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A Forging Process of Aviation Compressor Blade Based on Nickel-based Superalloy

A nickel-based high-temperature alloy and compressor technology, applied in metal processing equipment, mechanical equipment, engine components, etc., can solve problems such as processing difficulties, destroying the continuity of metal streamlines, the surface integrity of finished blades, and reducing the mechanical properties of finished blades , to achieve less machining allowance, improve product qualification rate and consistency, and achieve good consistency

Active Publication Date: 2020-10-16
无锡航亚科技股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The existing nickel-based superalloy blade forging process is a common die forging process, which requires machining to remove the machining allowance on the airfoil profile, which is not only difficult to process, but also destroys the continuity of the metal streamline and the surface of the finished blade Integrity, the technical problem of reducing the mechanical properties of finished blades, the present invention provides a forging process for aviation compressor blades based on nickel-based superalloys, which can realize the precision forging of nickel-based superalloy blades, and make the blade forgings The size of the airfoil directly reaches the size of the finished product, no further machining is required, the continuity of the metal streamline is retained, the mechanical properties are improved, and the surface integrity and metallographic structure meet the design requirements

Method used

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  • A Forging Process of Aviation Compressor Blade Based on Nickel-based Superalloy
  • A Forging Process of Aviation Compressor Blade Based on Nickel-based Superalloy
  • A Forging Process of Aviation Compressor Blade Based on Nickel-based Superalloy

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Experimental program
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Effect test

Embodiment 1

[0091] Taking the continuous production of 200 forgings of the tenth stage rotor blades of an aero-engine compressor in China as an example, the lathe blanking equipment used is an ordinary CNC lathe, the glass lubricant used is a water-based lubricant, and the molding equipment used for extrusion is a 400-ton hydraulic press , The molding equipment used for pre-forging and final forging is a 1000-ton screw press, and the forging heating converter used meets the industry's Class 3 furnace, and the furnace temperature accuracy is ±10°C. Continuously produce 200 pieces of rotor blade forgings, the forging cycle is 1 piece per minute, after passing the first piece confirmation and 3 consecutive pieces of qualified approval, 1 piece will be randomly inspected for every 50 pieces in the process.

[0092] The forging process of the aviation compressor blade based on nickel-based superalloy of the present invention, it comprises the following steps:

[0093] Step 1, blanking, use CNC...

Embodiment 2

[0130] Taking the continuous production of 200 forgings of the tenth stage rotor blades of an aero-engine compressor in China as an example, the lathe blanking equipment used is an ordinary CNC lathe, the glass lubricant used is a water-based lubricant, and the molding equipment used for extrusion is a 400-ton hydraulic press , The molding equipment used for pre-forging and final forging is a 1000-ton screw press, and the forging heating converter used meets the industry's Class 3 furnace, and the furnace temperature accuracy is ±10°C. Continuously produce 200 pieces of rotor blade forgings, the forging cycle is 1 piece per minute, after passing the first piece confirmation and 3 consecutive pieces of qualified approval, 1 piece will be randomly inspected for every 50 pieces in the process.

[0131] The forging process of the aviation compressor blade based on nickel-based superalloy of the present invention, it comprises the following steps:

[0132] Step 1, blanking, use CNC...

Embodiment 3

[0169] Taking the continuous production of 200 forgings of the tenth stage rotor blades of an aero-engine compressor in China as an example, the lathe blanking equipment used is an ordinary CNC lathe, the glass lubricant used is a water-based lubricant, and the molding equipment used for extrusion is a 400-ton hydraulic press , The molding equipment used for pre-forging and final forging is a 1000-ton screw press, and the forging heating converter used meets the industry's Class 3 furnace, and the furnace temperature accuracy is ±10°C. Continuously produce 200 pieces of rotor blade forgings, the forging cycle is 1 piece per minute, after passing the first piece confirmation and 3 consecutive pieces of qualified approval, 1 piece will be randomly inspected for every 50 pieces in the process.

[0170] The forging process of the aviation compressor blade based on nickel-based superalloy of the present invention, it comprises the following steps:

[0171] Step 1, blanking, use CNC...

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Abstract

The invention provides a forging technology of a nickel-based superalloy based aviation compressor blade. The forging technology of the nickel-based superalloy based aviation compressor blade solves the problems that an existing forging technology of the nickel-based superalloy blade is a common die forging technology, machining allowance on a blade body profile can only be removed by machining, the machining is difficult, the continuity of a metal flow line and the surface integrity of a finished blade are damaged, and mechanical properties of the finished blade are reduced. The method comprises the steps of feeding, surface cleaning, glass lubricant spraying, bar heating, extruding, surface cleaning, glass lubricant dip coating, pre-forging heating, pre-forging, surface cleaning, edge cutting, glass lubricant spraying, final forging heating, final forging, surface cleaning, edge cutting, vibration finishing, solid solution treatment, twist correction, acid corrosion, aging treatment,vibration finishing and final inspection.

Description

technical field [0001] The invention relates to the field of blade forging processing, in particular to a forging process of an aviation compressor blade based on a nickel-based superalloy. Background technique [0002] In order to meet the requirements of high performance, high safety, high reliability and long life of the engine, the high-pressure rotor blades of aviation compressors must have excellent metallurgical properties, precise dimensions, and excellent surface integrity. Therefore, the manufacturing technology of compressor blades belongs to the manufacturing One of the most complex technologies in the industry. [0003] Compressor high-pressure rotor blades are mostly made of nickel-based superalloy (Inconel718), which is a nickel-based superalloy material that is precipitated and strengthened by body-centered square γ" and face-centered cubic γ' phases. It has good comprehensive performance in the temperature range of ℃, and the yield strength below 650 ℃ rank...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21K3/04B21J5/00B21J3/00
CPCB21J3/00B21J5/002B21K3/04
Inventor 赵晓忠丁立周敏卞喜明
Owner 无锡航亚科技股份有限公司
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