CN110657046B - System and method for testing low-temperature ignition capability of igniter for rocket engine - Google Patents
System and method for testing low-temperature ignition capability of igniter for rocket engine Download PDFInfo
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- CN110657046B CN110657046B CN201910958840.1A CN201910958840A CN110657046B CN 110657046 B CN110657046 B CN 110657046B CN 201910958840 A CN201910958840 A CN 201910958840A CN 110657046 B CN110657046 B CN 110657046B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/99—Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
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Abstract
The invention provides a system and a method for testing the low-temperature ignition capability of an igniter for a rocket engine, which solve the problem that whether the ignition function of the igniter at low temperature is normal or not can not be verified at present. The system comprises a first pipeline, a test box unit, a second pipeline, an ignition observation liquid receiving tank and a high-speed camera; the test box unit comprises a high-low temperature test box, an ignition guide pipe and a simulation guide pipe, wherein the ignition guide pipe and the simulation guide pipe are arranged in the high-low temperature test box; an ignition agent is arranged in the ignition guide pipe; kerosene is arranged in the simulation conduit, and a temperature measuring point is arranged; the inlet end of the first pipeline is connected with the crushing gas source, and the outlet end of the first pipeline is connected with the inlet joint of the ignition guide pipe; the first pipeline is provided with a switch valve, a nitrogen displacement unit and a flow regulating orifice plate; the nitrogen replacement unit is used for replacing air in a first pipeline between the switch valve and the ignition guide pipe inlet joint; the inlet end of the second pipeline is connected with the outlet joint of the ignition guide pipe, and the outlet end of the second pipeline extends into the ignition observation liquid receiving tank; the high-speed camera is used for shooting the ignition condition of the outlet end of the second pipeline.
Description
Technical Field
The invention relates to a system and a method for testing low-temperature ignition capability of an igniter for a rocket engine.
Background
The liquid oxygen kerosene rocket engine uses an igniter to ignite, the launching temperature is possibly lower than-40 ℃ in winter according to the requirements of a launching site, and in order to ensure the normal work of the engine under the low temperature condition, whether the ignition function of the igniter is normal or not needs to be verified at the temperature. However, no test system specially used for the ignition capability of the ignition agent in a low-temperature environment (lower than-40 ℃) exists at present, and a test system is urgently needed to be designed for qualitatively analyzing the ignition capability of the ignition agent in the low-temperature environment.
Disclosure of Invention
The invention provides a system and a method for testing the low-temperature ignition capability of an igniter for a rocket engine, aiming at solving the technical problem that the prior art can not verify whether the ignition function of the igniter at low temperature is normal.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
an igniter low-temperature ignition capability test system for a rocket engine is characterized in that: the device comprises a first pipeline, a test box unit, a second pipeline, an ignition observation liquid receiving tank and a high-speed camera;
the test box unit comprises a high-low temperature test box, an ignition guide pipe and a simulation guide pipe, wherein the ignition guide pipe and the simulation guide pipe are arranged in the high-low temperature test box; an ignition agent is arranged in the ignition guide pipe; kerosene is arranged in the simulation conduit, and an inserted temperature measuring point and a surface patch type temperature measuring point are arranged in the simulation conduit; the temperature regulating capacity of the high-low temperature test box is-70 ℃ to +150 ℃;
the inlet end of the first pipeline is connected with an extrusion breaking air source, and the outlet end of the first pipeline penetrates through the high-low temperature test box and then is connected with the inlet joint of the fire conduit;
the first pipeline is sequentially provided with a switch valve, a nitrogen displacement unit and a flow regulating pore plate along the conveying direction, and the switch valve, the nitrogen displacement unit and the flow regulating pore plate are all positioned outside the high-low temperature test box; the nitrogen replacement unit is used for replacing air in a first pipeline between the switch valve and the ignition guide pipe inlet joint;
the inlet end of the second pipeline is connected with the outlet joint of the ignition guide pipe, and the outlet end of the second pipeline penetrates out of the high-low temperature test box and then extends into the ignition observation liquid receiving tank;
the high-speed camera is used for shooting the ignition condition of the outlet end of the second pipeline.
