Anti-scouring test device for throat liner and gas vane materials

Abstract

A throat liner and gas vane material anti-washout test device belongs to the technical field of ground-based simulation aerodynamic thermal tests and comprises an electric arc heater, a particle broadcasting system and a supersonic spray pipe. The arc heater generates high-temperature air, aluminum oxide particles or graphite particles are fed into the high-temperature air on the upstream of the supersonic spray pipe through the particle broadcasting system, the aluminum oxide particles or the graphite particles and the high-temperature air are accelerated through the supersonic spray pipe, and the accelerated particles flow through the throat liner and the surface of the gas vane material in parallel. According to the invention, the aluminum oxide particles of the main product after combustion of the solid rocket engine are used as the test working medium, so that the precision of the anti-scouring test of the throat liner and the gas vane can be obviously improved, and the environment of the throat liner and the gas vane material in actual work can be more truly simulated.

Description

Technical Field

[0001] This invention relates to a test device for erosion resistance of throat liner and gas rudder material, belonging to the field of ground-based simulated aerodynamic thermal testing technology. Background Technology

[0002] Throat liner material, as a key component of solid rocket motors, significantly impacts engine performance and operational safety. During engine operation, the throat liner is damaged by the high-temperature, high-pressure, high-speed thermal flux containing erosive particles, causing ablation of the inner surface, leading to surface regression and dimensional changes. Since heat transfer is most intense at the nozzle throat, ablation is most severe there, and the enlarged throat diameter ultimately reduces engine performance. Therefore, the ablation resistance of the throat liner is a crucial indicator for nozzle evaluation. Gas rudder material, as a vital component for aircraft control, requires evaluation of its erosion resistance under high-temperature exhaust gases through ground testing.

[0003] C / C composite materials are excellent ablation thermal structural materials, widely used in engine throat liners due to their high strength, good ablation resistance, and extremely high impact resistance. Because they are used in the thermal environment of solid rocket motor nozzles, the erosion phenomenon of the nozzle throat liner is a complex process influenced by numerous factors, including the aerodynamic design of the nozzle, the ablation atmosphere (including propellant type and composition), fiber characteristics, preform structure, material density, porosity, type of matrix carbon, degree of graphitization, and impurities. Due to the complexity of C / C material preparation and processing, the performance of different batches of products can vary, sometimes significantly. Given the importance and complexity of throat liner erosion, extensive research has been conducted both domestically and internationally on nozzle erosion, emphasizing the simulation of the erosion environment and the understanding of the erosion mechanism. Some studies have involved the analysis of the microstructure morphology of nozzle materials; therefore, obtaining the microstructure under different ablation states is particularly important for studying the ablation mechanism and analyzing the material's erosion resistance.

[0004] There are many methods for testing the particle erosion resistance of heat-resistant materials, such as solid rocket motor ablation / erosion tests; single-particle collision erosion tests with a fixed target and liquid or solid particles launched by a two-stage light gas cannon; free-flight erosion tests conducted in the atmosphere using small rockets; ballistic target erosion tests with a fixed rain screen and a model launched by a two-stage light gas cannon; and particle ablation / erosion tests using electric arc heaters. Currently, the most commonly used method is the electric arc heater particle erosion test, which uses graphite particles accelerated by a high-temperature, high-speed airflow to collide perpendicularly with a model. The mechanical impact generated by the particles' kinetic energy simulates the impact process of rain, snow, fog, hail, and other elements on the aircraft during actual flight.

[0005] Traditional electric arc heating particle ablation / erosion tests employ experimental techniques that simulate head-on collisions between the aircraft and solid particles such as rain, snow, and hail. The primary criterion for simulation is particle kinetic energy flux density. This technique can only simulate erosion phenomena occurring at the aircraft nose during actual flight and cannot simulate the parallel flow shearing effect of particles on the throat liner and gas rudder during actual operation. The significant difference between vertical collision and parallel flow shearing effect on the mechanical erosion of heat-resistant materials means that using vertical collision simulation would significantly increase the heat-resistant thickness of the throat liner and gas rudder materials, limiting the improvement of aircraft performance and consuming excessive amounts of heat-resistant materials.

