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Forging forming method of low-pressure turbine shaft made of C250 maraging steel

A technology of maraging steel and low-pressure turbine shaft, which is applied in the direction of engine components, mechanical equipment, etc., and can solve problems such as adverse effects on the structure and performance of forgings, unqualified structure and performance, etc.

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

However, in the process of forging C250 maraging steel long-shaft forgings such as low-pressure turbine shaft forgings using this method, if the forging process parameters such as forging temperature, strain rate, etc. are not properly selected and matched, the forging will be deformed during forming It cannot be 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

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  • Forging forming method of low-pressure turbine 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 low-pressure turbine 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 990°C to 1040°C, and after upsetting and elongation, it is heated to the forging temperature and then manufactured in a forging die. Form pre-forging billet 20, then heat pre-forging billet 20 to the forging temperature of 1020 ° C ~ 1060 ° C, and then place it in the forging die for 0.015s -1 ~0.0015s -1 The strain rate is to forge the blank 20 into a low-pres...

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Abstract

The method discloses a forging forming method of a low-pressure turbine 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 990 DEG C to 1,040 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 low-pressure turbine shaft forging at a strain rate of 0.015s<-1>-0.0015s<-1> in the forging die after heated to a forging temperature ranging from 1,020 DEG C to 1,060 DEG C; and the low-pressure turbine shaft forging is subjected to solid solution and aging heat treatment after forged, the solid solution is that the low-pressure turbine shaft forging is heated to 825 DEG C and is subjected to air cooling after heat insulation, and the aging is that the low-pressure turbine shaft forging is heated to 485 DEG C and is subjected to air cooling after heat insulation. The forging is mainly used for being prepared into a low-pressure turbine 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 low-pressure turbine 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 forgi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21K1/06C21D8/00
Inventor 邹伟谢永富占立水刘宪民葛金锋赵飞王龙祥杨国平
Owner GUIZHOU ANDA AVIATION FORGING
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