Further, the ignition guide pipe adopts ZsF10-9 ignition guide pipes (a special device for storing the ignition agent for the engine test), and the main performance parameters are as follows:
the filling amount of the ignition agent in the ignition guide pipe is 260 +/-5 mL;
the filling factor K of the ignition tube is 0.89;
the inlet joint and the outlet joint of the ignition guide pipe are DN20 step joints;
the working pressure of the ignition conduit is 30MPa, and the crushing pressure of the ignition conduit is 3 +/-0.5 MPa.
Further, the model of the high-low temperature test box is HRT1070, and the main performance parameters are as follows:
the temperature regulating capacity is-70 ℃ to +150 ℃;
nominal internal volume 1000L;
the power supply requirement voltage is 380V, and the power is 18 kW;
2 ducts and cable ports for DN100 are provided.
Further, the switch valve is a B0 valve; the aperture of the flow regulating orifice plate is 1 mm.
Further, the ignition conduit is provided with a wall temperature measuring point.
Meanwhile, the invention provides a method for testing the low-temperature ignition capability of the igniter for the rocket engine, which is characterized by comprising the following steps of:
1) putting the ignition conduit filled with the test medium into a high-low temperature test chamber;
2) an inlet joint of the ignition guide pipe is connected with a crushing gas source outside the high-low temperature test box through a first pipeline, and an outlet joint of the ignition guide pipe is led out of an ignition observation liquid receiving tank outside the high-low temperature test box through a second pipeline;
3) opening a switch valve on the first pipeline, crushing the ignition conduit by using a crushing gas source, and debugging the aperture of the flow regulating orifice plate according to the liquid diffusion condition in the high-speed camera shooting;
4) placing the ignition guide pipe filled with the ignition medium into a high-low temperature test box, and replacing the ignition guide pipe filled with the test medium;
meanwhile, a simulation conduit filled with kerosene is placed in a high-low temperature test box, and the simulation conduit is provided with an inserted temperature measuring point and a surface patch type temperature measuring point;
5) cooling the high-low temperature test chamber, observing the wall temperature of the simulation conduit and the internal temperature of the simulation conduit until the temperature in the simulation conduit reaches the test temperature and is consistent with the wall temperature;
6) replacing air in the first pipeline between the switch valve and the inlet joint by using a nitrogen replacement unit;
7) opening a switch valve, crushing an air source to crush the ignition conduit, and judging the low-temperature ignition capacity of the igniter according to the camera shooting result of the high-speed camera; the imaging result includes the form of diffusion of the ignition agent, the time of combustion after diffusion, the location of combustion, and the severity of combustion.
Further, in the step 1) and the step 5), the ignition guide pipe is isolated from the outside by adopting a membrane after being filled, and the membrane is made of PTFE with the thickness of 1 mm.
Further, in step 1), the test medium is T3 medium.
Further, it is characterized in that: the aperture of the flow regulating orifice plate is 1 mm.
Further, in the step 4), installing a wall temperature measuring point on the ignition conduit filled with the ignition medium;
and 5) observing the wall temperatures of the ignition guide pipe and the simulation guide pipe and the internal temperature of the simulation guide pipe until the temperature in the simulation guide pipe reaches the test temperature and is consistent with the wall temperature.
Compared with the prior art, the invention has the advantages that:
1. according to the testing system, the ignition guide pipe is arranged in the high-low temperature test box, the high-low temperature test box simulates a low-temperature environment, the simulation guide pipe filled with kerosene is arranged in the high-low temperature test box, the wall temperature and the insertion temperature of the simulation guide pipe are compared, the internal temperature of the ignition guide pipe can basically accord with the outer wall temperature, the temperature requirement of the ignition agent is ensured, and the ignition capability of the ignition agent in the ignition guide pipe is tested according to the ignition condition of the outlet end of the second pipeline shot by a high-speed camera.
