Flame flow accelerator for erosion and ablation simulation test
By designing flame flow accelerators for refractory metal inner ring, thermal insulation layer and high-strength steel shell, the problems of equipment stability and accuracy in the existing technology simulate high-temperature flame and high-speed flame flow erosion ablation environment are solved, and high efficiency is achieved , continuous simulation tests reduce test errors and costs.
Patent Information
- Application Number
- CN202411507608.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-28
- Publication Date
- 2025-01-03
AI Technical Summary
In the prior art, under the simulated high-temperature flame and high-speed flame flow erosion ablation environment, the gas and flame flow pressure and velocity of the test equipment are relatively low, and the gas composition and the real environment are very different, resulting in large limitations in the test evaluation results, and the simulation test device is easy to Coating peeling, thermal cracking and other problems occur, which affects the test efficiency and accuracy.
A flame flow accelerator is designed, including the accelerator body consisting of a refractory metal inner ring, a heat insulation layer and a high-strength steel shell. The flame flow channel consists of a converging part, a throat diameter part, an expansion part and a connection part, a throat diameter part and an expansion part. The diameter and angle of the part are designed specifically. The insulation layer uses low-density carbon/phenolic composite material and ceramic powder to form a high-efficiency insulation layer to ensure the stability and reliability of the accelerator in a high-temperature environment.
It realizes effective simulation of high temperature, high-speed gas or flame flow, avoids problems such as melting and thermal cracking, ensures the continuity and accuracy of the test, reduces test errors, and has a simple structure and low cost, making it suitable for recycling.
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Figure CN119246402A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of simulation test, and in particular to a flame accelerator used for scouring and ablation simulation test. Background Art
[0002] During operation, hot-end components such as gas engines, solid rocket engines, gas guide holes and barrels of internal energy guns are usually in a complex environment of high temperature, high-speed gas or flame erosion and ablation. The hot-end components are very likely to have defects such as size enlargement and thermal cracks due to the erosion and ablation of gas or flame, which can greatly reduce the service life of the hot-end components or even cause them to fail to work properly. Therefore, during the design and manufacturing process of the above-mentioned hot-end components, it is usually necessary to evaluate their erosion and ablation resistance and other properties to evaluate their safety and reliability during actual use.
[0003] At present, the existing technology uses test methods such as oxygen-acetylene ablation, plasma ablation, and metal combustion experimental devices to simulate the performance of hot end components in high-temperature flames and high-frequency heat flow impact environments; however, the gas and flame pressure and speed of existing equipment are relatively low, and the gas composition and other factors are quite different from the actual environment, which can easily lead to problems such as large limitations on test evaluation results and inconsistency between test data and actual usage, and thus cannot provide effective reference or guidance for the design and manufacture of components; at the same time, during the simulation process of the existing high-temperature flame ablation device, the accelerated combustion section of the gas or flame flow is very likely to have coating peeling, thermal cracks, melting or structural changes due to high-speed flame scouring and ablation, which can lead to the inability of the simulation test device to conduct continuous and long-term simulation tests, affecting the test efficiency, and the defects of the simulation test device due to the high-temperature flame flow will further affect the accuracy of the test results and increase the simulation test error. Summary of the invention
[0004] In view of the problems existing in the above-mentioned prior art, the object of the present invention is to provide a flame flow accelerator for erosion and ablation simulation test, which can effectively simulate the erosion and ablation caused by high-temperature and high-speed gas or flame flow, thereby providing test data support for the evaluation of the erosion and ablation resistance of hot end components; at the same time, the flame flow accelerator will not have problems such as melting and thermal cracking during the continuous and long-term flame flow erosion and ablation process, has high stability and reliability, and can effectively avoid test errors caused by defects in simulation test equipment.
