A deformed superalloy blade forging and precision forging method thereof

A technology for deforming high-temperature alloys and blades, which is applied in metal extrusion, metal processing equipment, metal extrusion control equipment, etc., can solve problems such as not being able to meet the temperature bearing capacity of blades, and achieve improved material utilization and complete shape , no folding and pulling effect

Active Publication Date: 2022-06-17
BEIJING CISRI GAONA TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The limit working temperature of the GH4169 alloy is 650°C, which cannot meet the requirements of the blade on the material's temperature bearing capacity.
At present, there is no report on the use of GH4169D alloy to manufacture aeroengine compressor blades

Method used

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  • A deformed superalloy blade forging and precision forging method thereof
  • A deformed superalloy blade forging and precision forging method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0063] A precision forging method for deformed superalloy blade forgings, comprising the following steps:

[0064] S1. Extrusion: Select the qualified nickel-based superalloy GH4169D alloy bar, and carry out surface treatment on the GH4169D alloy bar. Specifically, use 120-mesh steel sand medium for shot blasting process, and the shot blasting time is 15min. Bar surface cleaning;

[0065] Then put the GH4169D alloy bar into an oven, the heating temperature is 120°C, and the heating time is 60min, and then the bar is taken out from the oven and sprayed with glass lubricant to obtain a rod with a coating thickness of 0.09±0.01mm sprayed with glass lubricant material;

[0066] Then, the alloy bar is heated in a heating furnace, the heating temperature is 1060 ° C, and the temperature is kept for 15 minutes. Then, the alloy bar in the heating furnace is taken out of the heating furnace and transferred to a screw press within 17 seconds. Extrusion, cooling, extrusion ratio of 7; ...

Embodiment ２

[0079] A precision forging method for deformed superalloy blade forgings is carried out according to the method in Example 1, and the difference is:

[0080] S1. Extrusion: heat the bar in a heating furnace, the heating temperature is 950 ° C, and the temperature is kept for 60 minutes, and then the alloy bar in the heating furnace is taken out of the heating furnace and transferred to the screw press within 17 seconds for extrusion. Forming, the extrusion ratio is 2;

[0081] S2. Upsetting: return the extrusion to the furnace for heating, the heating temperature is 910°C, and the heating time is 60 minutes, and then the extrusion is quickly taken out from the heating furnace within 17 seconds, and the screw press hits the upsetting to obtain the upsetting, and cools;

[0082] S3. Pre-forging: return the upsetting parts to the furnace for heating, the heating temperature is 910°C, and the heating time is 60 minutes, and then the upsetting parts in the heating furnace are taken...

Embodiment ３

[0085] A deformed superalloy blade forging and its precision forging method are carried out according to the method in Embodiment 1, and the difference is:

[0086] S1. Extrusion: heat the bar in the heating furnace, the heating temperature is 1150 ℃, keep the temperature for 8 minutes, and then take out the alloy bar in the heating furnace from the heating furnace and transfer it to the screw press within 17 seconds for extrusion. Forming, the extrusion ratio is 12;

[0087] S2. Upsetting: return the extrusion to the furnace for heating, the heating temperature is 1060°C, and the heating time is 8 minutes, and then the extrusion is quickly taken out from the heating furnace within 17 seconds, and the screw press hits the upsetting to obtain the upsetting and cools;

[0088] S3. Pre-forging: return the upsetting parts to the furnace for heating, the heating temperature is 1060°C, and the heating time is 6 minutes, and then the upsetting parts in the heating furnace are taken o...

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Abstract

The invention discloses a deformed high-temperature alloy blade forging and a precision forging method thereof, comprising the following steps: S1, heat-preserve the high-temperature alloy bar at 950-1150°C for 8-60 minutes, and extrude; S2, heat the high-temperature alloy bar at 910-1060°C Heating for 8-60 minutes, heading; S3, heating at 910-1060°C for 6-60 minutes, pre-forging; S4, heating at 910-1060°C for 4-60 minutes, and final forging to obtain a final forging; the invention also discloses a Using the deformed superalloy blade forging obtained by the above precision forging method, the advantage of the present invention is to realize the precision forging of the blade forging based on the new nickel-based superalloy GH4169D material, and the obtained GH4169D alloy blade can meet the shape and size of the aeroengine blade and the temperature of 650 ° C. The performance requirements at a high temperature of ~750°C meet the requirements for the temperature bearing capacity of blade materials due to the continuous improvement of the performance and use requirements of aero-engines.

Description

technical field [0001] The invention relates to the technical field of engine blade forging, and more particularly, to a deformed superalloy blade forging and a precision forging method thereof. Background technique [0002] In order to meet the requirements of high performance, high safety, high reliability and long life of aero-engine, aero-engine blades must have excellent metallurgical properties, accurate dimensions, and excellent surface integrity. Therefore, the manufacturing technology of compressor blades belongs to the manufacturing industry. and one of its complex technologies. Nickel-based alloys refer to a class of alloys with comprehensive properties such as high strength and certain oxidation and corrosion resistance at high temperatures of 650-1000 °C. Nickel-based superalloys are widely used in the preparation of aero-engine parts. However, the nickel-based superalloy material also has another characteristic that its structure is particularly sensitive to t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21J5/00B21J5/02B21C29/00B21C31/00B21J1/06C22C19/05B05D7/14B05D3/02
CPCB21J5/002B21J5/02B21C29/003B21C31/00B21J1/06C22C19/055B05D7/14B05D3/0218
Inventor 王民庆杜金辉邓群刘辉朱勤天胡日吴玉博王知颖
Owner BEIJING CISRI GAONA TECH
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