2. The ignition conduit in the test system can be provided with a wall temperature measuring point so as to more accurately ensure that the temperature of the ignition agent in the ignition conduit meets the test requirements.
3. The testing method comprises the steps of firstly, carrying out a crushing test on a test medium of an unfilled ignition duct by adopting nitrogen, debugging and determining the aperture of the flow regulating orifice plate (throttling scheme), ensuring the safety and reliability of the testing process, ensuring no medium splash in the test and verifying the feasibility of the testing scheme; and then placing the ignition guide pipe filled with the ignition medium and the simulation guide pipe filled with kerosene into a high-low temperature test box to perform a crushing test of the ignition medium, and shooting the ignition condition at the outlet end of the second pipeline by using a high-speed camera to test the ignition capability of the ignition agent in the ignition guide pipe.
Drawings
FIG. 1 is a schematic view of a low temperature ignitability testing system for an igniter for rocket engines of the invention;
FIG. 2 is a schematic view showing the structure of an ignition duct in the testing system for low-temperature ignitability of an ignition agent for rocket engines according to the present invention;
FIG. 3 is a graph of the temperature profile of the ignition tube wall and chamber at different cooling times during the test method of the present invention;
FIG. 4 is a graph of the drop in temperature data for a fire conduit from initial cool down to temperature equilibrium in a test method of the present invention; wherein, the curve a is the internal temperature of the kerosene guide pipe, the curve b is the surface temperature of the kerosene guide pipe, the curve c is the surface temperature of the ignition guide pipe, and the curve d is the peripheral environment temperature;
FIG. 5 is a graph of temperature pressure data for an ignition tube crush in a test method of the present invention;
wherein, the curve a and the curve b are the internal temperature and the surface temperature of the kerosene guide pipe respectively, the curve c is the wall temperature of the ignition guide pipe, and the curve d is the peripheral environment temperature;
FIG. 6 is a graph comparing temperature simulation results with experimental data in the test method of the present invention;
wherein, curve a1 and curve b1 are the temperature of the inner wall of the ignition conduit, curve c is the temperature of the outer wall of the ignition conduit, curve d is the ambient temperature, curve e is the temperature of the outer wall of the simulated conduit, and curve f is the temperature of the inner wall of the simulated conduit;
wherein the reference numbers are as follows:
1-a first pipeline, 11-a switch valve, 12-a flow regulation orifice plate, 13-a nitrogen displacement unit, 2-a test box unit, 21-a high-low temperature test box, 22-an ignition guide pipe, 221-an inlet joint, 222-an outlet joint, 23-an analog guide pipe, 3-a second pipeline, 4-an ignition observation liquid receiving tank and 5-a high-speed camera.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
As shown in fig. 1, the system for testing the low-temperature ignition capability of the igniter for the rocket engine comprises a first pipeline 1, a test box unit 2, a second pipeline 3, an ignition observation liquid receiving tank 4 and a high-speed camera 5; the test chamber unit 2 comprises a high-low temperature test chamber 21, an ignition guide pipe 22 arranged in the high-low temperature test chamber 21 and a simulation guide pipe 23; an ignition agent is arranged in the ignition conduit 22; the structure of the simulation conduit 23 is consistent with that of the ignition conduit 22, kerosene is arranged in the simulation conduit, and an inserted temperature measuring point and a surface patch temperature measuring point are arranged in the simulation conduit; the inlet end of the first pipeline 1 is connected with an extrusion breaking air source, and the outlet end of the first pipeline penetrates through the high-low temperature test box 21 and then is connected with the inlet joint 221 of the fire conduit 22; the first pipeline 1 is sequentially provided with a switch valve 11, a nitrogen replacement unit 13 and a flow regulation pore plate 12 along the conveying direction, and the switch valve, the nitrogen replacement unit and the flow regulation pore plate are all positioned outside the high-low temperature test box 21; the nitrogen gas replacement unit 13 is used for replacing the air in the first pipeline 1 between the switch valve 11 and the inlet joint 221 of the ignition guide pipe 22; the inlet end of the second pipeline 3 is connected with the outlet joint 222 of the ignition guide pipe 22, and the outlet end of the second pipeline penetrates through the high-low temperature test box 21 and then extends into the ignition observation liquid receiving tank 4; the high speed camera 5 is used to photograph the ignition at the outlet end of the second conduit 3.