[0005] The purpose of the present invention is achieved through the following technical solutions: A flame flow accelerator for erosion and ablation simulation test comprises an accelerator body, a flame flow channel is provided in the middle of the accelerator body, and the flame flow channel comprises a convergent part, a throat part, an expansion part and a connecting part which are coaxially arranged from left to right, wherein the left and right ends of the throat part are respectively connected with the convergent part and the expansion part, and the convergent part is a conical structure with a diameter gradually decreasing from left to right (i.e., from the end far from the throat part to the end close to the throat part), and the expansion part is a conical structure with a diameter gradually increasing from left to right (i.e., from the end close to the throat part to the end far from the throat part). The accelerator body has a large conical structure, and the end of the expansion part away from the throat diameter part is connected to the connecting part; the shell part of the accelerator body is provided with a refractory metal inner ring, a thermal insulation layer and a high-strength steel outer shell in sequence from the inner ring to the outer ring, and the high-strength steel outer shell is located on the inner wall of the expansion section and has a groove with a longitudinal section extending from the expansion part to the convergence part and a stepped structure, a thermal insulation layer is arranged on the surface of the groove and the longitudinal section of the thermal insulation layer is an inverted "Z"-shaped structure, and the surface of the thermal insulation layer (i.e., the side surface away from the high-strength steel outer shell) is embedded in the refractory metal inner ring.
[0006] Based on further optimization of the above scheme, the diameter of the throat portion is 4mm~25mm, and the width of the throat portion is 3mm~10mm; the width of the convergent portion is 5mm~15mm, and the angle of the convergent portion is 60°~120°; the width of the expansion portion is 15mm~30mm, and the angle of the expansion portion is 8°~56°, and the maximum diameter of the convergent portion is greater than the maximum diameter of the expansion portion.
[0007] Based on further optimization of the above solution, the refractory metal inner ring is made of any one of tungsten-molybdenum alloy, tungsten-niobium alloy, molybdenum-tantalum alloy and molybdenum-rhenium alloy.
[0008] Based on further optimization of the above solution, the thickness of the thermal insulation layer is 0.5 to 1.5 mm.
[0009] Based on further optimization of the above scheme, the thermal insulation layer is formed by mixing a low-density carbon / phenolic composite material with ceramic powder; wherein the low-density carbon / phenolic composite material is formed by wrapping a carbon fiber material with phenolic resin, the carbon fiber adopts chopped carbon fiber P800 with a fiber diameter of 10 to 15 μm, the particle size of the phenolic resin is less than 75 μm, and the mass ratio of carbon fiber to phenolic resin is 1:0.8 to 2; the ceramic powder adopts a mixed powder of zirconium oxide, silicon nitride and aluminum oxide, and the mass proportion of ceramic powder in the low-density carbon / phenolic composite material is 10% to 20%.
[0010] Based on further optimization of the above scheme, in the mixed powder: the particle size of the zirconium oxide powder is 0.3μm~2μm, the particle size of the silicon nitride powder is 0.05μm~0.5μm, and the particle size of the aluminum oxide powder is 1~10μm; the mass ratio of zirconium oxide powder, silicon nitride powder and aluminum oxide powder is 6.5~7.5:1.5~2.5:0.8~1.2.
[0011] Based on further optimization of the above scheme, the distance between the left end of the groove and the left end face of the accelerator body is 2mm~5mm, the distance between the left end of the groove and the maximum diameter of the convergence part is 2.5mm~4.5mm, and the distance between the right end of the groove and the right end face of the expansion part is 1mm~2mm.
[0012] Based on further optimization of the above scheme, the inner diameter of the connecting part is greater than the maximum diameter of the expansion part, the inner diameter of the connecting part is determined according to the outer diameter of the hot end component to be tested, and the installation of the hot end component on the flame accelerator is achieved by the inner wall of the connecting part contacting the outer wall of the hot end component to be tested; the width of the connecting part is 5mm to 30mm.
[0013] Based on further optimization of the above solution, the high-strength steel shell is made of any one of 35CrMnSiA and 30CrMnSiNi2A.
