Preparation method of high temperature resistant Cu-Cr-Nb-Ce alloy for combustion chamber lining of aero-engine

A cu-cr-nb-ce, aero-engine technology, applied in the manufacturing field of aero-engine combustion chamber lining materials, can solve the problems of loss of strengthening effect, second phase coarsening, etc., and achieve no reduction in mechanical properties, low cycle Excellent fatigue performance and thermal conductivity, good ductility effect

Active Publication Date: 2019-09-10
SHAANXI SIRUI ADVANCED MATERIALS CO LTD
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

On the contrary, most copper alloys, such as Cu-Cr and Cu-Ag-Zr alloys, at the same temperature, the second

Method used

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  • Preparation method of high temperature resistant Cu-Cr-Nb-Ce alloy for combustion chamber lining of aero-engine
  • Preparation method of high temperature resistant Cu-Cr-Nb-Ce alloy for combustion chamber lining of aero-engine
  • Preparation method of high temperature resistant Cu-Cr-Nb-Ce alloy for combustion chamber lining of aero-engine

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Experimental program
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Embodiment 1

[0034] Such as figure 1 , 2 Shown, a kind of preparation method of high-temperature resistant Cu-Cr-Nb-Ce alloy for aero-engine combustor lining mainly comprises the following steps:

[0035] (1) Ingredients: The chemical composition and weight percentage of Cu-Cr-Nb-Ce alloy are: 6.45% Cr, 5.3% Nb, 0.05% Ce, 0.004% Fe, 0.004% Al, 0.003% C, 0.05% O, 0.001% N, the balance is copper, among which, Cu is added by electrolytic copper plate, Cr is added by CuCr10 master alloy, and Nb is added by pure Nb block;

[0036] (2) Vacuum induction smelting: the electrolytic copper plate of above-mentioned percentage by weight is packed in the vacuum induction furnace, vacuumizes, and after the electrolytic copper plate is melted, then respectively add CuCr10 master alloy and the Nb block that purity is 99.9% in the vacuum induction furnace, Heating up to 1600°C for smelting, finally adding rare earth Ce, feeding argon with a concentration of 99.999% for protection, and keeping it for 10 m...

Embodiment 2

[0041] Such as image 3 , 4 Shown, a kind of preparation method of high-temperature resistant Cu-Cr-Nb-Ce alloy for aero-engine combustor lining mainly comprises the following steps:

[0042] (1) Ingredients: The chemical composition and weight percentage of Cu-Cr-Nb-Ce alloy are: 6.65% Cr, 5.85% Nb, 0.065% Ce, 0.003% Fe, 0.003% Al, 0.002% C, 0.04% O, 0.001% N, the balance is copper, among which, Cu is added by electrolytic copper plate, Cr is added by CuCr10 master alloy, and Nb is added by pure Nb block;

[0043] (2) Vacuum induction smelting: the electrolytic copper plate of above-mentioned percentage by weight is packed in the vacuum induction furnace, vacuumizes, and after the electrolytic copper plate is melted, then respectively add CuCr10 master alloy and the Nb block that purity is 99.9% in the vacuum induction furnace, Heating up to 1600°C for smelting, finally adding rare earth Ce, feeding argon with a concentration of 99.999% for protection, and keeping it for 20...

Embodiment 3

[0048] Such as Figure 5 , 6 Shown, a kind of preparation method of high-temperature resistant Cu-Cr-Nb-Ce alloy for aero-engine combustor lining mainly comprises the following steps:

[0049] (1) Ingredients: The chemical composition and weight percentage of Cu-Cr-Nb-Ce alloy are: 7.4% Cr, 6.6% Nb, 0.065% Ce, 0.002% Fe, 0.002% Al, 0.001% C, 0.03% O, 0.001% N, the balance is copper, among which, Cu is added by electrolytic copper plate, Cr is added by CuCr10 master alloy, and Nb is added by pure Nb block;

[0050] (2) Vacuum induction smelting: the electrolytic copper plate of above-mentioned percentage by weight is packed in the vacuum induction furnace, vacuumizes, and after the electrolytic copper plate is melted, then respectively add CuCr10 master alloy and the Nb block that purity is 99.9% in the vacuum induction furnace, Heating up to 1600°C for smelting, finally adding rare earth Ce, feeding argon gas with a concentration of 99.999% for protection, and keeping the te...

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Abstract

The invention discloses a preparation method of high temperature resistant Cu-Cr-Nb-Ce alloy for the combustion chamber lining of an aero-engine and belongs to the technical field of manufacture of the combustion chamber lining material of the aero-engine. The preparation method mainly comprises the following steps: 1, preparing and proportioning materials; 2, carrying out vacuum induction melting; 3, casting; 4 carrying out electrode induction gas atomization; and 5, carrying out powder canning hot extrusion. The Cu-Cr-Nb-Ce alloy has higher high temperature resistant strength and excellent ductility, Cr and Nb in the alloy can form LAVES (Cr2Nb) phase, and the LAVES (Cr2Nb) phase is still stable when the temperature is higher than 1600 DEG C, so that the Cu-Cr-Nb-Ce alloy is dispersion strengthening copper alloy of plenty of Cr2Nb hardening phases; the Cr2Nb hardening phases can refine and control the grain size of copper to further improve the strength of copper alloy; in addition,the Cr2Nb hardening phases can prevent the phenomenon that the crystal particle is thick and large or the grain boundary is oxidized or melts when the material is at the high temperature, so that fatigue, and ablation, crack and fracture failure of a hot end part are avoided when the material is at the high temperature; and the Cu-Cr-Nb-Ce alloy is an extremely attractive material used at the hightemperature environment.

Description

technical field [0001] The invention belongs to the technical field of manufacturing lining materials of aero-engine combustion chambers, and in particular relates to a method for preparing a high-temperature-resistant Cu-Cr-Nb-Ce alloy for aero-engine combustion chamber linings. Background technique [0002] Liquid hydrogen and liquid oxygen engines are being widely used as the power of launch vehicles. The inner wall of the combustion chamber of this liquid rocket engine is subjected to high temperature, high pressure, and high-speed air flow, and is subjected to high thermal stress caused by pressure loads and temperature gradients on both sides of the inner wall. Copper alloys and copper-based composites are attractive for lining rocket engine components because they have higher thermal conductivity than other engineering materials. [0003] The engine combustion chamber is the core component to ensure the normal operation of the rocket, and the working conditions are v...

Claims

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Application Information

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IPC IPC(8): C22C9/00C22C1/04B22F9/08B22F3/04B22F3/15B22F3/20
CPCB22F3/04B22F3/15B22F3/20B22F9/082B22F2003/208B22F2009/0848C22C1/0425C22C9/00
Inventor 马明月庾高峰张航武旭红吴斌李小阳王文斌
Owner SHAANXI SIRUI ADVANCED MATERIALS CO LTD
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