CN113125503B - Measurement method of thermoacoustic instability experiment system for measuring combustion response of propellant - Google Patents
Measurement method of thermoacoustic instability experiment system for measuring combustion response of propellant Download PDFInfo
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- CN113125503B CN113125503B CN202110389954.6A CN202110389954A CN113125503B CN 113125503 B CN113125503 B CN 113125503B CN 202110389954 A CN202110389954 A CN 202110389954A CN 113125503 B CN113125503 B CN 113125503B
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Abstract
The invention discloses a measuring method of a thermoacoustic unstable experimental system for measuring the combustion response of a propellant, which comprises the following steps: step A, a thermoacoustic instability experiment system for measuring the combustion response of a propellant is arranged, and the experiment system comprises: the Rijke pipe is provided with an opening end which is an air inlet end; in the Rijke pipe, and near the air inlet end, a heating net is arranged parallel to the longitudinal section of the Rijke pipe, the heating net is in a shape of a round cake, and a plurality of openings are arranged on the heating net. A mass analyzer is arranged in the middle of the Rijke tube and used for bearing and weighing the propellant; the mass analyzer is connected with the acquisition system through a wire. And B, under the condition that nitrogen is introduced into the Rijke pipe, starting an induction power supply, and heating the heating net. And C, obtaining the pressure and temperature values in the Rijke tube, and deriving. And D, igniting the propellant, and measuring the mass change of the propellant. The thermoacoustic instability experimental system for measuring the combustion response of the propellant generates a continuous pressure oscillation in the Rijke pipe, and is closer to the real working environment in the engine.
Description
Technical Field
The invention belongs to the technical field of thermoacoustic instability test, and particularly relates to a measurement method of a thermoacoustic instability experimental system for measuring the combustion response of a propellant.
Background
In the working process of the solid rocket engine, propellant combustion heat release and sound field coupling can occur in the combustion chamber, irregular and periodical pressure oscillation is generated, the internal trajectory curve is abnormal due to light weight, the engine shell is broken and even exploded due to heavy weight, and disastrous results are caused. This irregularly oscillating and evolving process caused by combustion is known as combustion instability.
Unstable combustion of solid rocket engines can be divided into two main categories of acoustic instability and non-acoustic instability according to the occurrence mechanism. Acoustic instability is the result of the interaction of the combustion process with acoustic processes in the engine cavity, and is characterized by a frequency of pressure oscillations that substantially coincides with the natural frequency of the cavity. The solid rocket engine combustion chamber is approximately an acoustic cavity, and the coupling action of the acoustic process in the engine combustion chamber and the propellant combustion can cause self-excitation oscillation. Acoustic instabilities in solid rocket engines are essentially continuous effects of acoustic oscillations in the combustion chamber under the action of the propellant combustion, even with increased oscillations. The acoustic unstable combustion can be classified into linear unstable combustion and nonlinear unstable combustion according to the variation of the sound pressure amplitude. Assuming no damping in the engine, the acoustic energy rate of change can be expressed as how much acoustic energy gain is provided for the combustion response, or as the amount of amplified acoustic oscillation capability, if only the propellant combustion response amplifies the acoustic oscillation. However, in a practical engine, since various gain and damping factors exist simultaneously, the amplification and attenuation of the acoustic oscillation are the combined result of the various factors. The main acoustic energy gain in a solid rocket engine combustion chamber is derived from the combustion response of the propellant, and can be divided into pressure response and velocity response according to the response source. As a major gain factor for combustion instability, a response function is typically characterized. How to obtain such a response function is very tricky both theoretically and engineering.
Currently, the measurement of the combustion response function of a propellant generally employs a T-burner and a rotary valve. The T-shaped burner is mainly characterized in that the spray pipe is arranged in the middle of the combustion chamber, so that the loss of sound energy can be reduced, and the vibration can be easily excited. The device has the advantages of simple structure, convenient operation and the like, and is widely applied, but the device also has the defects of high cost, test error up to 30-50%, difficulty in developing low-frequency experiments and the like. Aiming at the defects of the T-type burner method, a rotary valve method is provided subsequently, and the method has the advantages of wide testing frequency domain, good economic applicability, closest testing result to an actual engine, capability of carrying out an aluminum-containing propellant experiment, extremely high requirement on the testing precision of an experiment measurement and control system, but the defects of high probe abrasion, large testing error, large data quantity, complex device and operation flow and the like. The above disadvantages limit the wide application of rotary valve processes.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a measuring method of a thermoacoustic instability experimental system for measuring the combustion response of a propellant, which generates continuous pressure oscillation in a Rijke pipe and is closer to the real working environment in an engine.