First, main equipment and performance index thereof
1. Ignition conduit 22
The low-temperature ignition capability test adopts ZsF10-9 ignition guide pipes as test objects, ZsF10-9 is a special storage device for placing rocket ignition agents, the structural form of the storage device is shown in figure 2, and the main performance parameters are as follows:
a) the filling amount of the ignition agent in the ignition tube 22 is 260 plus or minus 5 mL;
b) the filling factor K of ignition tube 22 is 0.89;
c) inlet connection 221 and outlet connection 222 of ignition conduit 22 are DN20 step connections;
d) the working pressure of the ignition guide pipe is 30 MPa; the crushing pressure of the conduit is 3 +/-0.5 MPa;
e) the ignition conduit 22 is provided with a wall temperature gauge.
2. High and low temperature test chamber 21
The model of the high-low temperature test box 21 is HRT1070, and the main performance parameters are as follows:
a) the temperature regulating capacity is-70 ℃ to +150 ℃;
b) nominal internal volume 1000L;
c) the power supply requirement voltage is 380V, and the power is 18 kW;
d) 2 ducts and cable ports for DN100 are provided.
3. High-speed camera 5
a) High speed camera 5 model: dimax HD
b) Lens model: canon EF 70-200mm f/2.8L
c) Resolution ratio: 1920 x 1080
d) Frame rate: 500 frames/second
e) Dynamic range: 1600:1
f) Shutter speed: 257 μ s.
4. Nitrogen gas replacement unit
The nitrogen replacement unit 13 comprises a nitrogen inlet valve arranged on the first pipeline 1, a nitrogen feeding pipeline communicated with the nitrogen inlet valve and a nitrogen source.
5. Switch valve
The switch valve adopts a B0 valve.
6. The structure of the dummy tube is identical to that of the ignition tube,
analyzing and adjusting parameters
1. Temperature stratification caused by rapid cooling of the high and low temperature chambers causes a deviation in the temperature of the liquid in the ignition conduit 22 from the surface temperature of the chamber.
In actual work, the low-temperature working state of the ignition conduit 22 is mainly affected by the ambient temperature, the reduction rate of the ambient temperature is low during work, and the problem that the reduction rate is low and the reduction rate is kept low continuously is solved. Because the structure of the ignition conduit 22 and its physical and chemical properties are not suitable for the insertion type temperature measurement method, the condition of the internal and external temperature difference is analyzed and calculated to solve the problem.
The initial temperature t of the wall of the ignition tube 22 is used for calculationwAt a temperature of 17 ℃ and an ambient temperature t∞The temperature is-50 ℃ as the initial condition; the temperature difference Δ t of the Gravadaff number is tw-t∞67 ℃ and qualitative temperature tm＝(tw+t∞) The v is 12.14 x 10 by looking up table at-16.5 deg.C-6m2The Gr-dawn Gr is calculated by the following formula:
wherein alpha isv＝(273+tm)，l＝0.048；
Is calculated to obtain
Calculating Nu by using correlation of large-space natural convection experimentm：
Num＝C(Gr·Pr)n
In the formula, NumThe number of Knudell for surface heat transfer; the liquid state belongs to laminar flow, and C is 0.48, and n is 0.25;
nu is obtained by calculationm＝0.48*(1.92*10^6*0.714)0.25＝16.4；
Coefficient of heat transfer
Considering the heat radiation of the ignition conduit 22, the radiation heat transfer quantity changes with the temperature change, and the natural convection heat transfer quantity is equivalent to the radiation heat transfer quantity according to experience, and approximately 7.8W/m is taken2K, total heat transfer coefficient 15.6W/m2*K；
Setting the heat transfer coefficient as a third type boundary condition of numerical simulation, and calculating to obtain the temperature distribution of the wall surface of the conduit and the cavity in each time period as shown in FIG. 3;
therefore, the comparison of the wall temperature and the insertion temperature of the simulated conduit 23 is compared with the kerosene filled in the simulated conduit 23 in the test to confirm that the internal temperature of the actual ignition conduit 22 is substantially consistent with the external wall temperature. Meanwhile, the ignition agent temperature is ensured to reach the stable temperature by adopting the modes of prolonging the standing time and increasing the temperature exchange time.
