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High-temperature alloy turbine disc coating and manufacturing method thereof

A high-temperature alloy and manufacturing method technology, which is applied in the direction of metal material coating process, coating, fusion spraying, etc., can solve the problems of easy peeling of ceramic coatings, few inspections of mechanical properties, easy peeling of heterogeneous particles, etc., to achieve Meet the effects of mechanical properties, grain refinement, and avoid coating peeling

Inactive Publication Date: 2021-07-23
NANJING JIANGDONG IND & TRADE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to enhance the mechanical properties of existing turbine discs, ceramic coatings with good mechanical properties are often coated on the surface, but the existing ceramic coatings are generally Al 2 o 3 , Al 2 o 3 It is a large heterogeneous particle, which is easy to peel off, especially the ceramic coating is easy to peel off during the high-speed rotating friction of the turbine disk
Moreover, the existing turbine disks generally examine their mechanical properties in high-temperature environments, and seldom examine their mechanical properties in low-temperature environments. However, during the high-altitude operation of aviation aircraft, the high-altitude environment temperature in winter is lower. For normal operation in a lower external environment, it is very necessary to design a high-temperature resistant superalloy turbine disk coating and its manufacturing method

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] A high-temperature alloy turbine disk coating, the composition and mass percentage are as follows: Cr: 10%, Al: 2%, Si: 1.5%, Fe: 5%, Ti: 1%, C: 0.5%, B: 4% , Zn: 1.2%, Mo: 1%, Sb: 0.2%, Co: 0.5%, Cu: 3%, and the balance is Ni.

[0029] A method for manufacturing a high-temperature alloy turbine disk coating, comprising the following steps:

[0030] Step 1: Melting in a vacuum melting furnace: After vacuuming, preheat the vacuum melting furnace at 550°C. After the preheating is complete, put Zn into the bottom of the vacuum melting furnace, then cover Ni on the Zn, and raise the temperature to 1100°C within 30 minutes ℃, after melting, raise the temperature to 1800℃ within 4 hours, then add Cr, Al, Si, Fe, Ti, C, B, Mo, Sb, Co and Cu. Stirring with argon; the stirring time is 2h; then use the medium frequency electromagnetic field to stir for 1h, and obtain the superalloy liquid after the stirring is completed;

[0031] Step 2: The vacuum melting furnace and the vacuu...

Embodiment 2

[0043]A high-temperature alloy turbine disk coating, the composition and mass percentage are as follows: Cr: 13%, Al: 4%, Si: 4%, Fe: 8%, Ti: 1.5%, C: 1%, B: 6% , Zn: 2%, Mo: 2%, Sb: 0.4%, Co: 0.8%, Cu: 5%, and the balance is Ni.

[0044] A method for manufacturing a high-temperature alloy turbine disk coating, comprising the following steps:

[0045] Step 1: Melting in a vacuum melting furnace: After vacuuming, preheat the vacuum melting furnace at 580°C. After the preheating is completed, put Zn into the bottom of the vacuum melting furnace, then cover Ni on the Zn, and raise the temperature to 1120°C within 30 minutes. After melting, raise the temperature to 2000°C within 4 hours, then add Cr, Al, Si, Fe, Ti, C, B, Mo, Sb, Co and Cu, and the vacuum melting furnace first adopts low-frequency electromagnetic external field stirring, and simultaneously blows argon to stir; Stirring time is 3h; then use intermediate frequency electromagnetic external field stirring for 5h, aft...

Embodiment 3

[0058] The difference between this embodiment and embodiment 1 is only:

[0059] A high-temperature alloy turbine disk coating, the composition and mass percentage are as follows: Cr: 11%, Al: 3%, Si: 3%, Fe: 7%, Ti: 1.2%, C: 0.8%, B: 5% , Zn: 1.5%, Mo: 1.5%, Sb: 0.3%, Co: 0.7%, Cu: 4%, and the balance is Ni.

[0060] The average elongation of the turbine disk prepared in this embodiment is 33%, the tensile strength is 524Mpa, and the hardness reaches 249HV. The impact absorption energy Akv2 of the turbine disk at -100°C is 56J, and the impact absorption energy Akv2 of the turbine disk at -40°C The average impact absorption energy Akv2 of the turbine disk at 100-700°C is 76J. The turbine disk of this embodiment was subjected to a friction and wear test. After the test, the wear marks of the turbine disk were smooth and the coating was intact.

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Abstract

The invention discloses a high-temperature alloy turbine disc coating which comprises the following components in percentage by mass: 10-13 percent of Cr, 2-4 percent of Al, 1.5-4 percent of Si, 5-8 percent of Fe, 1-1.5 percent of Ti, 0.5-1 percent of C, 4-6 percent of B, 1.2-2 percent of Zn, 1-2 percent of Mo, 0.2-0.4 percent of Sb, 0.5-0.8 percent of Co, 3-5 percent of Cu and the balance of Ni. The invention further discloses a manufacturing method of the high-temperature alloy turbine disc coating. The coating is uniform in structure, refined in grain, low in oxygen content, few in structure defects in the casting process, few in composition segregation in the structure, free of dendritic segregation, high in solid solubility, uniform in solid solution strengthening phase distribution and low in impurity content. And nano-scale multi-element ceramic reinforced phases are uniformly distributed in the coating to form a wear-resistant framework, so that the coating is prevented from being peeled off.

Description

technical field [0001] The invention relates to a high-temperature alloy turbine disc coating and a manufacturing method thereof, belonging to the technical field of metal materials. Background technique [0002] The turbine disk is a part of the aero-engine. The working conditions of the turbine disk are harsh, and it needs to work under different temperatures, loads, and environmental media (air, gas). Therefore, the design and manufacture of the turbine disk must meet the following properties: high strength, wear resistance High resistance, good heat resistance, strong corrosion resistance, good stability in high and low temperature environments (that is, good thermal crack resistance, and low temperature shock resistance), etc., so as to ensure its service life and safety during service. [0003] In order to enhance the mechanical properties of existing turbine discs, ceramic coatings with good mechanical properties are often coated on the surface, but the existing ceram...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/123C23C4/067C23C4/18C22C19/05
CPCC23C4/123C23C4/067C23C4/18C22C19/056
Inventor 徐春娟
Owner NANJING JIANGDONG IND & TRADE CO LTD
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