Preparation method of self-heat-dissipation high-temperature alloy blade

Abstract

The invention relates to a preparation method of a self-heat-dissipation high-temperature alloy blade, which is characterized in that a copper-magnesium-steel composite component is preset in the high-temperature alloy blade, and in the presence of the component, the use temperature of the high-temperature alloy blade can be increased by about 15% on the original basis; the high-temperature alloy blade adopting the structure can work normally for a long time under the working condition of extreme high temperature; the copper-magnesium-steel composite component is compounded through two steps, in the first step, low-temperature small deformation is assisted through electric pulses, magnesium is melted and combined with copper and steel interfaces, meanwhile, steel and copper are recrystallized, and crystal grains are refined, in the second step, high-temperature large deformation is achieved through a heat source, and in the process, the copper and the steel are subjected to large plastic deformation through large plastic deformation, so that the copper-magnesium-steel composite component is formed. And the interface bonding is tighter, so that the copper-magnesium-steel composite component is obtained.

Description

Technical Field

[0001] The invention discloses a method for preparing a self-heat dissipating high-temperature alloy blade, and belongs to the technical field of thermal processing. Background Art

[0002] Foreign researchers have been working on copper and steel functional gradient materials and exploring their mechanical properties. This material combines the unique properties of copper and steel - steel's heat resistance and copper's thermal conductivity. In the future, it is expected to be used to manufacture combustion chamber components for aircraft and rocket engines, effectively preventing engine overheating damage.

[0003] High-temperature alloy turbine blades are key components of aircraft engines. Both domestic and foreign countries have been looking to increase their operating temperature, mainly through the continuous development of new materials, but this often results in a long development cycle and low economic benefits. Summary of the invention

[0004] The present invention is designed precisely in view of the above-mentioned existing technical conditions and provides a method for preparing a self-heating high-temperature alloy blade. Its purpose is to pre-install a copper-magnesium-steel composite component inside the high-temperature alloy blade. The component can increase the operating temperature of the high-temperature alloy blade when present, so that the high-temperature alloy blade adopting this structure can maintain normal operation for a long time under extremely high temperature conditions.

[0005] To achieve the above purpose, the technical solution of the present invention is as follows:

[0006] The steps of the method for preparing the self-heat dissipating high-temperature alloy blade proposed by the present invention are as follows:

[0007] Step 1: Use a mechanical processing method to process parallel grooves on the surfaces of two high-temperature alloy plates of the same specifications and sizes. The positions of the grooves on the surfaces of the two high-temperature alloy plates correspond to each other. The grooves run through the entire surface of the high-temperature alloy plate to the edge. The width of the groove is 1 / 10 of the width of the high-temperature alloy plate, and the depth of the groove is 1 / 10 of the thickness of the high-temperature alloy plate. After the processing is completed, the surfaces of the two high-temperature alloy plates and the groove surfaces are fully cleaned with gasoline, acetone and alcohol;

[0008] Step 2: Magnesium foil is laid on the surfaces of the two high-temperature alloy plates and the grooves, and then a copper rod is placed in the groove of one of the high-temperature alloy plates. The length and width of the copper rod are consistent with the groove and form a transition fit. The height of the copper rod is 2.5 to 3 times the depth of the groove. Then, the other high-temperature alloy plate is buckled and docked together, so that the copper rod is placed in the cavity formed by the corresponding grooves on the upper and lower sides of the two high-temperature alloy plates to form a steel-copper composite plate;

[0009] Step 3, placing the steel-copper composite plate in a vacuum chamber and heating it, clamping a pulse power generator between the opposite edges of the high-temperature alloy plates, setting pressure heads on the upper and lower surfaces of the steel-copper composite plate, and applying opposite compressive stresses to the upper and lower surfaces of the steel-copper composite plate while the steel-copper composite plate is energized. The above-mentioned energization process is 10-15 minutes, the heating temperature of the steel-copper composite plate is 500-700°C, and the compressive stress is 300-700MPa. During this process, the magnesium foil melts, the copper rod undergoes plastic deformation, and the distance between the upper and lower high-temperature alloy plates on the steel-copper composite plate is reduced by 50% compared with before the pressure is applied;

[0010] Step 4: Place the steel-copper composite plate obtained after the processing in step 3 in a resistance furnace for heating at a temperature of 700-1000° C. for 30-40 min, and then place it in a rolling mill for rolling at a reduction of 5-10% per pass until the distance between the two high-temperature alloy plates of the steel-copper composite plate is closed to obtain a copper-magnesium-steel composite component;

[0011] Step 5: Place the copper-magnesium-steel composite component obtained after the processing in step 4 at the center of a cylindrical stainless steel sheath, the height of the inner cavity of the sheath is twice the length of the copper-magnesium-steel composite component in this direction, fill the gap between the copper-magnesium-steel composite component and the inner wall of the sheath with high-temperature alloy powder, then seal and evacuate the sheath, heat the sheath to 1000-1050°C, keep it warm for 1 hour, and then use a hydraulic press to perform direct forging in an atmospheric environment to obtain a blade blank with a core of the copper-magnesium-steel composite component;

[0012] Step six: machining the blade blank to finally obtain a high-temperature alloy blade.

