CN113125503A - Measurement method of thermoacoustic instability experimental system for measuring propellant combustion response - Google Patents
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Abstract
The invention discloses a measuring method of a thermoacoustic instability experimental system for measuring propellant combustion response, which comprises the following steps: step A, setting a thermoacoustic instability experimental system for measuring propellant combustion response, wherein the experimental system comprises: the opening end of the Rijke pipe is an air inlet end; a heating net is arranged in the Rijke tube and close to the air inlet end and is parallel to the longitudinal section of the Rijke tube, the heating net is in a round cake shape, and a plurality of openings are distributed on the heating net. A mass analyzer is arranged in the middle of the Rijke tube and is used for bearing and weighing the propellant; the quality analyzer is connected with the acquisition system in a line. And step B, starting an induction power supply and heating the heating net under the condition that nitrogen is introduced into the Rijke tube. And C, obtaining and exporting the pressure and temperature values in the Rijke tube. And D, igniting the propellant, and measuring the mass change of the propellant. The thermo-acoustic instability experimental system for measuring the propellant combustion response is used for generating continuous pressure oscillation in the Rijke tube, 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 measuring method of a thermoacoustic instability experimental system for measuring propellant combustion response.
Background
During the working process of the solid rocket engine, the coupling of propellant combustion heat release and a sound field can occur in a combustion chamber, irregular and periodic pressure oscillation is generated, the inner ballistic curve is abnormal if the pressure oscillation is small, and the shell of the engine is cracked and even exploded if the pressure oscillation is large, so that disastrous results are caused. This combustion-induced ringing and progression is referred to as combustion instability.
Unstable combustion in solid rocket engines can be classified into acoustic instability and non-acoustic instability according to the mechanism of occurrence. Acoustic instability is the result of the interaction of the combustion process with acoustic processes in the engine cavity and is characterized by pressure oscillations having a frequency substantially identical to the natural frequency of the cavity. The combustion chamber of the solid rocket engine is approximately an acoustic cavity, and self-excited acoustic oscillation can be caused by the coupling action of an acoustic process and propellant combustion in the combustion chamber of the engine. The acoustic instability in solid rocket engines is essentially a continuous action of acoustic oscillations in the combustion chamber under the action of propellant combustion, even an oscillation aggravation. The acoustically unstable combustion can be classified into a linear unstable combustion and a nonlinear unstable combustion according to a variation in sound pressure amplitude. Assuming that there is no damping in the engine, and only the propellant combustion response amplifies the acoustic oscillations, the rate of change of acoustic energy can be expressed as how much gain of acoustic energy is provided to the combustion response, or how much the acoustic oscillation capability is amplified. However, in an actual engine, since various gain and damping factors coexist, amplification and attenuation of acoustic oscillation are the result of the combined action of 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 speed response according to the response source. As a primary gain factor for combustion instability, it is commonly characterized by a response function. How to obtain such a response function is extremely troublesome, both theoretically and engineering.
The measurement of the propellant combustion response function currently uses T-burners and rotary valves. The T-shaped combustor is mainly characterized in that a spray pipe is arranged in the middle of a combustion chamber, so that the acoustic energy loss can be reduced, and the oscillation is easy to excite. The device has the advantages of simple structure, convenient operation and the like, is widely applied, but also has the defects of high cost, high test error of 30-50%, difficulty in carrying out low-frequency experiments and the like. The method has the advantages that the method is wide in test frequency domain, good in economic applicability, most close to an actual engine in test result, capable of developing an aluminum-containing propellant experiment and extremely high in test precision requirement of an experiment measurement and control system, and has the defects of probe abrasion, large test error, large data volume, complex device and operation flow and the like. The above disadvantages limit the wide application of the rotary valve method.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a measurement method for a thermo-acoustic instability experimental system for measuring propellant combustion response, aiming at the defects of the prior art, wherein a continuous pressure oscillation is generated in a Rijke tube, and the continuous pressure oscillation is closer to the real working environment in an engine.
In order to solve the technical problems, the invention adopts the technical scheme that the measuring method of the thermoacoustic instability experimental system for measuring the propellant combustion response comprises the following steps:
step A, setting a thermoacoustic instability experimental system for measuring propellant combustion response, wherein the experimental system comprises: one end of the Rijke tube is open, the other end of the Rijke tube is closed, and the open end is an air inlet end; a heating net is arranged in the Rijke tube and close to the air inlet end and is parallel to the longitudinal section of the Rijke tube, the heating net is in a round cake shape, and a plurality of openings are distributed on the heating net for air flow; a heat insulation ring is annularly sleeved on the outer side wall of the heating net in a circle, 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 and is connected with an induction power supply, and after power is supplied, the induction coil is used for heating the heating net; a mass analyzer is arranged in the middle of the Rijke tube and is used for bearing and weighing the propellant; the quality analyzer is connected with the acquisition system in a line.
B, starting an induction power supply under the condition that nitrogen is introduced into the Rijke tube, heating the heating net until the heating net is in a luminous state, and disconnecting the induction power supply;
c, obtaining pressure and temperature values in the Rijke tube and deriving the pressure and temperature values;
and D, igniting the propellant, and measuring the mass change of the propellant.