[0014] The following are the technical effects that the present invention has: The accelerator body formed by a refractory metal inner ring, a thermal insulation layer and a high-strength steel outer shell in the present application can not only utilize the refractory metal inner ring to resist multiple scouring and ablation of high-temperature and high-speed combustion gas in the scouring and ablation simulation test, thereby achieving the purpose of multiple cycles; it can also effectively ensure the strength of the accelerator body, avoid overheating of the high-strength steel outer shell and affect the external environment and equipment, affect the simulation test data, and other problems. At the same time, the thermal insulation layer is formed by mixing a low-density carbon / phenolic composite material with a ceramic material formed by mixing specific powders. Not only does the carbon-phenolic resin use carbonization at ultra-high temperature (generally 1800-2500°C) to generate a carbonized layer to achieve heat insulation, but the phase change of zirconium oxide at ultra-high temperature (i.e., the transformation from monoclinic phase to tetragonal phase and cubic phase) is combined with silicon nitride ceramics with a stable crystal structure at high temperature as a skeleton and a composite layer composed of alumina with low thermal conductivity, so as to further insulate the heat after the carbonization layer is blocked and improve the thermal insulation effect. The high porosity of the low-density carbon / phenolic composite material and the molten carbonization of the phenolic matrix provide a buffer space for the phase change of zirconium oxide at ultra-high temperature. Without adding additional stabilizers, the cracking and peeling of the thermal insulation layer or the carbonized layer formed by pyrolysis caused by the volume change during the phase change of zirconium oxide can be avoided, thereby ensuring the uniformity of the thermal insulation layer, thereby avoiding the temperature convergence points or poor thermal insulation effect caused by cracking and peeling. In addition, by melting the phenolic matrix during the pyrolysis and carbonization process and flushing the refractory metal inner ring with the ablative airflow, the bonding strength between the refractory metal inner ring and the high-strength steel outer shell is enhanced, thereby ensuring the integrity of the accelerator body and avoiding safety problems such as heat leakage and air leakage caused by air gaps.
[0015] The overall structure of the present application is simple and easy to prepare. It can achieve multiple high-temperature and high-speed gas erosion and ablation requirements, meet the design requirements for cyclic use, and have lower costs for simulation tests. At the same time, compared with oxyacetylene ablation, metal combustion and other tests, the erosion and ablation test using the flame accelerator of the present application is closer to the actual working conditions of the artillery barrel, and can qualitatively, quantitatively and accurately characterize the erosion and ablation performance of the barrel material under high-temperature and high-speed gunpowder gas. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 Schematic diagram of the structure of the accelerator body in an embodiment of the present invention.
[0017] Among them, 11, convergence part; 12, throat diameter part; 13, expansion part; 14, connection part; 21, refractory metal inner ring; 22, thermal insulation layer; 23, high-strength steel outer shell. DETAILED DESCRIPTION
[0018] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.
[0019] Embodiment 1: A flame accelerator used for erosion and ablation simulation test, referring to Figure 1 As shown: it includes an accelerator body, a flame flow channel is opened in the middle of the accelerator body, and the flame flow channel is coaxially arranged from left to right, including a convergent part 11, a throat part 12, an expansion part 13 and a connecting part 14, wherein the left and right ends of the throat part 12 are respectively connected to the convergent part 11 and the expansion part 12, the diameter D of the throat part 12 is 4mm to 25mm (preferably 15mm), and the width L of the throat part 2 The convergent portion 11 is a conical structure with a diameter gradually decreasing from left to right (i.e., from the end away from the throat diameter portion 12 to the end close to the throat diameter portion 12). The width L of the convergent portion 11 is 1 The diameter of the expansion portion 13 gradually increases from left to right (i.e., from the end close to the throat diameter portion 12 to the end away from the throat diameter portion 12). The width L of the expansion portion 13 is 3 The maximum diameter of the convergent portion 11 is greater than the maximum diameter of the expansion portion 12 (such as Figure 1As shown); one end of the expansion portion 13 away from the throat diameter portion 12 is connected to the connecting portion 14, the inner diameter of the connecting portion 14 is greater than the maximum diameter of the expansion portion 13, the inner diameter of the connecting portion 14 is determined according to the outer diameter of the hot end component to be tested (i.e., the barrel), and the hot end component is installed on the flame accelerator by the inner wall of the connecting portion 14 contacting the outer wall of the hot end component to be tested; the width L of the connecting portion 14 5 5mm~30mm (preferably 20mm).