In order to solve the technical problems, the technical scheme adopted by the invention is that a measurement method of a thermoacoustic instability experiment system for measuring the combustion response of a propellant is as follows:
step A, a thermoacoustic instability experiment system for measuring the combustion response of a propellant is arranged, and the experiment system comprises: the Rijke pipe is provided with an opening at one end and a closed end, and the opening end is an air inlet end; a heating net is arranged in the Rijke pipe and close to the air inlet end and parallel to the longitudinal section of the Rijke pipe, the heating net is in a round cake shape, and a plurality of openings are arranged on the heating net for gas flow; a heat insulation ring is sleeved on the periphery of the outer side wall of the heating net, and the outer side wall of the heat insulation ring is tightly attached to the inner wall of the Rijke pipe;
an induction coil is sleeved on the outer wall of the Rijke pipe, the induction coil is connected with an induction power supply, and after power is supplied, the induction coil is used for heating a heating net; a mass analyzer is arranged in the middle of the Rijke tube and used for bearing and weighing the propellant; the mass analyzer is connected with the acquisition system through a wire.
Step B, under the condition that nitrogen is introduced into the Rijke pipe, an induction power supply is started, the heating net is heated until the heating net is in a luminous state, and the induction power supply is disconnected;
step C, obtaining the pressure and temperature values in the Rijke tube and deriving;
and D, igniting the propellant, and measuring the mass change of the propellant.
Further, the open end of the Rijke tube is communicated with a damping chamber, and the diameter of the damping chamber is larger than that of the Rijke tube; the front end of the damping chamber is provided with an air inlet which is used for being connected with the gas supply device.
Further, a glass window is arranged in the middle of the Rijke tube and positioned in the propellant combustion area for observing the combustion state of the propellant.
Further, a plurality of round holes are formed in the Rijke pipe at intervals along the length direction of the Rijke pipe, and a pressure sensor is arranged in each round hole.
Further, the mass analyzer comprises an objective table, wherein an eddy current sensor probe is arranged at the lower part of the objective table; the objective table is a plate body, and one side of the objective table is connected with the rack through a cantilever beam which is horizontally arranged.
Further, the Rijke tube is made of zirconia.
The invention has the following advantages: 1. the high-frequency induction microwave electric heater is adopted for heating, so that the Rijke tube can generate larger amplitude at high temperature, stable thermoacoustic oscillation experimental environment with larger pressure amplitude is generated, and a foundation is provided for propellant experiments.
2. The cantilever beam mass analyzer is arranged on the Rijke tube and is used for measuring the propellant combustion response in the thermo-acoustic oscillation environment.
3. And a glass window is arranged for observing the combustion process of the propellant in the oscillation environment.
Drawings
FIG. 1 is a schematic diagram of a thermoacoustic instability experiment system for measuring the combustion response of a propellant.
Fig. 2 is a schematic structural diagram of a mass analyzer according to the present invention.
FIG. 3 is a schematic diagram of the sensor and site locations.
Fig. 4 is a schematic view of the structure of a heating net covered with a heat insulating ring.
In the figure: 1. the mass analyzer comprises an induction power supply, a mass analyzer, an induction coil, a Rijke tube, a damping chamber, an air inlet, a rack, a cantilever beam, a stage, an eddy current sensor probe, a cable, a thermocouple, a pressure sensor, a graphite heating net and a heat insulation ring.
Detailed Description
In the measuring method of the thermoacoustic instability experimental system for measuring the combustion response of the propellant,
step a, a thermo-acoustic instability test system for measuring the combustion response of a propellant is provided, as shown in fig. 1, 3 and 4, comprising: a Rijke pipe 4 with one end open and one end closed, and the open end is an air inlet end; a heating net 14 is arranged in the Rijke pipe 4 and near the air inlet end and is parallel to the longitudinal section of the Rijke pipe 4, the heating net 14 is in a round cake shape, and a plurality of holes are arranged on the heating net 14 for gas flow; a heat insulation ring 15 is sleeved on the periphery of the outer side wall of the heating net 14, and the outer side wall of the heat insulation ring 15 is tightly attached to the inner wall of the Rijke pipe 4.
An induction coil 3 is sleeved on the outer wall of the Rijke tube 4, the induction coil 3 is connected with an induction power supply 1, and after power is supplied, the induction coil 3 is used for heating a heating net 14; a mass analyser is provided in the middle of the Rijke tube 4 for carrying and weighing the propellant. The Rijke tube 4 is used for providing a thermoacoustic oscillation experimental environment under the condition of heating and gas filling. The induction coil 3 is made of copper. The Rijke tube 4 is made of zirconia.
And B, under the condition that nitrogen is introduced into the Rijke pipe 4, starting the induction power supply 1, heating the heating net 14 until the heating net 14 is in a luminous state, and switching off the induction power supply 1.
And C, obtaining the pressure and temperature values in the Rijke pipe 4 and deriving.
And D, igniting the propellant, and measuring the mass change of the propellant.