Further, the opening end of the Rijke pipe is communicated with a damping chamber, and the diameter of the damping chamber is larger than that of the Rijke pipe; the front end of the damping chamber is provided with an air inlet which is used for being connected with an air supply device.
Further, a glass window is arranged in the middle of the Rijke tube and positioned in a propellant combustion area and used for observing the combustion state of the propellant.
Furthermore, a plurality of round holes are arranged on the Rijke pipe at intervals along the length direction of the Rijke pipe, and a pressure sensor is respectively arranged in each round hole.
Furthermore, the mass analyzer comprises an object stage, wherein an eddy current sensor probe is arranged at the lower part of the object stage; 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.
Furthermore, 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, a stable thermoacoustic oscillation experimental environment with larger pressure intensity and amplitude is generated, and a foundation is provided for propellant experiments.
2. And the cantilever beam mass analyzer is arranged on the Rijke tube and is used for measuring propellant combustion response in the thermoacoustic 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 structural diagram of a thermoacoustic instability experimental system for measuring propellant combustion response.
Fig. 2 is a schematic view of the structure of the mass analyzer of the present invention.
FIG. 3 is a schematic diagram of the structure of the sensor and the position of the measuring point.
Fig. 4 is a schematic structural diagram of a heating net sleeved with an insulating ring.
In the figure: 1. the system comprises an induction power supply, 2 a mass analyzer, 3 an induction coil, 4 a Rijke tube, 5 a damping chamber, 6 an air inlet, 7 a rack, 8 a cantilever beam, 9 an objective table, 10 an eddy current sensor probe, 11 a cable, 12 a thermocouple, 13 a pressure sensor, 14 a graphite heating net and 15 a heat insulation ring.
Detailed Description
The invention relates to a measuring method of a thermoacoustic instability experimental system for measuring propellant combustion response,
step a, setting a thermoacoustic instability experimental system for measuring propellant combustion response, as shown in fig. 1, 3 and 4, the experimental system comprising: a Rijke tube 4, one end of which is open and the other end is closed, and 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 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 openings are distributed on the heating net 14 and used for air flowing; a heat insulation ring 15 is annularly sleeved on the outer side wall of the heating net 14 in a circle, 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 arranged in the middle inside the Rijke tube 4 for carrying and weighing the propellant. Under the condition of heating and gas introduction, the Rijke tube 4 is used for providing a thermo-acoustic oscillation experimental environment. The induction coil 3 is made of copper. The Rijke tube 4 is made of zirconia.
And step B, starting the induction power supply 1 under the condition that nitrogen is introduced into the Rijke tube 4, heating the heating net 14 until the heating net 14 is in a luminous state, and disconnecting the induction power supply 1.
And C, obtaining and exporting the pressure and temperature values in the Rijke pipe 4.
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 an air supply device. And nitrogen is introduced in the experiment process, the gas flow can be controlled through the damping chamber 5, and the acoustic boundary of the Rijke pipe 4 pipeline is ensured not to be changed.
And a glass window is arranged in the middle of the Rijke tube 4 and positioned in a propellant combustion area and used 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 disposed at a lower portion of the stage 9; the object stage 9 is a plate, one side of which is connected with the rack 7 through a cantilever beam 8 which is horizontally arranged. The eddy current sensor probe 10 is connected to the controller via a cable 11.
The principle of the Rijke tube 4 is by the rayleigh criterion: the air near the heating device expands less in density after being heated, and the temperature is reduced and the density is increased after the air moves upwards to contact with the pipe wall. The periodic process causes the periodic distribution of air density in the pipe, generates pressure oscillation in the pipe, is further used for propellant experiments, and observes the properties of the propellant in an oscillation environment.
More specifically, some dimensions of the thermo-acoustic instability experimental system for measuring propellant combustion response are as follows: the diameter of the damping chamber 5 is 500mm, the length is 500mm, the end part is provided with an air inlet 6 to be connected with an air path, and the air flow is controlled simultaneously. The diameter of the damping chamber 5 is greater than the diameter of the Rijke tube 4 so that the acoustic boundary of the Rijke tube 4 does not change; the Rijke tube 4 is 1000mm long, the internal diameter is 100mm, the external diameter is 140mm, and 4 round holes with the diameter of 18mm are arranged at the positions of 150mm, 210mm, 280mm and 350mm above the Rijke tube 4 and are used for installing a temperature measuring device, namely a thermocouple. A 20mm circular hole is opened at 500mm for connection so that the power supply of the mass analyzer 2 is led out therefrom.
