Liquid rocket engine thrust chamber injector panel and preparation method thereof

Abstract

The invention discloses a liquid rocket engine thrust chamber injector panel and a preparation method thereof, and relates to the technical field of aerospace engine thrust chamber manufacturing. Comprising the following steps that raw materials are subjected to atmosphere protection induction melting, and a Cu-Cr-Zr-Nb alloy ingot blank is prepared; the cast ingot blank is forged for 60 min to 150 min at the temperature of 850 DEG C to 950 DEG C, the forging deformation per fire is controlled to be 30% to 50%, and a forged blank is obtained; after solution heat treatment is conducted on the forged blank, rough rolling is conducted at the temperature of 850-950 DEG C, and a rough rolling blank is obtained; after the rough rolling blank is annealed, intermediate rolling is conducted at the temperature of 850-950 DEG C, and a rolled blank is obtained; and after the rolled blank is cut into a circular blank of the injector panel, aging heat treatment is conducted, machining is conducted till the dimensional tolerance required by a product drawing is achieved, and the finished injector panel is obtained. The Cu-Cr-Zr-Nb material panel has high heat conductivity and high-temperature strength, and the problem of material ablation caused by poor heat conduction of an existing injector panel material is solved.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace engine thrust chamber manufacturing, and in particular to a liquid rocket engine thrust chamber injector panel and a preparation method thereof. Background Art

[0002] The thrust chamber of a liquid rocket engine is an important device of the engine. The thrust chamber is mainly composed of an igniter, an injector, and a combustion chamber. The injector is generally a three-bottom two-chamber structure. The panel is located at the bottom of the injector, which plays the role of fixing the nozzle and separating the injection chamber from the combustion chamber. The gas-liquid injection, atomization, evaporation and mixing process of the rocket engine thrust chamber injector is very fast, and the flame peak is very close to the injector panel. Therefore, during the operation, the injector panel is subjected to high-temperature combustion gas of up to 3000℃ on one side and low-temperature hydrogen of -170℃ on the other side. The panel is subjected to large temperature difference stress and is very easy to warp and deform, causing ablation damage. The working environment is very harsh, and corresponding heat dissipation and thermal protection measures must be adopted to prevent the panel from warping or ablation due to excessive cold and hot temperature difference stress. Porous sweating materials are often used to manufacture panels for liquid rocket engine injectors. They are both heat-resistant materials and structural materials. They belong to forced sweating type heat-resistant structural materials. Hydrogen sweating cooling is currently widely used, and the amount of hydrogen permeation is 3%-5% of the total hydrogen flow. Most models use porous panels made of wire mesh sintering and rolling. However, with the further increase in thrust level, the risk of unstable combustion increases accordingly. In addition to adopting relevant stabilization devices or stabilization measures, high-thrust engines have further improved the requirements for panel materials. The use of alloy panels with high thermal conductivity and moderate high-temperature strength can reduce temperature gradients and thermal stresses, and perforated sweating cooling can make the thermal protection effect better. The commonly used panel material is GH3030 panel (composition: C≤0.12%; Cr: 19.0%-22.0%; Ti: 0.15%-0.35%; Al≤0.15%; Fe≤1.5%; Mn≤0.7%; Si≤0.8%; P≤0.03%; S≤0.02%; Ni is the balance), and its thermal conductivity needs to be further improved, and it is easy to have material ablation problems caused by poor heat conduction. Based on this, the present application proposes a liquid rocket engine thrust chamber injector panel and a preparation method thereof. Summary of the invention

[0003] The main purpose of the present application is to provide a liquid rocket engine thrust chamber injector panel and a preparation method thereof, aiming to solve the technical problem that the thermal conductivity of the existing injector panel material needs to be improved.

[0004] To achieve the above-mentioned purpose, the present application proposes a method for preparing a liquid rocket engine thrust chamber injector panel, comprising the following steps:

[0005] The raw materials are subjected to atmosphere protection induction melting to prepare Cu-Cr-Zr-Nb alloy ingot blanks;

[0006] Forging the ingot blank at 850° C.-950° C. for 60 min-150 min, controlling the deformation amount of each forging to be 30%-50%, to obtain a forged blank;

[0007] After the forging blank is subjected to solution heat treatment, rough rolling is performed at 850°C-950°C to obtain a rough rolled blank; after the rough rolled blank is subjected to annealing, intermediate rolling is performed at 850°C-950°C to obtain a rolled blank;

[0008] After the rolled blank is cut into a circular blank of an injector panel, an aging heat treatment is performed, and then the blank is machined to the dimensional tolerance required by the product drawing to obtain a finished injector panel.

