Ceramic matrix ablation experiment platform under action of particle-containing high-temperature and high-pressure combustion gas flow

Abstract

The invention relates to a ceramic matrix ablation experiment platform under the action of particle-containing high-temperature and high-pressure combustion gas flow. The ceramic matrix ablation experiment platform comprises a combustion chamber shell, a front sealing head, a rear sealing head, a solid propellant, an igniter, a positioning nut, a sensor base, a throat liner test piece, a throat liner cover, a test piece bracket and a flat plate test piece, the front end socket and the rear end socket are arranged at the front end and the rear end of the combustion chamber shell and used for sealing the combustion chamber shell, the igniter is arranged on the front end socket, the solid propellant is contained in the combustion chamber shell, and the igniter ignites the solid propellant behind the end cover to generate high-temperature and high-pressure fuel gas flow containing particles to ablate a ceramic-based test piece. According to the experimental device for ablation of the ceramic matrix by the particle-containing high-temperature and high-pressure combustion gas flow, the rule of influence of the particle-containing high-temperature and high-pressure combustion gas flow on the ablation performance of the ceramic matrix is obtained, and data support is provided for perfecting an ablation model.

Description

Technical Field

[0001] The invention relates to the field of ceramic substrate ablation under the action of particle-containing high-temperature and high-pressure gas flow, and provides a ceramic substrate ablation experimental platform under the action of particle-containing high-temperature and high-pressure gas flow to simulate the real ablation environment of ceramic substrate specimens. Background Art

[0002] With the continuous improvement of engine thrust performance, the temperature in the combustion chamber is getting higher and higher. The requirements for the thermomechanical and thermochemical properties of the hot end components such as the engine nozzle throat liner under high heat load are getting higher and higher. Traditional metals and high-temperature alloys can no longer meet their needs. Ceramic matrix composites (CMC) are a composite material with ceramic as the matrix and fiber or particles as the reinforcement phase. It has the advantages of high temperature resistance, low density, high specific strength, oxidation resistance, ablation resistance, high reliability, and easy processing. It can effectively achieve a 50% to 70% reduction in structure, an increase in operating temperature of more than 200°C, and a significant reduction in the amount of cooling gas, thereby improving the efficiency of aircraft engines.

[0003] For ceramic matrix materials, thermochemical ablation and particle erosion are very likely to occur under the action of high temperature and high pressure two-phase flow, which will change the mechanical properties and ablation properties of the ceramic matrix. In order to deeply analyze the influence of high temperature and high pressure gas flow containing particles on the ablation properties of ceramic matrix, obtain the characterization data of ablation characteristics of ceramic matrix specimens under different combustion temperatures, working pressures and ablation times, and improve the ablation model data, an ablation experimental platform for ceramic matrix under the action of high temperature and high pressure gas flow containing particles is needed. Summary of the invention

[0004] In order to simulate the real ablation environment of ceramic-based specimens, the purpose of the present invention is to provide an experimental device for the ablation of ceramic substrates by high-temperature and high-pressure gas flow containing particles, obtain the influence of high-temperature and high-pressure gas flow containing particles on the ablation performance of ceramic substrates, and provide data support for improving the ablation model.

[0005] The present invention is achieved through the following technical solutions.

[0006] A ceramic substrate ablation experimental platform under the action of particle-containing high-temperature and high-pressure gas flow, comprising a combustion chamber shell, a front head, a rear head, a solid propellant, an igniter, a positioning nut, a sensor base, a throat liner test piece, a throat liner cover, a test piece bracket and a flat test piece; the front head and the rear head are arranged at the front and rear ends of the combustion chamber shell, and are used to seal the combustion chamber shell; the igniter is arranged on the front head, and the solid propellant is installed in the combustion chamber shell. The igniter ignites the solid propellant behind the end cover to generate a particle-containing high-temperature and high-pressure gas flow The ceramic-based specimen is ablated; the sensor base is arranged on the combustion chamber shell, and the sensor base is connected to a high-frequency pressure sensor and a tungsten-rhenium thermocouple to measure the working pressure and working temperature inside the combustion chamber shell; the throat liner specimen is fixed to the rear head through a throat liner cover, and the specimen bracket is fixedly installed on the throat liner cover, and the flat specimen is fixed to the specimen bracket through a positioning nut, and the distance between the flat specimen and the throat liner cover is changed by adjusting the positioning nut, thereby changing the distance between the flat specimen and the gas flow, and measuring the temperature of the flat specimen by a colorimetric high temperature thermometer.

[0007] Furthermore, the solid propellant is a hydroxybutyl propellant containing 17% aluminum, adopts an end-face charge configuration, and has a diameter of 90 mm. The ablation time is controlled by adopting propellant charges of different thicknesses.

[0008] Furthermore, the rear end cap is a convergent rear end cap, which is used to accelerate particles. The particles flow out through the throat liner specimen along with the high-temperature and high-pressure gas and act on the external flat specimen.