[0006] Traditional electric arc heating particle ablation / erosion tests use graphite particles as working particles, which collide perpendicularly with the heat-resistant material. However, as the throat liner material and gas vane of a solid rocket motor, its working environment is aluminum oxide particles generated by the solid rocket motor. Therefore, using real working particles can more accurately simulate the actual working environment of the throat liner material and gas vane. Aluminum oxide particles have greater viscosity than graphite particles, but lower hardness, making them difficult to propagate and thus limiting their application in actual ground tests. Summary of the Invention

[0007] The technical problem to be solved by this invention is to overcome the shortcomings of the prior art and solve the problem of simulating the scour test method for throat liner and gas rudder materials.

[0008] The objective of this invention is achieved through the following technical solutions:

[0009] In a first aspect, the present invention provides a throat liner and gas rudder material erosion resistance testing device, including an electric arc heater, a particle seeding system, and a supersonic nozzle;

[0010] The electric arc heater generates high-temperature air, which is then sent into the high-temperature air upstream of the supersonic nozzle through a particle seeding system. The particles are accelerated together with the high-temperature air through the supersonic nozzle, and the accelerated particles flow parallel over the throat liner and the surface of the gas rudder material.

[0011] Based on the first aspect, in one embodiment of the present invention, the flow rate of aluminum oxide particles can be adjusted according to the experimental simulation requirements.

[0012] Based on the first aspect, in one embodiment of the present invention, the flow rate of aluminum oxide particles is adjusted by adjusting the control gas pressure of the particle seeding system and the diameter of the particle seeding pipe.

[0013] Based on the first aspect, in one embodiment of the present invention, the opening of the particle seeding gun of the particle seeding system is on the leeward side of the airflow.

[0014] Based on the first aspect, in one embodiment of the present invention, the particle delivery gun adopts a water-cooled jacket structure.

[0015] Based on the first aspect, in one embodiment of the present invention, the size of the supersonic nozzle is determined according to the model.

[0016] In a second aspect, the present invention provides a method for testing the erosion resistance of throat liner and gas rudder materials, employing the erosion resistance testing apparatus described in the first aspect, and the testing method includes:

[0017] S1. Measure the flow field at the exit of the supersonic nozzle according to the test requirements, and at the same time measure the operating parameters of the electric arc heater;

[0018] S2. Determine the operating parameters of the particle seeding system according to the test conditions, calibrate the flow field of aluminum oxide particles, and determine the particle mass flow rate after the electric arc of the electric arc heater.

[0019] S3. After determining the test conditions, conduct erosion resistance tests on the throat liner and gas rudder materials.

[0020] Based on the second aspect, in one embodiment of the present invention, the flow rate of aluminum oxide particles is adjusted by adjusting the control gas pressure and the control particle seeding pipe diameter of the particle seeding system (2).

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] (1) The present invention can accurately provide the ground erosion resistance test accuracy of the throat liner and gas rudder heat protection material, obtain a reasonable heat protection thickness of the throat liner and gas rudder, and provide useful help for the heat protection design of the throat liner and gas rudder.

[0023] (2) Using aluminum oxide particles, the main product of solid rocket engine combustion, as the test working medium can significantly improve the accuracy of throat liner and gas rudder erosion resistance test and more realistically simulate the environment of throat liner and gas rudder materials in actual operation.

[0024] (3) The present invention conducts erosion resistance test research on throat liner material and gas rudder material on ground electric arc heater equipment. It has many advantages such as short test preparation cycle, low test cost and low equipment power. It can be widely used in the erosion resistance test research of throat liner and gas rudder material.

[0025] (4) The test method and test device of the present invention can conduct ground tests to assess the erosion resistance of the throat liner material and gas rudder of solid rocket engines; the arc power required by the test device is adjustable, the test conditions are widely covered, and orbit simulation can be performed for different test conditions during the test. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the experimental apparatus of the present invention.

[0027] Figure 2 This is a schematic diagram of an aluminum oxide particle distributing gun.

[0028] Figure 3 This is a diagram of the shortest nozzle structure based on Sivells. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0030] A throat liner and gas rudder material erosion resistance testing device includes an arc heater 1, a particle seeding system 2, and a supersonic nozzle 3, the specific structure of which is as follows: Figure 1 As shown. Figure 1 The model shown is generally provided by the party proposing the experiment. The nozzle size is determined according to the model. The electric arc heater is a general-purpose device, mainly used to heat the air. After the particle seeding gun sprays aluminum oxide particles into the high-temperature air, they are accelerated together with the airflow through the supersonic nozzle and collide with the model surface to complete the experimental simulation process.