2. Analysis of influence of high-speed nitrogen flow on sprayed igniter
The test is based on the fact that the situation that kerosene and liquid oxygen collide with an ignition agent at the same time cannot be simulated under the test conditions, the scheme that the ignition agent and the kerosene enter an ignition area as an engine is not adopted, and the alternative scheme that nitrogen and the ignition agent enter the ignition area at the same time is adopted; if the ignition agent and a large amount of nitrogen enter the ignition area at the same time, the ignition agent is materialized due to high-speed nitrogen flow, a real process cannot be simulated, and potential safety hazards are brought to a test site by the large-area atomized ignition agent.
Therefore, the flow resistance of the pipeline is adjusted by adjusting the throttling scheme of the flow regulating orifice plate 12 of the first pipeline, a T3 (a special cleaning agent mainly comprising an alcohol medium) medium is used for carrying out a simulation test, and high-speed photography is used for confirming that the situation that rapid atomization does not occur when liquid and nitrogen flow out is achieved, so that the flow resistance of the pipeline is confirmed. In this embodiment, the aperture of the flow regulating orifice plate 12 is 1mm, and the system in this state is used for pre-testing, and is adaptively adjusted according to the test result to ensure the safety of the test.
3. Determination of test temperature
The requirement of this embodiment is to obtain the low temperature ignition capability under the condition of-40 ℃, and in consideration of the cost of the system and the low temperature condition which may appear in the Goulan target station, the recorded meteorological data in China are referred, the extreme lowest temperature of the Heilongjiang desert river is recorded as-52.3 ℃ in 2.13.13.2.1969, and the temperature of the high-low temperature box is set as-53 ℃.
Meanwhile, the embodiment provides a method for testing the low-temperature ignition capability of the igniter for the rocket engine, which comprises the following steps:
step one, simulation test
The empty ignition duct 22 is used for carrying out a crushing test of the T3 medium before the test, and the main working flow is as follows:
1.1) filling an empty ignition guide pipe 22 with T3, and putting the filled ignition guide pipe 22 into a high-low temperature test box 21; an inlet joint 221 of the ignition guide pipe 22 is connected with a crushing gas source outside the high-low temperature test box 21 through a first pipeline 1, and an outlet joint 222 of the ignition guide pipe is led out of an ignition observation liquid receiving tank 4 outside the high-low temperature test box 21 through a second pipeline 3;
wherein, the filling of the simulation piece of the ignition conduit 22 is to simplify the test process, and a replacing membrane is adopted, and the membrane is made of PTFE with the thickness of 1 mm;
1.2) installing the flow regulating pore plate 12 on a first pipeline, supplying air before B0, and supplying the air at a pressure of 4 MPa;
1.3) after receiving signals which are ready for acquisition of a measurement system and are ready for high-speed camera 5, opening a B0 valve on the first pipeline 1, and carrying out a crushing test on the ignition conduit 22 by using a crushing gas source;
1.4) carrying out state observation through the result of the liquid diffusion condition in the camera shooting of the high-speed camera 5, debugging the aperture of the flow regulating orifice plate 12, determining the throttling scheme that the aperture of the flow regulating orifice plate 12 on the first pipeline 1 is 1mm, and achieving the expected extrusion effect through the adjusted scheme.