[0020] Reference Figure 1 As shown: the shell part of the accelerator body is provided with a refractory metal inner ring 21, a heat insulation layer 22 and a high-strength steel shell 23 in sequence from the inner ring to the outer ring. The high-strength steel shell 23 is located at the inner wall of the expansion part 13 and has a groove with a longitudinal section extending from the expansion part 13 to the convergence part 11 and a stepped structure. The heat insulation layer 22 is provided on the surface of the groove and the longitudinal section of the heat insulation layer 22 is an inverted "Z"-shaped structure (such as Figure 1 As shown in the longitudinal cross-sectional diagram of the accelerator body, the heat insulation layer 22 is a "Z"-shaped structure with two inverted upper and lower sections), the distance L between the left end of the groove and the left end face of the accelerator body 5 is 2 mm to 5 mm (preferably 3 mm), and the distance L between the left end of the groove and the maximum diameter of the convergent portion 11 is 6 is 2.5 mm to 4.5 mm (preferably 3.5 mm), and the distance L between the right end of the groove and the right end surface of the expansion portion 13 is 7 It is 1mm to 2mm (preferably 1.5mm) and is used for clamping the mounting portion corresponding to the barrel.
[0021] The surface of the heat insulation layer 22 (i.e., the side away from the high-strength steel shell 23) is embedded with a refractory metal inner ring 21 (see Figure 1 As shown, the convergent portion 11, the throat portion 12 and a portion of the expansion portion 13 are opened inside the refractory metal inner ring 21, and the other portion of the expansion portion 13 and the connecting portion 14 are opened inside the high-strength steel shell 23).
[0022] The refractory metal inner ring 21 is made of tungsten-molybdenum alloy. The thickness of the heat insulation layer 22 is 0.5-1.5 mm (preferably 1 mm); the heat insulation layer 22 is formed by mixing a low-density carbon / phenolic composite material with ceramic powder; wherein the low-density carbon / phenolic composite material is formed by wrapping a carbon fiber material with phenolic resin, the carbon fiber is chopped carbon fiber P800, the fiber diameter is 10 μm, the particle size of the phenolic resin is less than 75 μm, and the mass ratio of carbon fiber to phenolic resin is 1:0.8; the ceramic powder is a mixed powder of zirconium oxide, silicon nitride and aluminum oxide, the particle size of zirconium oxide powder is 0.3 μm, the particle size of silicon nitride powder is 0.05 μm, and the particle size of aluminum oxide powder is 1; the mass ratio of zirconium oxide powder, silicon nitride powder and aluminum oxide powder is 6.5:1.5:0.; the mass ratio of ceramic powder to low-density carbon / phenolic composite material is 10%. The high-strength steel shell 23 is made of 35CrMnSiA material, and the maximum thickness of the high-strength steel shell 23 (ie, the thickness corresponding to the connecting portion 14 ) is set according to actual conditions.
[0023] Embodiment 2: A flame accelerator used for erosion and ablation simulation test, referring to Figure 1 As shown: it includes an accelerator body, a flame flow channel is opened in the middle of the accelerator body, and the flame flow channel is coaxially arranged from left to right, including a convergent part 11, a throat part 12, an expansion part 13 and a connecting part 14, wherein the left and right ends of the throat part 12 are respectively connected to the convergent part 11 and the expansion part 12, the diameter D of the throat part 12 is 4mm to 25mm (preferably 15mm), and the width L of the throat part 2 The convergent portion 11 is a conical structure with a diameter gradually decreasing from left to right (i.e., from the end away from the throat diameter portion 12 to the end close to the throat diameter portion 12). The width L of the convergent portion 11 is 1 The diameter of the expansion portion 13 gradually increases from left to right (i.e., from the end close to the throat diameter portion 12 to the end away from the throat diameter portion 12). The width L of the expansion portion 13 is 3 The maximum diameter of the convergent portion 11 is greater than the maximum diameter of the expansion portion 12 (such as Figure 1 As shown); one end of the expansion portion 13 away from the throat diameter portion 12 is connected to the connecting portion 14, the inner diameter of the connecting portion 14 is greater than the maximum diameter of the expansion portion 13, the inner diameter of the connecting portion 14 is determined according to the outer diameter of the hot end component to be tested (i.e., the barrel), and the hot end component is installed on the flame accelerator by the inner wall of the connecting portion 14 contacting the outer wall of the hot end component to be tested; the width L of the connecting portion 14 5 5mm~30mm (preferably 20mm).