[0009] Optionally, in the step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank, the raw materials include electrolytic copper plate, chromium-niobium master alloy and zirconium sponge;

[0010] The content of niobium in the chromium-niobium master alloy is 45wt%-50wt%, and the balance is chromium.

[0011] Optionally, the composition of the Cu-Cr-Zr-Nb alloy ingot includes, by mass percentage: Cr: 0.5%-1.2%; Zr: 0.03%-0.3%; Nb: 0.01%-0.4%; Fe≤0.03%; Si≤0.01%; Al≤0.01%; O≤0.02%; and Cu is the balance.

[0012] Optionally, the step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank comprises:

[0013] The electrolytic copper plate is added into an induction melting furnace and heated to 1100° C.-1200° C. After the electrolytic copper plate is melted, the chromium-niobium master alloy is added, and the alloy is further heated to 1100° C.-1400° C. and refined for 10 min-40 min. The zirconium sponge is then added and cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank.

[0014] Optionally, in the step of subjecting the forging blank to solution heat treatment, the temperature of the solution heat treatment is 900°C-980°C, and the temperature is kept at 1h-2h.

[0015] Optionally, in the step of rough rolling at 850°C-950°C, the forged billet after solution heat treatment is milled and then rough rolled at 850°C-950°C, with a rolling rate of 3.0m / min-4.0m / min, and the rolling deformation is controlled to be 50%-60%.

[0016] Optionally, in the step of annealing the rough-rolled billet, the annealing temperature is 600° C.-800° C., and the annealing time is 1 h-4 h.

[0017] Optionally, in the step of performing intermediate rolling at 850°C-950°C, the rolling rate is

[0018] 4.5m / min-5.5m / min, control the rolling deformation to 50%-60%.

[0019] Optionally, in the step of performing aging heat treatment, the temperature of the aging heat treatment is 400°C-500°C, and the temperature is kept for 2h-5h.

[0020] The present application also proposes a liquid rocket engine thrust chamber injector panel, which is obtained using the above-mentioned method for preparing the liquid rocket engine thrust chamber injector panel.

[0021] This application includes at least the following beneficial effects:

[0022] The present application first designs the composition of the injector panel material, and adopts Cu, Cr, Zr, and Nb as alloy components. The Cu alloy has a high thermal conductivity, and Cr and Nb can form an intermetallic compound Cr2Nb. Cr2Nb can be used as a strengthening phase to enhance the electrical conductivity and thermal conductivity of the Cu alloy, while refining and controlling the grain size of Cu, thereby improving the high-temperature strength and thermal stability of the Cu alloy. Zr can significantly improve the strength and heat resistance of the copper alloy through solid solution strengthening and precipitation strengthening mechanisms. At the same time, Zr has a significant effect of refining the copper grain size in the copper alloy, and the addition of Zr can improve the existence form of the Cr-rich phase, transforming it from a short rod shape to a spherical shape, further enhancing the strength and hardness of the alloy, thereby improving the mechanical properties of the panel material. After high-temperature forging and controlling the deformation amount of each forging fire, a forging billet with a dense structure and uniform composition can be obtained, and then Solution heat treatment allows the excess phase to be fully dissolved into the solid solution to obtain a supersaturated solid solution, so as to eliminate the precipitates on the cast structure, reduce brittleness, and maintain the stability of the alloy components. After rough rolling at 850°C-950°C, intermediate rolling is performed again at 850°C-950°C. Compared with conventional cold rolling, the present application can ensure the complete occurrence of dynamic recrystallization of the metal components in the panel material, thereby improving the internal structure of the metal and improving the mechanical properties. Finally, aging heat treatment is performed to eliminate residual stress and phase change stress, thereby obtaining a Cu-Cr-Zr-Nb material panel with high thermal conductivity. The panel can be mass-produced through rolling, which is more efficient than the current single-piece forging, has high material utilization rate, and low unit cost. At the same time, the material has high high-temperature strength, uniform structure, and stable performance, which solves the material ablation problem caused by poor heat conduction of the current injector panel material. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. It is obvious that the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0024] Figure 1 This is a flow chart of a method for preparing a liquid rocket engine thrust chamber injector panel according to an embodiment of the present application;

[0025] Figure 2 This is the metallographic structure diagram of the injector panel described in Example 1 of the present application.