The throttling scheme that the aperture of the flow regulating orifice plate 12 is 1mm is adopted, the safety and the reliability of the whole test process are verified, no medium splashes in the test process, the video shot by the high-speed camera 5 is video, and the T3 medium extrusion effect of the simulation test meets the test requirements.
Step two, ignition guide 22 testing
After the feasibility of the test scheme and the images are effectively obtained as verified by the T3 crush test, the ignition agent crush test of the ignition tube 22 is performed after the system is adjusted according to the test, and the main flow is as follows:
2.1) installing a wall temperature measuring point on the ignition guide pipe 22 filled with the ignition medium, placing the ignition guide pipe into a high-low temperature box after the installation is finished, connecting an inlet joint 221 of the ignition guide pipe 22 with a crushing gas source outside the high-low temperature test box 21 through a first pipeline 1, and leading an outlet joint 222 of the ignition guide pipe out of an ignition observation liquid receiving tank 4 outside the high-low temperature test box 21 through a second pipeline 3; measuring the temperature through a sensor of a wall temperature measuring point; the first pipeline 1, the second pipeline 3 and the sensor wire are led out of the high-low temperature test box 21 through the open holes on the two sides of the high-low temperature test box 21, and the rest of the open holes are blocked by sponge materials;
2.2) filling the simulation conduit 23 with kerosene, placing the simulation conduit in the high-low temperature test box 21, and installing the simulation conduit (3) with an inserted temperature measuring point and a surface-mounted temperature measuring point.
2.3) cooling the high-low temperature test box 21 and monitoring the temperature; by observing the wall temperatures and the internal temperature of the simulation conduit 23, the temperature of the ignition agent in the simulation conduit is ensured to be fully and uniformly consistent with the wall temperature basically, the error is not more than 0.1 ℃, and the constant temperature is continued for 60 minutes.
2.4) the nitrogen gas replacement unit 13 replaces the air in the first pipeline 1 between the switch valve 11 and the inlet joint 221 of the ignition duct 22 with 0.6MPa nitrogen gas;
2.5) after receiving a signal which is ready for acquisition of the measurement system and ready for preparation of the high-speed camera 5 of the control system, opening a B0 valve, and crushing the ignition conduit 22 by using a crushing gas source;
2.6) acquiring crushing related pressure, temperature and shooting data, and judging the low-temperature ignition capacity of the igniter according to the shooting mode of the igniter by the high-speed camera 5, the combustion time after the diffusion, the combustion position, the combustion intensity and other results.
Analysis of test data
a) Temperature pressure data
The profile of the process of the ignition tube 22 from initial cool down to temperature equilibrium is shown in fig. 4: by comparing the ignition conduit surface temperature curve c, the kerosene conduit surface curve b, the kerosene conduit internal temperature curve a, and the curve d, the peripheral environment temperature is obtained.
The set temperature of the high-low temperature box is-53 ℃, the actually measured wall temperature is-51.8 ℃, the measurement precision of the sensor is considered, the actually measured wall temperature of the measurement system is taken as the indication temperature, and the temperature of the ignition agent is verified to be-51.8 ℃.
The temperature changes in the maintenance process are carried out on the high-low temperature box fault tripping section by the middle rising part from the beginning of the reduction of the ambient temperature. Under the balanced heat exchange mode, the wall temperature measuring point is basically consistent with the plug-in temperature measuring point, and the ignition agent temperature can be considered as the wall temperature by considering the closer physical and chemical properties of the kerosene and the ignition agent. The temperature and pressure data curve of the ignition conduit during crushing is shown in fig. 5, and the process that normal-temperature nitrogen enters the inner wall of the ignition conduit after crushing can be seen according to the curve c, the temperature rapidly rises, and the test is verified to be in accordance with the expectation. By comparing the difference between the internal temperature curve a and the surface temperature curve b of the kerosene conduit, the internal temperature of the ignition conduit can be judged to meet the requirement through the surface temperature curve c of the ignition conduit.