[0024] Reference Figure 1 As shown: the shell part of the accelerator body is provided with a refractory metal inner ring 21, a heat insulation layer 22 and a high-strength steel shell 23 in sequence from the inner ring to the outer ring. The high-strength steel shell 23 is located at the inner wall of the expansion part 13 and has a groove with a longitudinal section extending from the expansion part 13 to the convergence part 11 and a stepped structure. The heat insulation layer 22 is provided on the surface of the groove and the longitudinal section of the heat insulation layer 22 is an inverted "Z"-shaped structure (such as Figure 1 As shown in the longitudinal cross-sectional diagram of the accelerator body, the heat insulation layer 22 is a "Z"-shaped structure with two inverted upper and lower sections), the distance L between the left end of the groove and the left end face of the accelerator body 5 is 2 mm to 5 mm (preferably 3 mm), and the distance L between the left end of the groove and the maximum diameter of the convergent portion 11 is 6 is 2.5 mm to 4.5 mm (preferably 3.5 mm), and the distance L between the right end of the groove and the right end surface of the expansion portion 13 is 7 It is 1mm to 2mm (preferably 1.5mm) and is used for clamping the mounting portion corresponding to the barrel.
[0025] The surface of the heat insulation layer 22 (i.e., the side away from the high-strength steel shell 23) is embedded with a refractory metal inner ring 21 (see Figure 1 As shown, the convergent portion 11, the throat portion 12 and a portion of the expansion portion 13 are opened inside the refractory metal inner ring 21, and the other portion of the expansion portion 13 and the connecting portion 14 are opened inside the high-strength steel shell 23).
[0026] The refractory metal inner ring 21 is made of tungsten-niobium alloy. The thickness of the heat insulation layer 22 is 0.5-1.5 mm (preferably 1 mm); the heat insulation layer 22 is formed by mixing a low-density carbon / phenolic composite material with ceramic powder; wherein the low-density carbon / phenolic composite material is formed by wrapping a carbon fiber material with phenolic resin, the carbon fiber is chopped carbon fiber P800, the fiber diameter is 12 μm, the particle size of the phenolic resin is less than 75 μm, and the mass ratio of carbon fiber to phenolic resin is 1:1.5; the ceramic powder is a mixed powder of zirconium oxide, silicon nitride and aluminum oxide, the particle size of zirconium oxide powder is 1 μm, the particle size of silicon nitride powder is 0.25 μm, and the particle size of aluminum oxide powder is 5 μm; the mass ratio of zirconium oxide powder, silicon nitride powder and aluminum oxide powder is 7:2:1; the mass proportion of ceramic powder in the low-density carbon / phenolic composite material is 15%. The high-strength steel shell 23 is made of 30CrMnSiNi2A material, and the maximum thickness of the high-strength steel shell 23 (ie, the thickness corresponding to the connecting portion 14 ) is set according to actual conditions.