[0026] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0028] In view of the technical problems existing in the prior art, the embodiments of the present application provide a method for preparing a liquid rocket engine thrust chamber injector panel, such as Figure 1 As shown, the following steps are included:

[0029] The raw materials are subjected to atmosphere protection induction melting to prepare Cu-Cr-Zr-Nb alloy ingot blanks;

[0030] Forging the ingot blank at 850° C.-950° C. for 60 min-150 min, controlling the deformation amount of each forging to be 30%-50%, to obtain a forged blank;

[0031] After the forging blank is subjected to solution heat treatment, rough rolling is performed at 850°C-950°C to obtain a rough rolled blank; after the rough rolled blank is subjected to annealing, intermediate rolling is performed at 850°C-950°C to obtain a rolled blank;

[0032] After the rolled blank is cut into a circular blank of an injector panel, an aging heat treatment is performed, and then the blank is machined to the dimensional tolerance required by the product drawing to obtain a finished injector panel.

[0033] The present application first designs the composition of the injector panel material, and adopts Cu, Cr, Zr, and Nb as alloy components. The Cu alloy has a high thermal conductivity, and Cr and Nb can form an intermetallic compound Cr2Nb. Cr2Nb can be used as a strengthening phase to enhance the electrical conductivity and thermal conductivity of the Cu alloy, while refining and controlling the grain size of Cu, thereby improving the high-temperature strength and thermal stability of the Cu alloy. Zr can significantly improve the strength and heat resistance of the copper alloy through solid solution strengthening and precipitation strengthening mechanisms. At the same time, Zr has a significant effect of refining the copper grain size in the copper alloy, and the addition of Zr can improve the existence form of the Cr-rich phase, transforming it from a short rod shape to a spherical shape, further enhancing the strength and hardness of the alloy, thereby improving the mechanical properties of the panel material. After high-temperature forging and controlling the deformation amount of each forging fire, a forging billet with a dense structure and uniform composition can be obtained, and then Solution heat treatment allows the excess phase to be fully dissolved into the solid solution to obtain a supersaturated solid solution, so as to eliminate the precipitates on the cast structure, reduce brittleness, and maintain the stability of the alloy components. After rough rolling at 850°C-950°C, intermediate rolling is performed again at 850°C-950°C. Compared with conventional cold rolling, the present application can ensure the complete occurrence of dynamic recrystallization of the metal components in the panel material, thereby improving the internal structure of the metal and improving the mechanical properties. Finally, aging heat treatment is performed to eliminate residual stress and phase change stress, thereby obtaining a Cu-Cr-Zr-Nb material panel with high thermal conductivity. The panel can be mass-produced through rolling, which is more efficient than the current single-piece forging, has high material utilization rate, and low unit cost. At the same time, the material has high high-temperature strength, uniform structure, and stable performance, which solves the material ablation problem caused by poor heat conduction of the current injector panel material. As an implementation method of the present application, in the step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank, the raw materials include electrolytic copper plate, chromium-niobium master alloy and zirconium sponge;

[0034] The content of niobium in the chromium-niobium master alloy is 45wt%-50wt%, and the balance is chromium.

[0035] In the specific implementation process, the electrolytic copper plate has the advantages of high purity, good electrical conductivity and thermal conductivity, reusability, environmental protection, strong controllability, excellent surface quality and good dimensional stability. The use of high-purity electrolytic copper plate is conducive to the preparation of copper alloys with excellent performance. The content of copper in the electrolytic copper plate used in this application is above 99.97wt%; sponge zirconium has very strong corrosion resistance. Adding sponge zirconium to copper alloys can significantly improve the corrosion resistance of copper alloys and improve the overall mechanical properties of copper alloys. The content of zirconium in the sponge zirconium used in this application is above 99.50wt%; chromium and niobium are added in the form of an intermediate alloy. Due to the high density of chromium, direct addition may lead to segregation, and chromium has a high melting point. Direct addition to copper metal may be difficult to evenly integrate due to the high melting point, while the melting point of the chromium-niobium intermediate alloy is lower than that of elemental chromium, and it is easier to melt and disperse during the alloy preparation process. Compared with the traditional material prepared by adding metal chromium and metal niobium separately, its organization is more uniform, the performance is consistent, and the comprehensive performance is excellent.