[0031] The electric arc heater 1 generates high-temperature air, which is then sent into the high-temperature air upstream of the supersonic nozzle 3 via the particle seeding system 2. The particles are accelerated together with the high-temperature air through the supersonic nozzle 3. The accelerated particles flow parallel over the throat liner and the surface of the gas rudder material (i.e., act on the model surface), which more realistically conducts a thermal erosion test on the throat liner and the gas rudder material, and evaluates and analyzes the erosion resistance performance of the heat-resistant material.

[0032] The flow rate of aluminum oxide particles can be adjusted according to the experimental simulation requirements by changing the control gas pressure and the diameter of the particle seeding pipe in the particle seeding system. The opening of the particle seeding gun in particle seeding system 2 is on the leeward side of the airflow. To ensure smooth particle seeding, an aluminum oxide particle seeding gun is specially designed and manufactured. Figure 2 As shown, its structure adopts a water-cooled jacket structure. Alumina particles flow out through the upper pipe and enter the nozzle for acceleration under the action of the pressure difference between the upstream and downstream. This alumina particle seeding gun overcomes the disadvantage of the high viscosity of alumina particles, realizes the smooth seeding of alumina particles, and ensures the uniformity of the particle field at the nozzle outlet to meet the test requirements.

[0033] like Figure 3 As shown, the supersonic nozzle 3 is based on tungsten-copper alloy and adopts the shortest supersonic nozzle design method. By setting the axial Mach number distribution to calculate the wall profile, the internal profile of the nozzle is designed to ensure that the ground aerodynamic thermal erosion test equipment meets the test requirements and has a long service life and good test repeatability.

[0034] The test method includes the following steps:

[0035] (a) Measure the flow field at the nozzle exit according to the test conditions, and at the same time measure the operating parameters of the electric arc heater;

[0036] (b) Determine the operating parameters of the particle seeding system according to the test conditions, calibrate the flow field of aluminum oxide particles, and determine the particle mass flow rate after the electric arc of the electric arc heater.

[0037] (c) After determining the test conditions, conduct erosion resistance tests on the throat liner and gas rudder materials of the solid rocket engine.

[0038] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0039] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A test apparatus for erosion resistance of throat liner and gas rudder material, characterized in that, It includes an electric arc heater (1), a particle seeding system (2), and a supersonic nozzle (3); The electric arc heater (1) generates high-temperature air, which is then sent into the high-temperature air upstream of the supersonic nozzle (3) through the particle seeding system (2). The particles are accelerated together with the high-temperature air through the supersonic nozzle (3), and the accelerated particles flow parallel over the throat liner and the surface of the gas rudder material.

2. The erosion resistance testing device according to claim 1, characterized in that, The flow rate of aluminum oxide particles can be adjusted according to the needs of the experimental simulation.

3. The erosion resistance testing device according to claim 2, characterized in that, The flow rate of aluminum oxide particles is adjusted by adjusting the control gas pressure and the diameter of the control particle seeding pipe of the particle seeding system (2).

4. The erosion resistance testing device according to claim 1, characterized in that, The opening of the particle seeding gun of the particle seeding system (2) is on the leeward side of the airflow.

5. The erosion resistance testing device according to claim 4, characterized in that, The particle delivery gun adopts a water-cooled jacket structure.

6. The erosion resistance testing device according to claim 1, characterized in that, The dimensions of the supersonic nozzle (3) are determined based on the model.

7. A test method for erosion resistance of throat liner and gas rudder material, characterized in that, The test method using the erosion resistance test apparatus as described in claim 1 includes: S1. According to the test requirements, the flow field at the outlet of the supersonic nozzle (3) is measured, and the operating parameters of the electric arc heater (1) are measured at the same time. S2. Determine the operating parameters of the particle seeding system (2) according to the test conditions, calibrate the flow field of aluminum oxide particles, and determine the particle mass flow rate after the electric arc of the electric arc heater (1). S3. After determining the test conditions, conduct erosion resistance tests on the throat liner and gas rudder materials.

8. The erosion resistance testing device according to claim 1, characterized in that, The flow rate of aluminum oxide particles is adjusted by adjusting the control gas pressure and the diameter of the control particle seeding pipe of the particle seeding system (2).

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