[0009] Furthermore, the flat specimen is a ceramic-based specimen.

[0010] Furthermore, the throat liner specimen is a ceramic-based specimen, and throat liners with different throat sizes are used to change the working pressure, and the influence of the working pressure and working time on the ablation performance of the ceramic-based specimen is analyzed.

[0011] The ablation experiment of the ceramic substrate by high-temperature and high-pressure gas flow containing particles using the above platform includes the following steps:

[0012] Step 1: Load the solid propellant into the combustion chamber casing and seal it using the front and rear heads.

[0013] Step 2: Install an igniter on the front head to ignite the solid propellant.

[0014] Step three, install the throat liner specimen on the rear head. The throat liner specimen is a ceramic-based specimen. The working pressure is changed by using throat liner specimens of different sizes and fixed by the throat liner cover.

[0015] Step 4: Install the specimen holder and the flat specimen on the throat liner cover. The flat specimen is a ceramic matrix specimen. The distance between the gas flow and the flat specimen is controlled by adjusting the positioning nut on the specimen holder.

[0016] Step 5: Install a high-frequency pressure sensor and a tungsten-rhenium thermocouple on the sensor base on the combustion chamber shell to measure the working pressure and working temperature inside the combustion chamber.

[0017] Step six, use an igniter to ignite the solid propellant. After the solid propellant is ignited, a high-temperature and high-pressure combustion gas flow containing particles is generated, which ablates the throat liner specimen and the flat plate specimen.

[0018] Step seven: Use a colorimetric thermometer to measure the temperature of the flat specimen, use a high-frequency pressure sensor and a tungsten-rhenium thermocouple to measure the working pressure and temperature in the combustion chamber shell, and analyze the influence of working pressure and working time on the ablation performance of the ceramic-based specimen.

[0019] Step 8: The ablation performance of the material is usually evaluated by the ablation rate, which is usually the mass ablation rate R. m and line ablation rate R d To express it, the ablation characterization parameters of the ceramic-based throat liner and the flat specimen are calculated according to equations (1) and (2). The ablation effect of the particle-containing gas is decoupled and analyzed by the single factor analysis method, and the influence of the particle-containing high-temperature and high-pressure gas flow on the ablation performance of the ceramic-based is obtained.

[0020]

[0021] Compared with the prior art, the advantages of the present invention are as follows: the present invention provides an experimental device for ablation of ceramic substrates by high-temperature and high-pressure gas flow containing particles, obtains the influence of high-temperature and high-pressure gas flow containing particles on the ablation performance of ceramic substrates, and provides data support for improving the ablation model. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural cross-sectional view of the ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles of the present invention;

[0023] Figure 2 It is a three-dimensional diagram of the ceramic matrix ablation experimental platform under the action of the particle-containing high-temperature and high-pressure gas flow of the present invention;

[0024] Figure 3 It is a three-dimensional picture of the throat lining specimen of the ceramic matrix ablation test platform under the action of the particle-containing high-temperature and high-pressure gas flow of the present invention;

[0025] The reference numerals in the drawings are: front head 1, combustion chamber casing 2, sensor base 3, rear head 4, throat liner specimen 5, throat liner cover 6, flat specimen 7, specimen bracket 8, solid propellant 9, igniter 10, and positioning nut 11. DETAILED DESCRIPTION

[0026] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0027] like Figures 1 to 3 As shown, a ceramic matrix ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles comprises a combustion chamber shell 2, a front head 1, a rear head 4, a solid propellant 9, an igniter 10, a positioning nut 11, a sensor base 3, a throat liner specimen 5, a throat liner cover 6, a specimen bracket 8 and a flat specimen 7; the front head 1 and the rear head 4 are arranged at the front and rear ends of the combustion chamber shell 2, and are used to seal the combustion chamber shell 2, the igniter 10 is arranged on the front head 1, the solid propellant 9 is installed in the combustion chamber shell 2, and the igniter 10 ignites the solid propellant 9 behind the end cover to generate high-temperature and high-pressure gas containing particles. The compressed gas flow ablates the ceramic-based specimen; the sensor base 3 is arranged on the combustion chamber shell 2, and the sensor base 3 is connected to a high-frequency pressure sensor and a tungsten-rhenium thermocouple to measure the working pressure and working temperature inside the combustion chamber shell 2; the throat liner specimen 5 is fixed on the rear head 4 through the throat liner cover 6, and the specimen bracket 8 is fixedly installed on the throat liner cover 6, and the flat specimen 7 is fixed to the specimen bracket 8 through a positioning nut 11. The distance between the flat specimen 7 and the throat liner cover 6 is changed by adjusting the positioning nut 11, thereby changing the distance between the flat specimen 7 and the gas flow, and measuring the temperature of the flat specimen 7 by a colorimetric high temperature thermometer.