[0027] Embodiment 3: A flame accelerator used for erosion and ablation simulation test, referring to Figure 1As shown: it includes an accelerator body, a flame flow channel is opened in the middle of the accelerator body, and the flame flow channel is coaxially arranged from left to right, including a convergent part 11, a throat part 12, an expansion part 13 and a connecting part 14, wherein the left and right ends of the throat part 12 are respectively connected to the convergent part 11 and the expansion part 12, the diameter D of the throat part 12 is 4mm to 25mm (preferably 15mm), and the width L of the throat part 2 The convergent portion 11 is a conical structure with a diameter gradually decreasing from left to right (i.e., from the end away from the throat diameter portion 12 to the end close to the throat diameter portion 12). The width L of the convergent portion 11 is 1 The diameter of the expansion portion 13 gradually increases from left to right (i.e., from the end close to the throat diameter portion 12 to the end away from the throat diameter portion 12). The width L of the expansion portion 13 is 3 The maximum diameter of the convergent portion 11 is greater than the maximum diameter of the expansion portion 12 (such as Figure 1 As shown); one end of the expansion portion 13 away from the throat diameter portion 12 is connected to the connecting portion 14, the inner diameter of the connecting portion 14 is greater than the maximum diameter of the expansion portion 13, the inner diameter of the connecting portion 14 is determined according to the outer diameter of the hot end component to be tested (i.e., the barrel), and the hot end component is installed on the flame accelerator by the inner wall of the connecting portion 14 contacting the outer wall of the hot end component to be tested; the width L of the connecting portion 14 5 5mm~30mm (preferably 20mm).
[0028] Reference Figure 1 As shown: the shell part of the accelerator body is provided with a refractory metal inner ring 21, a heat insulation layer 22 and a high-strength steel shell 23 in sequence from the inner ring to the outer ring. The high-strength steel shell 23 is located at the inner wall of the expansion part 13 and has a groove with a longitudinal section extending from the expansion part 13 to the convergence part 11 and a stepped structure. The heat insulation layer 22 is provided on the surface of the groove and the longitudinal section of the heat insulation layer 22 is an inverted "Z"-shaped structure (such as Figure 1 As shown in the longitudinal cross-sectional diagram of the accelerator body, the heat insulation layer 22 is a "Z"-shaped structure with two inverted upper and lower sections), the distance L between the left end of the groove and the left end face of the accelerator body 5 is 2 mm to 5 mm (preferably 3 mm), and the distance L between the left end of the groove and the maximum diameter of the convergent portion 11 is 6 is 2.5 mm to 4.5 mm (preferably 3.5 mm), and the distance L between the right end of the groove and the right end surface of the expansion portion 13 is 7 It is 1mm to 2mm (preferably 1.5mm) and is used for clamping the mounting portion corresponding to the barrel.
[0029] The surface of the heat insulation layer 22 (i.e., the side away from the high-strength steel shell 23) is embedded with a refractory metal inner ring 21 (see Figure 1 As shown, the convergent portion 11, the throat portion 12 and a portion of the expansion portion 13 are opened inside the refractory metal inner ring 21, and the other portion of the expansion portion 13 and the connecting portion 14 are opened inside the high-strength steel shell 23).
[0030] The refractory metal inner ring 21 is made of molybdenum-rhenium alloy. The thickness of the heat insulation layer 22 is 0.5-1.5 mm (preferably 1 mm); the heat insulation layer 22 is formed by mixing a low-density carbon / phenolic composite material with ceramic powder; wherein the low-density carbon / phenolic composite material is formed by wrapping a carbon fiber material with phenolic resin, the carbon fiber is chopped carbon fiber P800, the fiber diameter is 15 μm, the particle size of the phenolic resin is less than 75 μm, and the mass ratio of carbon fiber to phenolic resin is 1:2; the ceramic powder is a mixed powder of zirconium oxide, silicon nitride and aluminum oxide, the particle size of zirconium oxide powder is 2 μm, the particle size of silicon nitride powder is 0.5 μm, and the particle size of aluminum oxide powder is 10 μm; the mass ratio of zirconium oxide powder, silicon nitride powder and aluminum oxide powder is 7.5:2.5:1.2; the mass proportion of ceramic powder in the low-density carbon / phenolic composite material is 20%. The high-strength steel shell 23 is made of 35CrMnSiA material, and the maximum thickness of the high-strength steel shell 23 (ie, the thickness corresponding to the connecting portion 14 ) is set according to actual conditions.