[0013] During implementation, the material grade of the high temperature alloy plate in step 1 is 4340. Furthermore, the high temperature alloy plate has a length of 70-100 mm, a width of 30-50 mm, and a thickness of 7-10 mm.

[0014] During implementation, the thickness of the magnesium foil in step 2 is 0.1 mm.

[0015] The characteristics and beneficial effects of the technical solution of the present invention are as follows:

[0016] 1. The technical solution of the present invention pre-installs a copper-magnesium-steel composite component inside the high-temperature alloy blade. The component can increase the use temperature of the high-temperature alloy blade by about 15% on the original basis, so that the high-temperature alloy blade adopting this structure can maintain normal operation for a long time under extreme high-temperature conditions; In the solution of the present invention, the copper-magnesium-steel composite component is compounded in two steps. The first step is to melt magnesium and combine with the copper and steel interface through low-temperature small deformation assisted by electric pulses, and at the same time, the steel and copper are recrystallized to refine the grains. The second step is to perform large high-temperature deformation through heat source. In this process, copper and steel are more tightly combined at the interface with the help of large plastic deformation, thereby obtaining a copper-magnesium-steel composite component;

[0017] Second, when preparing the blade blank, the present invention directly places the copper-magnesium-steel composite component into the powder high-temperature alloy and performs a direct one-pass forging. Since it is performed in an atmospheric environment, the organization does not have time to fully grow and refine the organization;

[0018] 3. The scheme of the present invention uses a plastic forming method, with the help of electric field, temperature field and strain field, to achieve compounding of four metals, namely copper, steel, magnesium and high-temperature alloy, under the coordination of different energy fields. DETAILED DESCRIPTION

[0019] The technical solution of the present invention will be further described in detail below in conjunction with embodiments:

[0020] Example

[0021] The method for preparing a self-heating high-temperature alloy blade using the technical solution of the present invention has the following steps:

[0022] Step 1, prepare two high-temperature alloy plates of the same specification and size, the material grade of which is 4340, the length of the high-temperature alloy plates is 70-100mm, the width is 30-50mm, and the thickness is 7-10mm. Use a mechanical processing method to process grooves parallel to the long sides on the surfaces of the two high-temperature alloy plates. The number of grooves is 2-8. The positions of the grooves on the surfaces of the two high-temperature alloy plates correspond to each other. The grooves run through the entire surface of the high-temperature alloy plate to the edge. The width of the groove is 1 / 10 of the width of the high-temperature alloy plate, and the depth of the groove is 1 / 10 of the thickness of the high-temperature alloy plate. After the processing is completed, the surfaces of the two high-temperature alloy plates and the groove surfaces are fully cleaned with gasoline, acetone and alcohol;

[0023] Step 2: paving magnesium foil with a thickness of 0.1 mm on the surfaces of the two high-temperature alloy plates and the grooves, then placing a copper rod in the groove of one of the high-temperature alloy plates, the length and width of the copper rod being consistent with the groove and forming a transition fit, and the height of the copper rod being 3 times the depth of the groove, and then the other high-temperature alloy plate being inverted and butted together, so that the copper rod is placed in the cavity formed by the corresponding grooves on the upper and lower sides of the two high-temperature alloy plates, to form a steel-copper composite plate;

[0024] Step 3, placing the steel-copper composite plate in a vacuum chamber and heating it, clamping a pulse power generator between the opposite edges of the high-temperature alloy plates, setting pressure heads on the upper and lower surfaces of the steel-copper composite plate, and applying opposite compressive stresses to the upper and lower surfaces of the steel-copper composite plate while the steel-copper composite plate is energized. The above-mentioned energization process is 10-15 minutes, the heating temperature of the steel-copper composite plate is 500-700°C, and the compressive stress is 300-700MPa. During this process, the magnesium foil melts, the copper rod undergoes plastic deformation, and the distance between the upper and lower high-temperature alloy plates on the steel-copper composite plate is reduced by 50% compared with before the pressure is applied;