b) Theoretical comparison of data analysis and cooling lag in temperature reduction process
The process curve of the ignition tube 22 from the beginning of temperature reduction to temperature equilibrium is obtained through measurement and compared with the simulation process of the temperature reduction process, the comparison result is shown in fig. 6, and the method is effective by comparing the simulation condition with the actual condition. Through comparative theory analysis, the data is basically consistent with the actual data; the study conclusion can be followed as a basis for similar experiments, confirmed by means of numerical simulation when the internal temperature is not conveniently measured.
c) High speed camera 5 capture analysis
Analysis was performed for images within 100ms of the ignition agent entering the ignition zone:
the first stage is as follows: when the outlet end of the second pipeline 3 begins to vibrate, the membrane of the conduit is broken;
and a second stage: at 36ms, the outlet end of the second pipeline 3 starts to spray the igniter liquid with unobvious yellow flame;
and a third stage: at 74ms, the igniter liquid at the outlet end of the second pipeline 3 flows fully, and meanwhile, the outlet is accompanied by a bright flame which is yellowish green;
a fourth stage: at 84ms, the outlet end of the second tube 3 is completely covered by the flame.
Therefore, the igniter can be ignited quickly after flowing out from the nozzle, and the low-temperature ignition capability of the igniter is not influenced by low temperature at low temperature according to the fact that the igniter is ignited and burnt after about 36ms after flowing out from the nozzle according to the high-speed image. The flame after the high-speed flowing of the ignition agent is continuous, the ignition performance is good under the condition that the subsequent nitrogen flows out quickly, and the continuous ignition capability is not influenced by low temperature.
The above description is only for the purpose of describing the preferred embodiments of the present invention and does not limit the technical solutions of the present invention, and any known modifications made by those skilled in the art based on the main technical concepts of the present invention fall within the technical scope of the present invention.
Claims (10)
1. An igniter low-temperature ignition capability test system for a rocket engine is characterized in that: the device comprises a first pipeline (1), a test box unit (2), a second pipeline (3), an ignition observation liquid receiving tank (4) and a high-speed camera (5);
the test box unit (2) comprises a high-low temperature test box (21), an ignition guide pipe (22) arranged in the high-low temperature test box (21) and a simulation guide pipe (23);
an ignition agent is arranged in the ignition guide pipe (22);
kerosene is arranged in the simulation conduit (23), and an inserted temperature measuring point and a surface patch type temperature measuring point are arranged in the simulation conduit;
the temperature adjusting capacity of the high-low temperature test box (21) is-70 ℃ to +150 ℃;
the inlet end of the first pipeline (1) is connected with an extrusion gas source, and the outlet end of the first pipeline penetrates through the high-low temperature test box (21) and then is connected with the inlet joint (221) of the fire guide pipe (22);
a switch valve (11), a nitrogen replacement unit (13) and a flow regulation pore plate (12) are sequentially arranged on the first pipeline (1) along the conveying direction and are positioned outside the high-low temperature test box (21); the nitrogen replacement unit (13) is used for replacing air in the first pipeline (1) between the switch valve (11) and the inlet joint (221) of the ignition guide pipe (22);
the inlet end of the second pipeline (3) is connected with the outlet joint (222) of the ignition guide pipe (22), and the outlet end of the second pipeline penetrates out of the high-low temperature test box (21) and then extends into the ignition observation liquid receiving tank (4);
the high-speed camera (5) is used for shooting the ignition condition of the outlet end of the second pipeline (3).
2. The system for testing low-temperature ignitability of an igniter for rocket engines according to claim 1, wherein: the ignition guide pipe (22) adopts an ZsF10-9 ignition guide pipe, and the main performance parameters are as follows:
the filling amount of the ignition agent in the ignition guide pipe (22) is 260 +/-5 mL;
the filling factor K of the ignition tube (22) is 0.89;
the inlet joint (221) and the outlet joint (222) of the ignition guide pipe (22) are DN20 step joints;
the working pressure of the ignition conduit (22) is 30MPa, and the crushing pressure of the ignition conduit (22) is 3 +/-0.5 MPa.