Four round holes are arranged at the positions of 150mm, 300mm, 500mm and 750mm at the side part of the Rijke pipe 4 for installing the pressure sensor 13, and the diameter of the pressure sensor 13 is 14 mm. At the same time, a 50X 50mm glass window is opened at 500 mm. The graphite heating net 14 is made into a round cake shape, a plurality of openings are distributed on the graphite heating net for nitrogen flowing, and the diameter of the graphite heating net is 60 mm; an annular heat insulation ring 15 is sleeved on the edge of the graphite heating net 14 in a circle, the heat insulation ring 15 is made of carbon felt, and the diameter of the combination of the heating net 14 and the heat insulation ring 15 is 100 mm. The side edges of the insulating ring 15 closely abut the inner wall of the Rijke tube 4 at one quarter of the length inside 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 object stage 9 is 7.5 mm.
The working process of the thermoacoustic instability experimental system for measuring propellant combustion response in the invention is as follows: firstly installing a thermocouple 12 and a pressure sensor 13, then opening a gas cylinder, and introducing nitrogen into the device through a 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 disconnected, and pressure data and 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, the burning speed of the propellant is measured by the mass analyzer, and then the burning response function of the propellant under the oscillation pressure is obtained.
More specific experimental procedures were as follows:
1. testing whether the acquisition system is normal, namely testing whether the pressure sensor is normal, opening the acquisition system, observing whether the pressure value is balanced near the atmospheric pressure, and if so, judging that the acquisition system is normal;
2. sleeving a carbon felt heat insulation ring 15 on the side wall of the heating net 14 for one circle, and putting the carbon felt heat insulation ring into the zirconia Rijke tube 4;
3. connecting a gas cylinder, a pressure reducing valve and a damping chamber 5, adjusting the pressure of a gas source of a nitrogen path to 3-5Mpa, and checking whether the gas tightness is good;
4. starting a 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 the high-frequency induction microwave electric heater to heat the heating net 14;
7. heating for about 20s, and disconnecting the power supply when the heating net 14 is in a luminous state;
8. the acquisition system starts to acquire data;
9. the collected data are led out, thermocouple voltage values are read through Origin post-processing software and converted into temperature values, and the pressure sensor voltage values are converted into pressure values;
10. turning on an ignition power supply, igniting the propellant, and measuring the mass change of the propellant;
11. and measuring the burning rate of the propellant, and obtaining a propellant burning response function through calculation.
One of the key points of the present invention is to construct a thermoacoustically unstable environment, in which a large amplitude Rijke tube 4 is used. The heating power supply uses the induction power supply 1, the required high power can be provided for the heating net 14, the heating net 14 is made of graphite, the heating net can be heated to the temperature of 2000K under the induction power supply power, and a general electric heating system can only be heated to the temperature of less than 1000K, so that the heating net has great improvement. The second key point is that a mass analyzer is arranged in the Rijke tube 4 to carry out propellant combustion experiments. After the airflow passes through the heating net 14, large-amplitude pressure oscillation can be generated in the Rijke tube 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. The third key point is that a glass window is arranged at the place where the mass analyzer is placed for observing the combustion change of the propellant and obtaining the influence rule of the oscillation pressure on the propellant combustion.
Claims (6)
1. A measurement method of a thermoacoustic instability experimental system for measuring propellant combustion response is characterized by comprising the following steps:
step A, setting a thermoacoustic instability experimental system for measuring propellant combustion response, wherein the experimental system comprises:
a Rijke tube (4) with one end open and one end closed, and the open end is an air inlet end;
a heating net (14) is placed in the Rijke pipe (4) and is close to the air inlet end, the heating net (14) 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 openings are distributed on the heating net for air to flow; a heat insulation ring (15) is annularly sleeved on the outer side wall of the heating net (14) in a circle, 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 interior of the Rijke pipe (4) and is used for bearing and weighing the propellant;
b, starting an induction power supply (1) under the condition that nitrogen is introduced into the Rijke tube (4), heating the heating net (14) until the heating net (14) is in a light-emitting state, and disconnecting the induction power supply (1);
c, obtaining pressure and temperature values in the Rijke pipe (4) and deriving the pressure and temperature values;
and D, igniting the propellant, and measuring the mass change of the propellant.
2. A method of measuring a thermoacoustic instability experimental system for propellant combustion response, according to claim 1, characterized in that the 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 connected with an air supply device.
3. A method for measuring thermoacoustic instability experimental system for propellant combustion response according to claim 1 or 2, characterized in that a glass window is provided in the middle of the Rijke tube (4) and in the propellant combustion area for observing the combustion state of the propellant.
4. A method of measurement in a thermoacoustic instability experimental system for propellant combustion response measurement according to claim 3, characterized in that a plurality of temperature measurement holes are provided in the Rijke tube (4) at intervals along its length, each of the temperature measurement holes having a pressure sensor mounted therein.
5. The method for measuring the thermoacoustic instability experimental system for propellant combustion response 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 collection system; the objective table (9) is a plate body made of ceramic materials, and one side of the objective table is connected with the rack (7) through a cantilever beam (8) which is horizontally arranged.
6. A measurement method of a thermoacoustic instability experimental system for measuring propellant combustion response according to claim 5, characterized in that the Rijke tube (4) is made of zirconia.
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| CN114543984A (en) * | 2022-04-22 | 2022-05-27 | 北京航空航天大学 | Quantitative adjusting device and method for Rijke tube boundary dissipation |
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