Claims
1. A flame accelerator for erosion and ablation simulation test, characterized in that: It includes an accelerator body, a flame flow channel is opened in the middle of the accelerator body, and the flame flow channel is coaxially arranged from left to right, including a convergent part, a throat part, an expansion part and a connecting part, wherein the left and right ends of the throat part are respectively connected with the convergent part and the expansion part, and the convergent part is a conical structure with a diameter gradually decreasing from left to right, and the expansion part is a conical structure with a diameter gradually increasing from left to right, and the end of the expansion part away from the throat part is connected with the connecting part; the shell part of the accelerator body is sequentially provided with a refractory metal inner ring, a thermal insulation layer and a high-strength steel outer shell from the inner ring to the outer ring, and the inner wall of the high-strength steel outer shell located in the expansion section is provided with a groove with a longitudinal section extending from the expansion part to the convergent part as a stepped structure, a thermal insulation layer is arranged on the surface of the groove, and the longitudinal section of the thermal insulation layer is an inverted "Z"-shaped structure, and the surface of the thermal insulation layer is embedded with the refractory metal inner ring.
2. A flame accelerator for erosion and ablation simulation test according to claim 1, characterized in that: The diameter of the throat portion is 4mm to 20mm, and the width of the throat portion is 3mm to 10mm; the width of the convergent portion is 5mm to 15mm, and the angle of the convergent portion is 60° to 120°; the width of the expansion portion is 15mm to 30mm, and the angle of the expansion portion is 8° to 56°, and the maximum diameter of the convergent portion is greater than the maximum diameter of the expansion portion.
3. A flame accelerator for erosion and ablation simulation test according to claim 1 or 2, characterized in that: The refractory metal inner ring is made of any one of tungsten-molybdenum alloy, tungsten-niobium alloy, molybdenum-tantalum alloy and molybdenum-rhenium alloy.
4. A flame accelerator for erosion and ablation simulation test according to claim 3, characterized in that: The thickness of the heat insulation layer is 0.5-1.5 mm.
5. A flame accelerator for erosion and ablation simulation test according to claim 4, characterized in that: The thermal insulation layer is formed by mixing a low-density carbon / phenolic composite material with ceramic powder; wherein the low-density carbon / phenolic composite material is formed by wrapping a carbon fiber material with phenolic resin, the carbon fiber adopts chopped carbon fiber P800 with a fiber diameter of 10 to 15 μm, the particle size of the phenolic resin is less than 75 μm, and the mass ratio of the carbon fiber to the phenolic resin is 1:0.8 to 2; the ceramic powder adopts a mixed powder of zirconium oxide, silicon nitride and aluminum oxide, and the mass proportion of the ceramic powder in the low-density carbon / phenolic composite material is 10% to 20%.
6. A flame accelerator for erosion and ablation simulation test according to claim 5, characterized in that: In the mixed powder, the particle size of the zirconium oxide powder is 0.3 μm to 2 μm, the particle size of the silicon nitride powder is 0.05 μm to 0.5 μm, and the particle size of the aluminum oxide powder is 1 to 10 μm; the mass ratio of the zirconium oxide powder, the silicon nitride powder and the aluminum oxide powder is 6.5 to 7.5:1.5 to 2.5:0.8 to 1.
2.
7. A flame accelerator for erosion and ablation simulation test according to claim 1 or 2, characterized in that: The inner diameter of the connecting portion is greater than the maximum diameter of the expansion portion, and the inner diameter of the connecting portion is determined according to the outer diameter of the hot end component to be tested. The hot end component is installed on the flame accelerator by contacting the inner wall of the connecting portion with the outer wall of the hot end component to be tested; the width of the connecting portion is 5mm to 30mm.
8. A flame accelerator for erosion and ablation simulation test according to claim 1 or 2, characterized in that: The high-strength steel shell is made of any one of 35CrMnSiA and 30CrMnSiNi2A.