3. The system for testing low-temperature ignitability of an igniter for rocket engines according to claim 1, wherein: the main performance parameters of the high-low temperature test box (21) are as follows:
the temperature regulating capacity is-70 ℃ to +150 ℃;
nominal internal volume 1000L;
the power supply requirement voltage is 380V, and the power is 18 kW;
2 ducts and cable ports for DN100 are provided.
4. A rocket engine igniter low-temperature ignition ability test system according to any one of claims 1 to 3, wherein: the switch valve (11) is a B0 valve;
the aperture of the flow regulating orifice plate (12) is 1 mm.
5. The system for testing low-temperature ignitability of an igniter for rocket engines according to claim 4, wherein: the ignition conduit (22) is provided with a wall temperature measuring point.
6. A method for testing the low-temperature ignition capability of an igniter for a rocket engine is characterized by comprising the following steps:
1) putting an ignition conduit (22) filled with a test medium into a high-low temperature test box (21);
2) an inlet joint (221) of an ignition guide pipe (22) is connected with a crushing gas source outside a high-low temperature test box (21) through a first pipeline (1), and an outlet joint (222) of the ignition guide pipe is led out to an ignition observation liquid receiving tank (4) outside the high-low temperature test box (21) through a second pipeline (3);
3) opening a switch valve (11) on the first pipeline (1), crushing the ignition conduit (22) by a crushing gas source, and adjusting the aperture of the flow regulating pore plate (12) according to the liquid diffusion condition in the shooting of the high-speed camera (5);
4) putting the ignition guide pipe (22) filled with the ignition medium into the high-low temperature test box (21), and replacing the ignition guide pipe (22) filled with the test medium;
meanwhile, a simulation conduit (23) filled with kerosene is placed in a high-low temperature test box (21), and the simulation conduit (23) is provided with an inserted temperature measuring point and a surface patch type temperature measuring point;
5) cooling the high-low temperature test box (21), observing the wall temperature of the simulation guide pipe (23) and the internal temperature of the simulation guide pipe (23) until the temperature in the simulation guide pipe (23) reaches the test temperature and is consistent with the wall temperature;
6) replacing air in the first pipeline (1) between the switch valve (11) and the inlet joint (221) by using a nitrogen replacement unit (13);
7) opening the switch valve (11), crushing the ignition conduit (22) by the crushing gas source, and judging the low-temperature ignition capacity of the igniter according to the image pickup result of the high-speed camera (5); the imaging result includes the form of diffusion of the ignition agent, the time of combustion after diffusion, the location of combustion, and the severity of combustion.
7. The method for testing the low-temperature ignitability of an igniter for rocket engines according to claim 6, wherein: in the steps 1) and 5), the ignition guide pipe (22) is isolated from the outside by a membrane after being filled, and the membrane is made of PTFE with the thickness of 1 mm.
8. The method for testing the low-temperature ignitability of an igniter for rocket engines according to claim 7, wherein: in the step 1), the test medium is T3 medium.
9. The method for testing the low-temperature ignitability of an igniter for rocket engines according to claim 6, 7 or 8, wherein: the aperture of the flow regulating orifice plate (12) is 1 mm.
10. The method for testing the low-temperature ignitability of an igniter for rocket engines according to claim 9, wherein: in the step 4), installing a wall temperature measuring point on the ignition guide pipe (22) filled with the ignition medium;
and 5), observing the wall temperature of the ignition guide pipe (22) and the simulation guide pipe (23) and the internal temperature of the simulation guide pipe (23) until the temperature in the simulation guide pipe (23) reaches the test temperature and is consistent with the wall temperature.
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| US4130011A (en) * | 1977-06-14 | 1978-12-19 | The United States Of America As Represented By The Secretary Of The Air Force | Flared sonic end nozzle velocity coupling test burner |
| JP2003214598A (en) * | 2002-01-23 | 2003-07-30 | Mitsubishi Heavy Ind Ltd | Cryogenic liquid tank |
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