The air inlet end of the Rijke pipe 4 is communicated with the damping chamber 5, the front end of the damping chamber 5 is provided with an air inlet 6, and the air inlet 6 is used for being connected with a gas supply device. And nitrogen is introduced in the experimental process, the gas flow can be controlled through the damping chamber 5, and meanwhile, the acoustic boundary of the pipe of the Rijke pipe 4 is ensured not to be changed.
The central part of the Rijke tube 4 is provided with a glass window in the propellant combustion area for observing the combustion process of the propellant. A plurality of round holes are arranged on the Rijke pipe 4 at intervals along the length direction, and a pressure sensor is respectively arranged in each round hole.
As shown in fig. 2, the mass analyzer includes a stage 9, and an eddy current sensor probe 10 is provided at a lower portion of the stage 9; the objective table 9 is a plate body, and one side of the objective table is connected with the rack 7 through a cantilever beam 8 horizontally arranged. The eddy current sensor probe 10 is connected to a controller by a cable 11.
The principle of the Rijke tube 4 is by the rayleigh criterion: the air near the heating device is heated to reduce the expansion density, and the temperature is reduced and the density is increased after the air moves upwards to contact with the pipe wall. This periodic process results in a periodic distribution of air density within the tube, creating pressure oscillations within the tube, which in turn are used in propellant experiments to observe the properties of the propellant in an oscillating environment.
More specifically, some dimensions of the thermoacoustic instability test system for measuring the combustion response of a propellant are as follows: the damping chamber 5 has a diameter of 500mm and a length of 500mm, and an air inlet 6 is arranged at the end part and is connected with an air path, and the air flow is controlled. The diameter of the damping chamber 5 is larger than the diameter of the Rijke tube 4 so that the acoustic boundaries of the Rijke tube 4 are unchanged; the Rijke tube 4 is 1000mm long, 100mm in inner diameter and 140mm in outer diameter, and meanwhile 4 circular holes with diameters of 18mm are formed in 150mm,210mm,280mm and 350mm above the Rijke tube 4 and are used for installing a temperature measuring device, namely a thermocouple. A 20mm round hole was made 500mm for connection so that the mass analyzer 2 power was derived therefrom.
Four circular holes were provided at 150mm,300mm,500mm,750mm side portions of the Rijke tube 4 for mounting the pressure sensor 13, and the diameter of the pressure sensor 13 was 14mm. While a 50X 50mm glass window was opened at 500 mm. The graphite heating net 14 is made into a round cake shape, and a plurality of holes are distributed on the round cake shape for nitrogen to flow, and the diameter of the round cake is 60mm; an annular heat insulation ring 15 is sleeved on the periphery of the edge of the graphite heating net 14, the heat insulation ring 15 adopts carbon felt, and the diameter of the heating net 14 and the heat insulation ring 15 combined together is 100mm. At one quarter of the length inside the Rijke tube 4, the side edges of the insulating ring 15 closely fit the inner wall of the Rijke tube 4.
The specific dimensions of the mass analyzer are as follows: the height of the mass analyzer is 60mm, the length of the cantilever beam 8 is 80mm, the eddy current sensor probe 10 adopts M12 threads, and the radius of the objective table 9 is 7.5mm.
The thermoacoustic instability experiment system for measuring the combustion response of the propellant in the invention has the following working procedures: the thermocouple 12 and the pressure sensor 13 are installed first, then the gas cylinder is opened, and nitrogen is introduced into the device through the gas path. After nitrogen is introduced, a power supply is turned on to preheat the heating device, then the power is increased to increase the temperature of the heater to 2000K, the high temperature is maintained for 5-10 seconds, the electromagnetic induction power supply is turned off, and the pressure data and the temperature data inside the Rijke tube 4 are measured through the pressure sensor 13. After the induction heating power supply is disconnected, the ignition power supply is turned on to ignite the propellant, and the combustion speed of the propellant is measured by the mass analyzer, so that the combustion response function of the propellant under the oscillation pressure is obtained.
More specific experimental steps are as follows:
1. whether the acquisition system is normal or not is tested, namely whether the pressure sensor is normal or not is tested, the acquisition system is opened, whether the pressure value is balanced near the atmospheric pressure or not is observed, and if so, the acquisition system is normal;
2. a carbon felt heat insulation ring 15 is sleeved on the side wall of the heating net 14 for one circle, and the carbon felt heat insulation ring is placed into the zirconia Rijke pipe 4;
3. connecting a gas cylinder, a pressure reducing valve and a damping chamber 5, regulating the pressure of a nitrogen path gas source to 3-5Mpa, and checking whether the air tightness is good;
4. starting the heater to circulate cooling water, and maintaining the high-frequency induction microwave electric heater to work for a long time;
5. opening a nitrogen valve, and introducing nitrogen into the pipeline to enable the heating net 14 to be in a nitrogen environment;
6. starting an induction power supply, and starting a high-frequency induction microwave electric heater to heat the heating net 14;
7. heating for about 20s, and turning off the power supply when the heating net 14 is in a light-emitting state;
8. the acquisition system starts to acquire data;
9. the acquired data are led out, thermocouple voltage values are read through Origin post-processing software and converted into temperature values, and pressure sensor voltage values are converted into pressure values;
10. starting an ignition power supply, igniting the propellant, and measuring the mass change of the propellant;
11. the burning speed of the propellant is measured, and the burning response function of the propellant is obtained through calculation.
