will have an adverse effect on the structure and properties of the forging, and even produce scrap due to unqualified structure and properties

Method used

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  • Forging forming method of fan shaft made of C250 maraging steel

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[0018] The main chemical element content (weight percentage) of C250 maraging steel (00Ni18Co8Mo5TiAl) is: C content ≤ 0.01%, Mn content ≤ 0.1%, Si content ≤ 0.1%, Ni content 17% ~ 19%, Mo content 4.6% ~ 5.2%, O content ≤ 0.002%, Al content 0.05% ~ 0.15%, Ti content 0.3% ~ 0.5%, Co content 7% ~ 8.5%, P content ≤ 0.008%, S content ≤ 0.005%, N content ≤ 0.002%, the balance is Fe.

[0019] The forging process steps of the steel fan shaft forging are as follows:

[0020] Such as figure 1 As shown, the C250 maraging steel bar 10 blanked according to the specification is heated to a forging temperature of 1000°C to 1060°C, and after upsetting and elongation, it is heated to the forging temperature and then manufactured in a forging die. Form pre-forged billet 20, then heat pre-forged billet 20 to the forging temperature of 1000°C-1020°C, and then place it in the forging die for 0.01s -1 ~0.001s -1 The strain rate of forging blank 20 is formed into fan shaft forging 30 with a cir...

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Abstract

The method discloses a forging forming method of a fan shaft made of C250 maraging steel, which is provided for obtaining a forging with a better structure and a better property. The method comprises processing steps as follows: a C250 maraging steel bar material which is subjected to blanking according to specification is heated to a forging temperature ranging from 1,000 DEG C to 1,060 DEG C, heated to the forming temperature again after upset and stretched, and prepared into a pre-forged blank in a forging die; the pre-forged blank is forged into a fan shaft forging at a strain rate of 0.01s<-1>-0.001s<-1> in the forging die after heated to a forging temperature ranging from 1,000 DEG C to 1,020 DEG C; and the fan shaft forging is subjected to solid solution and aging heat treatment after forged, the solid solution is that the fan shaft forging is heated to 820 DEG C and is subjected to air cooling after heat insulation, and the aging is that the fan shaft forging is heated to 480 DEG C and is subjected to air cooling after heat insulation. The forging is mainly used for being prepared into a fan shaft part of an aero-engine.

Description

technical field [0001] The invention relates to a forging forming method of a shaft forging, in particular to a forging forming method of a C250 maraging steel fan shaft. Background technique [0002] C250 maraging steel is an ultra-high-strength steel formed by adding appropriate proportions of Co, Mo, Ti, Al and other elements based on carbon-free (or ultra-low carbon) iron-nickel martensite. Excellent toughness, hot and cold workability, no decarburization, small quenching deformation, etc., are widely used in ultra-high strength key components in aviation, aerospace and other fields. [0003] Chinese Invention Patent Specification CN 1435287A published on August 13, 2003 discloses an overall forging process for long-axis superalloy large forgings. By locally heating the billet and locally forming the locally heated billet through a combination die, the integral forging of long-axis superalloy large forgings is realized. However, in the process of using this method to f...

Claims

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Application Information

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IPC IPC(8): B21K1/06C21D8/00
Inventor 魏志坚王春旭葛金锋张衡赵飞杨志国苏海蒋礼萍
Owner GUIZHOU ANDA AVIATION FORGING
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