[0028] Furthermore, the solid propellant 9 is a HTPB propellant containing 17% aluminum, adopts an end-face charge configuration, and has a diameter of 90 mm. The ablation time is controlled by adopting propellant charges of different thicknesses.

[0029] Furthermore, the rear end cap 4 is a convergent rear end cap, which is used to accelerate particles. The particles flow out through the throat liner specimen 5 along with the high-temperature and high-pressure gas and act on the external flat specimen 7.

[0030] Furthermore, the flat specimen 7 is a ceramic-based specimen.

[0031] Furthermore, the throat liner specimen 5 is a ceramic-based specimen, and throat liners with different throat sizes are used to change the working pressure, and the influence of the working pressure and working time on the ablation performance of the ceramic-based specimen is analyzed.

[0032] The ablation experiment of the ceramic substrate by high-temperature and high-pressure gas flow containing particles using the above platform includes the following steps:

[0033] Step 1: Load the solid propellant 9 into the combustion chamber casing 2 and seal it using the front head 1 and the rear head 4.

[0034] Step 2: Install an igniter 10 on the front head 1 to ignite the solid propellant.

[0035] Step three, install the throat liner specimen 5 on the rear head 4. The throat liner specimen is a ceramic-based specimen. The working pressure is changed by using throat liner specimens of different sizes, and it is fixed by the throat liner cover 6.

[0036] Step 4: Install the specimen holder 8 and the flat specimen 7 on the throat liner cover 6. The flat specimen 7 is a ceramic matrix specimen. The distance between the gas flow and the flat specimen is controlled by adjusting the positioning nut 11 on the specimen holder.

[0037] Step five: install a high-frequency pressure sensor and a tungsten-rhenium thermocouple on the sensor base 3 on the combustion chamber housing 2 to measure the working pressure and working temperature inside the combustion chamber.

[0038] Step six, using an igniter to ignite the solid propellant 9, after the solid propellant is ignited, a high-temperature and high-pressure gas flow containing particles is generated, which ablates the throat liner specimen and the flat plate specimen.

[0039] Step seven, use a colorimetric thermometer to measure the temperature of the flat specimen 7, use a high-frequency pressure sensor and a tungsten-rhenium thermocouple to measure the working pressure and temperature in the combustion chamber shell, and analyze the influence of working pressure and working time on the ablation performance of the ceramic-based specimen.

[0040] Step 8: The ablation performance of the material is usually evaluated by the ablation rate, which is usually the mass ablation rate R. m and line ablation rate R d To express it, the ablation characterization parameters of the ceramic-based throat liner and the flat specimen are calculated according to equations (1) and (2). The ablation effect of the particle-containing gas is decoupled and analyzed by the single factor analysis method, and the influence of the particle-containing high-temperature and high-pressure gas flow on the ablation performance of the ceramic-based is obtained.

[0041]

[0042] The above description is only a preferred embodiment of the present invention, and does not limit the implementation mode and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles, characterized in that: The invention comprises a combustion chamber casing (2), a front sealing head (1), a rear sealing head (4), a solid propellant (9), an igniter (10), a positioning nut (11), a sensor base (3), a throat liner test piece (5), a throat liner cover (6), a test piece support (8) and a flat test piece (7); the front sealing head (1) and the rear sealing head (4) are arranged at the front and rear ends of the combustion chamber casing (2) and are used to seal the combustion chamber casing (2); the igniter (10) is arranged on the front sealing head (1); the solid propellant (9) is installed in the combustion chamber casing (2); the sensor base (3) is arranged on the combustion chamber casing (2 ), the sensor base (3) is connected to a high-frequency pressure sensor and a tungsten-rhenium thermocouple for measuring the working pressure and working temperature inside the combustion chamber shell (2); the throat liner specimen (5) is fixed to the rear head (4) through a throat liner cover (6), the specimen bracket (8) is fixedly installed on the throat liner cover (6), and the flat specimen (7) is fixed to the specimen bracket (8) through a positioning nut (11). By adjusting the positioning nut (11), the distance between the flat specimen (7) and the throat liner cover (6) is changed, thereby changing the distance between the flat specimen (7) and the gas flow, and measuring the temperature of the flat specimen (7) by a colorimetric high temperature thermometer.

2. The ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles according to claim 1 is characterized in that: The solid propellant (9) is a hydroxybutyl propellant containing 17% aluminum, adopts an end-face charging configuration, and has a diameter of 90 mm.

3. The ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles according to claim 1 is characterized in that: The rear end cap (4) is a convergent rear end cap, which is used to accelerate particles. The particles flow out through the throat liner specimen (5) along with the high-temperature and high-pressure combustion gas and act on the external flat specimen (7).

4. The ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles according to claim 1, characterized in that: The flat plate test piece (7) is a ceramic-based test piece.

5. The ceramic substrate ablation experimental platform under the action of high-temperature and high-pressure gas flow containing particles according to claim 1, characterized in that: The throat lining test piece (5) is a ceramic-based test piece.

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