One of the key points of the present invention is to construct a thermo-acoustic unstable environment, in which a large amplitude Rijke tube 4 is used. The heating power supply uses the induction power supply 1, so that the required high power can be provided for the heating net 14, the heating net 14 material uses graphite, and can be heated to 2000K under the power of the induction power supply, and a common electric heating system can only be heated to the temperature of less than 1000K, so that the heating power supply is greatly improved compared with the conventional electric heating system. And a second key point is that a mass analyzer is placed in the Rijke tube 4, and a propellant combustion experiment is carried out. After the air flow passes through the heating net 14, pressure oscillation with larger amplitude can be generated in the Rijke pipe 4, a propellant combustion experiment is carried out under the pressure oscillation environment, the combustion speed of the propellant is measured, and the combustion response function of the propellant is obtained. And the third key point is that a glass window is arranged at the place where the mass analyzer is arranged and is used for observing the combustion change of the propellant, so as to obtain the rule of influence of the oscillation pressure on the combustion of the propellant.
Claims (6)
1. A method of measuring a thermoacoustic instability experiment system for measuring the combustion response of a propellant, the method comprising:
step A, a thermoacoustic instability experiment system for measuring the combustion response of a propellant is arranged, and the experiment system comprises:
a Rijke pipe (4) with one end open and one end closed, wherein the open end is an air inlet end;
a heating net (14) is arranged in the Rijke pipe (4) and close to the air inlet end and parallel to the longitudinal section of the Rijke pipe (4), the heating net (14) is in a shape of a round cake, and a plurality of holes are distributed on the heating net for gas flow; a heat insulation ring (15) is sleeved on a circumference of the outer side wall of the heating net (14), and the outer side wall of the heat insulation ring (15) is tightly attached to the inner wall of the Rijke pipe (4);
an induction coil (3) is sleeved on the outer wall of the Rijke tube (4), the induction coil (3) is connected with an induction power supply (1), and after power is supplied, the induction coil (3) is used for heating the heating net (14);
a mass analyzer is arranged in the middle of the Rijke tube (4) and used for bearing and weighing the propellant;
step B, under the condition that nitrogen is introduced into the Rijke pipe (4), an induction power supply (1) is started, the heating net (14) is heated until the heating net (14) is in a luminous state, and the induction power supply (1) is disconnected;
step C, obtaining the pressure and temperature values in the Rijke tube (4) and deriving the values;
and D, igniting the propellant, and measuring the mass change of the propellant.
2. The method for measuring a thermoacoustic instability experiment system for measuring a combustion response of a propellant according to claim 1, wherein the air inlet end of the Rijke tube (4) is in communication with a damping chamber (5), and the diameter of the damping chamber (5) is larger than the diameter of the Rijke tube (4);
an air inlet (6) is formed in the front end of the damping chamber (5), and the air inlet (6) is used for being connected with a gas supply device.
3. A method of measuring a thermoacoustic instability experiment system for a combustion response of a propellant according to claim 1 or 2, wherein the Rijke tube (4) is provided with a glass window in the middle of the combustion area of the propellant for observing the combustion state of the propellant.
4. A method of measuring a thermoacoustic instability experiment system for measuring a combustion response of a propellant according to claim 3, wherein a plurality of temperature measuring holes are provided on the Rijke tube (4) at intervals along its length, and a pressure sensor is installed in each of the temperature measuring holes.
5. The method for measuring the thermoacoustic instability experiment system of the combustion response of the propellant according to claim 4, wherein the mass analyzer comprises a stage (9), an eddy current sensor probe (10) is arranged at the lower part of the stage (9), and the eddy current sensor probe (10) is used for measuring the mass of the propellant at each moment and is connected with a collecting system; the objective table (9) is a plate body, is made of ceramic, and is connected with the rack (7) on one side through a cantilever beam (8) horizontally arranged.
6. The method for measuring the thermoacoustic instability experiment system of the combustion response of a propellant according to claim 5, wherein the Rijke tube (4) is made of zirconia.
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| CN114543984B (en) * | 2022-04-22 | 2022-07-05 | 北京航空航天大学 | Quantitative adjusting device and method for Rijke pipe boundary dissipation |
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