[0036] As an implementation method of the present application, the composition of the Cu-Cr-Zr-Nb alloy ingot blank includes, by mass percentage:

[0037] Cr: 0.5%-1.2%; Zr: 0.03%-0.3%; Nb: 0.01%-0.4%; Fe≤0.03%; Si≤0.01%; Al≤0.01%; O≤0.02%; Cu is the balance.

[0038] Specifically, an appropriate amount of Nb element can improve the hardness of the alloy, but as the Nb content increases, the Cr2Nb phase morphology in the alloy will change. At the same time, when the Cr content is too high, it will cause the cast grain boundary segregation of the Cu-Cr-Zr alloy. Although the microhardness and tensile strength of the Cu-Cr-Zr alloy will increase, the conductivity and elongation will decrease. In order to make the panel material show the best microhardness and tensile strength, this application controls the Nb content to 0.01%-0.4% and the Cr content to 0.5%-1.2%; and the increase in Zr content can significantly improve the hardness of the alloy, but at the same time, the addition of Zr will hinder the movement of electrons, resulting in a decrease in the electrical conductivity of the alloy, so this application controls the Zr content to 0.03%-0.3%. After the design of the material composition and content of this application, the obtained Cu-Cr-Zr-Nb material panel can have a high tensile strength, uniform organization, and excellent performance.

[0039] As an implementation method of the present application, the step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank comprises:

[0040] The electrolytic copper plate is added into an induction melting furnace and heated to 1100° C.-1200° C. After the electrolytic copper plate is melted, the chromium-niobium master alloy is added, and the alloy is further heated to 1100° C.-1400° C. and refined for 10 min-40 min. The zirconium sponge is then added and cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank.

[0041] Specifically, the present application uses a vacuum induction melting furnace for smelting, and controls the refining temperature to 1100°C-1400°C, which can accurately control the chemical composition of the alloy. Active elements such as Al and Fe that have strong affinity with oxygen and nitrogen can be controlled within a very small range, which is beneficial to stabilizing the chemical composition of the alloy, avoiding impurity defects, and thus improving the chemical properties of the material.

[0042] As an implementation method of the present application, in the step of subjecting the forging blank to solid solution heat treatment, the temperature of the solid solution heat treatment is 900°C-980°C, and the temperature is kept at 1h-2h.

[0043] Specifically, when performing solution heat treatment, a resistance heating furnace is used, and the temperature is preferably set to 940°C and kept warm for 1.5 hours, and then immersed in water for cooling, so that the excess phase can be fully dissolved into the solid solution, and then immediately cooled to obtain a supersaturated solid solution, which can significantly improve the strength of the finished panel material and thereby improve the product quality of the injector panel.

[0044] As an implementable embodiment of the present application, in the step of rough rolling at 850℃-950℃, the forging billet after solution heat treatment is milled and then rough rolled at 850℃-950℃, the rolling rate is 3.0m / min-4.0m / min, and the rolling deformation is controlled to be 50%-60%.

[0045] Specifically, it is preferred to carry out rough rolling at 900°C and control the rolling deformation to 50%-60%. Compared with cold rolling treatment, it can ensure the complete occurrence of dynamic recrystallization of metal components in the panel material, thereby improving the internal structure of the metal and improving the high temperature strength of the injector panel material.

[0046] As an implementation method of the present application, in the step of annealing the rough-rolled billet, the annealing temperature is 600° C.-800° C., and the annealing time is 1 h-4 h.

[0047] In the specific implementation process, it is preferred to carry out annealing treatment at 700°C for 2.5 hours to eliminate internal stress, improve the stability and corrosion resistance of the panel, refine the grains, improve the internal structure of the metal, and thus improve the high-temperature mechanical properties of the injector panel.

[0048] As an implementable method of the present application, in the step of performing intermediate rolling at 850° C.-950° C., the rolling rate is 4.5 m / min-5.5 m / min, and the rolling deformation is controlled to be 50%-60%.

[0049] In the specific implementation process, it is preferred to carry out medium rolling at 900°C and control the rolling deformation to be 50%-60%. By rolling again, the panel material structure is ensured to be more uniform, thereby obtaining a panel material with more uniform and stable performance.

[0050] As an implementation method of the present application, in the step of performing aging heat treatment, the temperature of the aging heat treatment is 400°C-500°C, and the temperature is kept for 2h-5h.