[0025] Step 4: Place the steel-copper composite plate obtained after the processing in step 3 in a resistance furnace for heating at a temperature of 700-1000° C. for 30-40 min, and then place it in a rolling mill for rolling at a reduction of 5-10% per pass until the distance between the two high-temperature alloy plates of the steel-copper composite plate is closed to obtain a copper-magnesium-steel composite component;

[0026] Step 5: Place the copper-magnesium-steel composite component obtained after the processing in step 4 at the center of a cylindrical stainless steel sheath, the long side direction of the copper-magnesium-steel composite component is parallel to the central axis of the sheath, and the height of the inner cavity of the sheath is twice the length of the copper-magnesium-steel composite component in this direction, fill the gap between the copper-magnesium-steel composite component and the inner wall of the sheath with high-temperature alloy powder, then seal and evacuate the sheath, heat the sheath to 1000-1050° C., keep it warm for 1 hour, and then use a hydraulic press to perform direct forging in an atmospheric environment to obtain a blade blank with a core of the copper-magnesium-steel composite component;

[0027] Step six: machining the blade blank to finally obtain a high-temperature alloy blade.

Claims

1. A method for preparing a self-heat dissipating high temperature alloy blade, characterized in that: The steps of the preparation method are as follows: Step 1: Use a mechanical processing method to process parallel grooves on the surfaces of two high-temperature alloy plates of the same specifications and sizes. The positions of the grooves on the surfaces of the two high-temperature alloy plates correspond to each other. The grooves run through the entire surface of the high-temperature alloy plate to the edge. The width of the groove is 1 / 10 of the width of the high-temperature alloy plate, and the depth of the groove is 1 / 10 of the thickness of the high-temperature alloy plate. After the processing is completed, the surfaces of the two high-temperature alloy plates and the groove surfaces are fully cleaned with gasoline, acetone and alcohol; Step 2: Magnesium foil is laid on the surfaces of the two high-temperature alloy plates and the grooves, and then a copper rod is placed in the groove of one of the high-temperature alloy plates. The length and width of the copper rod are consistent with the groove and form a transition fit. The height of the copper rod is 2.5 to 3 times the depth of the groove. Then, the other high-temperature alloy plate is buckled and docked together, so that the copper rod is placed in the cavity formed by the corresponding grooves on the upper and lower sides of the two high-temperature alloy plates to form a steel-copper composite plate; Step 3, placing the steel-copper composite plate in a vacuum chamber and heating it, clamping a pulse power generator between the opposite edges of the high-temperature alloy plates, setting pressure heads on the upper and lower surfaces of the steel-copper composite plate, and applying opposite compressive stresses to the upper and lower surfaces of the steel-copper composite plate while the steel-copper composite plate is energized. The above-mentioned energization process is 10-15 minutes, the heating temperature of the steel-copper composite plate is 500-700°C, and the compressive stress is 300-700MPa. During this process, the magnesium foil melts, the copper rod undergoes plastic deformation, and the distance between the upper and lower high-temperature alloy plates on the steel-copper composite plate is reduced by 50% compared with before the pressure is applied; Step 4: Place the steel-copper composite plate obtained after the processing in step 3 in a resistance furnace for heating at a temperature of 700-1000° C. for 30-40 min, and then place it in a rolling mill for rolling at a reduction of 5-10% per pass until the distance between the two high-temperature alloy plates of the steel-copper composite plate is closed to obtain a copper-magnesium-steel composite component; Step 5: Place the copper-magnesium-steel composite component obtained after the processing in step 4 at the center of a cylindrical stainless steel sheath, the height of the inner cavity of the sheath is twice the length of the copper-magnesium-steel composite component in this direction, fill the gap between the copper-magnesium-steel composite component and the inner wall of the sheath with high-temperature alloy powder, then seal and evacuate the sheath, heat the sheath to 1000-1050°C, keep it warm for 1 hour, and then use a hydraulic press to perform direct forging in an atmospheric environment to obtain a blade blank with a core of the copper-magnesium-steel composite component; Step six: machining the blade blank to finally obtain a high-temperature alloy blade.

2. The method for preparing a self-heat dissipating high temperature alloy blade according to claim 1, characterized in that: The material grade of the high temperature alloy plate described in step 1 is 4340.

3. The method for preparing the self-heat dissipating high temperature alloy blade according to claim 2, characterized in that: The high temperature alloy plate described in step 1 has a length of 70-100 mm, a width of 30-50 mm, and a thickness of 7-10 mm.

4. The method for preparing a self-heat dissipating high temperature alloy blade according to claim 1, characterized in that: The thickness of the magnesium foil in step 2 is 0.1 mm.