[0051] In the specific implementation process, it is preferred to perform aging heat treatment at 450° C., which can make the microstructure of the injector panel more stable, thereby ensuring the dimensional accuracy and stability of the injector panel.

[0052] An embodiment of the present application also provides a liquid rocket engine thrust chamber injector panel, which is obtained using the above-mentioned method for preparing the liquid rocket engine thrust chamber injector panel.

[0053] The above technical solution of the present application is described in detail below in conjunction with specific embodiments.

[0054] Example 1

[0055] A method for preparing a liquid rocket engine thrust chamber injector panel comprises the following steps:

[0056] The electrolytic copper plate is added into an induction melting furnace and heated to 1150° C. After the electrolytic copper plate is melted, a chromium-niobium master alloy is added, and the mixture is further heated to 1300° C. and refined for 25 minutes. Sponge zirconium is added and then cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank. The content of niobium in the chromium-niobium master alloy is 47wt%, and the balance is chromium. The composition of the Cu-Cr-Zr-Nb alloy ingot blank includes:

[0057] Cr: 0.5%; Zr: 0.17%; Nb: 0.4%; Fe: 0.0:2%; Si: 0.008%; Al: 0.008%; O: 0.01%; Cu is the balance;

[0058] Forging the ingot blank at 900° C. for 105 min, controlling the deformation amount of each forging to be 40%, to obtain a forged blank;

[0059] The forging blank is subjected to solution heat treatment at 940° C. for 1.5 h, and then subjected to surface milling, and then subjected to rough rolling at 900° C., with a rolling rate of 3.5 m / min, and a rolling deformation amount controlled to be 55%;

[0060] The rough-rolled billet is annealed at 700° C. for 2.5 hours, and then intermediate-rolled at 900° C. at a rolling rate of 5.0 m / min and a rolling deformation amount of 55% to obtain a rolled billet;

[0061] After the rolled blank is cut into a circular blank of the injector panel, an aging heat treatment is performed at 450°C for 3.5 hours, and then the product is turned and milled to meet the dimensional tolerance required by the drawing to obtain a finished injector panel. The obtained injector panel is subjected to metallographic analysis using a 100μm metallographic microscope, and the following is obtained: Figure 2 The metallographic structure diagram shown.

[0062] Depend on Figure 2 It can be seen that the grain structure of the injector panel material obtained in Example 1 is uniform and fine, without abnormal phases, thereby ensuring the uniformity and stability of the injector panel product performance.

[0063] Example 2

[0064] A method for preparing a liquid rocket engine thrust chamber injector panel comprises the following steps:

[0065] The electrolytic copper plate is added into an induction melting furnace and heated to 1100° C. After the electrolytic copper plate is melted, a chromium-niobium master alloy is added, and the heating is continued at 1100° C. and refined for 40 minutes. Then, zirconium sponge is added and cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank; wherein the content of niobium element in the chromium-niobium master alloy is 45wt%, and the balance is chromium element; the composition of the Cu-Cr-Zr-Nb alloy ingot blank includes:

[0066] Cr: 0.6%; Zr: 0.03%; Nb: 0.3%; Fe: 0.01%; Si≤0.01%; Al≤0.01%; O≤0.02%; Cu is the balance;

[0067] Forging the ingot blank at 850° C. for 150 min, controlling the deformation amount of each forging to be 30%, to obtain a forged blank;

[0068] The forging blank is subjected to solution heat treatment at 900° C. for 2 hours, and then subjected to surface milling, and then subjected to rough rolling at 850° C., with a rolling rate of 3.0 m / min, and a rolling deformation amount controlled to be 50%;

[0069] The rough-rolled billet is annealed at 600° C. for 4 hours, and then intermediate-rolled at 850° C. at a rolling rate of 4.5 m / min, with the rolling deformation controlled to be 50%, to obtain a rolled billet;

[0070] After the rolled blank is cut into a circular blank of an injector panel, an aging heat treatment is performed at 400° C. for 5 hours, and then the product is turned and milled to meet the dimensional tolerance required by the drawing, thereby obtaining a finished injector panel.

[0071] Example 3

[0072] A method for preparing a liquid rocket engine thrust chamber injector panel comprises the following steps:

[0073] The electrolytic copper plate is added into an induction melting furnace and heated to 1200° C. After the electrolytic copper plate is melted, a chromium-niobium master alloy is added, and the mixture is further heated to 1400° C. and refined for 10 minutes. Sponge zirconium is added and then cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank. The content of niobium in the chromium-niobium master alloy is 50wt%, and the balance is chromium. The composition of the Cu-Cr-Zr-Nb alloy ingot blank includes:

[0074] Cr: 0.7%; Zr: 0.3%; Nb: 0.3%; Fe: 0.03%; Si: 0.01%; Al: 0.01%; O: 0.02%; Cu is the balance;

[0075] Forging the ingot blank at 950° C. for 60 minutes, controlling the deformation amount of each forging to be 50%, to obtain a forged blank;

[0076] The forging blank is subjected to solution heat treatment at 980° C. for 1 hour, and then subjected to surface milling, and then subjected to rough rolling at 950° C., with a rolling rate of 4.0 m / min, and a rolling deformation amount controlled to be 60%;

[0077] The rough-rolled billet is annealed at 800° C. for 4 hours, and then intermediate-rolled at 950° C. at a rolling rate of 5.5 m / min and a rolling deformation amount of 60% to obtain a rolled billet;

[0078] After the rolled billet is cut into a circular billet for an injector panel, an aging heat treatment is performed at 500° C. for 2 hours, and then the billet is turned and milled to make the product meet the dimensional tolerance required by the drawing, thereby obtaining a finished injector panel.

[0079] Example 4

[0080] A method for preparing a liquid rocket engine thrust chamber injector panel comprises the following steps:

[0081] The electrolytic copper plate is added into an induction melting furnace and heated to 1180° C. After the electrolytic copper plate is melted, a chromium-niobium master alloy is added, and the mixture is further heated to 1350° C. and refined for 25 minutes. Sponge zirconium is added and then cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank. The content of niobium in the chromium-niobium master alloy is 46wt%, and the balance is chromium. The composition of the Cu-Cr-Zr-Nb alloy ingot blank includes:

[0082] Cr: 0.54%; Zr: 0.25%; Nb: 0.35%; Fe: 0.025%; Si: 0.009%; Al: 0.01%; O: 0.01%; Cu is the balance;

[0083] Forging the ingot blank at 920° C. for 80 min, controlling the deformation amount of each forging to be 35%, to obtain a forged blank;

[0084] The forging blank is subjected to solution heat treatment at 960° C. for 1.8 h, and then subjected to surface milling, and then subjected to rough rolling at 880° C., with a rolling rate of 3.2 m / min, and a rolling deformation amount controlled to be 52%;

[0085] The rough-rolled billet is annealed at 720° C. for 3 hours, and then intermediate-rolled at 880° C. at a rolling rate of 4.8 m / min and a rolling deformation amount of 52% to obtain a rolled billet;

[0086] After the rolled blank is cut into a circular blank of an injector panel, an aging heat treatment is performed at 480° C. for 3 hours, and then the product is turned and milled to meet the dimensional tolerance required by the drawing, thereby obtaining a finished injector panel.

[0087] Example 5

[0088] A method for preparing a liquid rocket engine thrust chamber injector panel comprises the following steps:

[0089] The electrolytic copper plate is added into an induction melting furnace and heated to 1120° C. After the electrolytic copper plate is melted, a chromium-niobium master alloy is added, and the mixture is further heated to 1380° C. and refined for 22 minutes. Sponge zirconium is added and then cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank. The content of niobium in the chromium-niobium master alloy is 48wt%, and the balance is chromium. The composition of the Cu-Cr-Zr-Nb alloy ingot blank includes:

[0090] Cr: 0.6%; Zr: 0.28%; Nb: 0.2%; Fe: 0.01%; Si: 0.005%; Al: 0.003%; O: 0.02%; Cu is the balance;

[0091] Forging the ingot blank at 910° C. for 70 min, controlling the deformation amount of each forging to be 35%, to obtain a forged blank;

[0092] The forging blank is subjected to solution heat treatment at 920° C. for 1.3 h, and then subjected to surface milling, and then subjected to rough rolling at 870° C., with a rolling rate of 3.4 m / min, and a rolling deformation amount controlled to be 58%;

[0093] The rough-rolled billet is annealed at 750° C. for 3.2 hours, and then intermediate-rolled at 870° C. at a rolling rate of 4.8 m / min and a rolling deformation amount of 58% to obtain a rolled billet;

[0094] After the rolled billet is cut into a circular billet for an injector panel, an aging heat treatment is performed at 440° C. for 4.5 hours, and then the billet is turned and milled to make the product meet the dimensional tolerance required by the drawing, thereby obtaining a finished injector panel.

[0095] Experimental Example 1

[0096] The thermal conductivity of the injector panel obtained in the embodiment of the present application was tested at different temperatures, and the GH3030 material was used as a control group. The test results are shown in Table 1 below.

[0097] Table 1

[0098]

[0099] As can be seen from Table 1, the Cu-Cr-Zr-Nb material panel prepared in the embodiment of the present application has a relatively high thermal conductivity, which can reach above 330 W / m·K. Compared with the existing GH3030 material panel, its thermal conductivity can be increased by more than 10 times.

[0100] Experimental Example 2

[0101] The tensile strength of the injector panel obtained in the embodiment of the present application was tested at different temperatures. The test results are shown in Table 2 below.

[0102] Table 2

[0103]

[0104] It can be seen from Table 2 that the Cu-Cr-Zr-Nb material panel prepared in the present application has a high tensile strength, which can still reach more than 300 MPa at a high temperature of 400°C, indicating that it has a high high-temperature strength and can meet the use requirements of the liquid rocket engine thrust chamber injector panel.

[0105] The above description is only an optional embodiment of the present application, and does not limit the patent scope of the present application. All equivalent structural transformations made by using the contents of the present application specification and drawings under the inventive concept of the present application, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A method for preparing a liquid rocket engine thrust chamber injector panel, characterized in that: The following steps are involved: The raw materials are subjected to atmosphere protection induction melting to prepare Cu-Cr-Zr-Nb alloy ingot blanks; Forging the ingot blank at 850° C.-950° C. for 60 min-150 min, controlling the deformation amount of each forging to be 30%-50%, to obtain a forged blank; After the forging blank is subjected to solution heat treatment, rough rolling is performed at 850°C-950°C to obtain a rough rolled blank; after the rough rolled blank is subjected to annealing, intermediate rolling is performed at 850°C-950°C to obtain a rolled blank; After the rolled blank is cut into a circular blank of an injector panel, an aging heat treatment is performed, and then the blank is machined to the dimensional tolerance required by the product drawing to obtain a finished injector panel.

2. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank, the raw materials include electrolytic copper plate, chromium-niobium master alloy and zirconium sponge; The content of niobium in the chromium-niobium master alloy is 45wt%-50wt%, and the balance is chromium.

3. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 2, characterized in that: The composition of the Cu-Cr-Zr-Nb alloy ingot blank comprises, by mass percentage: Cr: 0.5%-1.2%; Zr: 0.03%-0.3%; Nb: 0.01%-0.4%; Fe≤0.03%; Si≤0.01%; Al≤0.01%; O≤0.02%; Cu is the balance.

4. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 3, characterized in that: The step of performing atmosphere protection induction melting on the raw materials to prepare the Cu-Cr-Zr-Nb alloy ingot blank comprises: The electrolytic copper plate is added into an induction melting furnace and heated to 1100° C.-1200° C. After the electrolytic copper plate is melted, the chromium-niobium master alloy is added, and the alloy is further heated to 1100° C.-1400° C. and refined for 10 min-40 min. The zirconium sponge is then added and cast to obtain a Cu-Cr-Zr-Nb alloy ingot blank.

5. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of subjecting the forging blank to solid solution heat treatment, the temperature of the solid solution heat treatment is 900° C.-980° C., and the temperature is kept at 1 h-2 h.

6. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of rough rolling at 850°C-950°C, the forged billet after solution heat treatment is milled and then rough rolled at 850°C-950°C, with a rolling rate of 3.0m / min-4.0m / min, and the rolling deformation is controlled to be 50%-60%.

7. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of annealing the rough rolled billet, the annealing temperature is 600° C.-800° C., and the annealing time is 1 h-4 h.

8. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of performing intermediate rolling at 850° C.-950° C., the rolling rate is 4.5 m / min-5.5 m / min, and the rolling deformation is controlled to be 50%-60%.

9. The method for preparing a liquid rocket engine thrust chamber injector panel according to claim 1, characterized in that: In the step of performing aging heat treatment, the temperature of the aging heat treatment is 400° C.-500° C., and the temperature is kept for 2h-5h.

10. A liquid rocket engine thrust chamber injector panel, characterized in that: Obtained by the preparation method of the liquid rocket engine thrust chamber injector panel as described in any one of claims 1 to 9.

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