A rocket engine injector fluid flow test system

Abstract

The present invention relates to the field of rocket engine technology, and in particular to a rocket engine injector liquid flow test system. The test system comprises: an injector measurement system; a liquid flow system, which is connected to the injector measurement system and is used to provide a liquid flow with a set pressure value to the injector measurement system; wherein the liquid flow system comprises a high-pressure gas cylinder, one end of which is connected to the high-pressure gas cylinder, and the other end of which is connected to the injector measurement system. A medium storage tank, and a pressure reducer arranged between the high-pressure gas cylinder and the medium storage tank, the high-pressure gas cylinder can provide a set pressure value to the medium in the medium storage tank through the pressure reducer, thereby realizing the reliable operation of the entire test system, and since there is no need to design a high-pressure pumping device separately, the relevant parts are easy to obtain or manufacture, so that the test cost of the entire test system is greatly reduced, and the cycle required for the test is also reduced.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, and in particular to a rocket engine injector liquid flow test system. Background Art

[0002] At present, liquid rocket engines rely on the propellants they carry to convert the chemical energy stored in the propellants into the heat energy of combustion through atomization, mixing and combustion of the propellants. The high-temperature and high-energy combustion gases expand in the nozzles, converting the thermal energy of the combustion gases into the kinetic energy of the gases, thereby generating the required thrust. As an important component of the rocket engine, the liquid rocket engine injector needs to be subjected to liquid flow tests after its assembly and before the hot test in order to verify the working status of the actual product, assess the flow characteristics, flow resistance characteristics and uniformity of the injector jet, etc., in order to obtain some precise parameters.

[0003] In this regard, in the prior art, the test system used in the injector liquid flow test requires different pumping equipment to pump out liquid flows of different pressure values. The pumped liquid flows pass through the injector. During the process of the liquid flow passing through the injector, the pressure, flow rate and other information of the liquid flow are detected and observed, thereby obtaining the flow characteristics, flow resistance characteristics and jet uniformity of the actual product. However, in the above test system, due to the high liquid pressure required for the test and the special application environment requirements, the engine injector liquid flow test system needs to design a high-pressure pumping equipment for the test separately, and the medium in the medium storage tank is pumped through the system, which makes the entire test process costly, the design and operation process complicated, and increases the test cycle. Summary of the invention

[0004] The main purpose of the present invention is to provide a rocket engine injector liquid flow test system to solve the problems of high test cost and long test cycle when performing liquid flow tests on rocket engine injectors in the prior art.

[0005] To achieve the above object, the present invention provides a rocket engine injector fluid flow test system, comprising:

[0006] An injector measurement system, comprising an injector and a measurement device in communication with the injector;

[0007] a liquid flow system, connected to the injector measurement system, for providing a liquid flow with a set pressure value to the injector measurement system;

[0008] Among them, the liquid flow system includes a high-pressure gas cylinder, a medium storage tank connected to the high-pressure gas cylinder at one end and connected to the injector measurement system at the other end, and a pressure reducer arranged between the high-pressure gas cylinder and the medium storage tank. The high-pressure gas cylinder can provide a set pressure value to the medium in the medium storage tank through the pressure reducer.

[0009] Furthermore, the fluid system also includes a pressure reducer front valve disposed between the high-pressure gas cylinder and the pressure reducer, and the pressure reducer front valve is used to control the on and off of the high-pressure gas cylinder.

[0010] Furthermore, the fluid flow system further comprises a pressure reducer rear valve disposed between the medium storage tank and the pressure reducer, and the pressure reducer rear valve is used to control the on-off of gas entering the medium storage tank.

[0011] Furthermore, the fluid system also includes an air venting pipeline arranged between the pressure reducer and the rear valve of the pressure reducer, and an air venting valve arranged on the air venting pipeline.

[0012] Furthermore, the fluid flow system further includes a discharge / filling pipeline arranged at the downstream end of the medium storage tank, and a discharge / filling valve arranged on the discharge / filling pipeline.

[0013] Further, the measuring device includes a mass flow meter connected to the injector, and a pressure sensor connected to the injector.

[0014] Furthermore, the injector measurement system also includes a filter arranged upstream of the injector.

[0015] Further, the filter is arranged upstream of the measuring device.

[0016] Further, it is characterized in that the injector measurement system also includes an injector switch arranged upstream of the injector.

[0017] The technical solution of the present invention has the following advantages:

[0018] In the rocket engine injector liquid flow test system provided by the present invention, a high-pressure gas cylinder that is easy to purchase is arranged in the liquid flow system, a pressure reducer is arranged downstream of the high-pressure gas cylinder, and a medium storage tank that can be used to store the medium is arranged. By adjusting the pressure reducer, the high-pressure gas cylinder applies a set pressure to the medium storage tank, so that the liquid flow system can output a medium with a set pressure value lower than the gas pressure of the high-pressure gas cylinder through the injector measurement system. While achieving reliable operation of the entire test system, since there is no need to separately design high-pressure pumping equipment, related components are easy to obtain or manufacture, so that the test cost of the entire test system is greatly reduced, and the cycle required for the test is also reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific implementation of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the specific implementation or the prior art description. Obviously, the drawings described below are some implementations of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. In the drawings:

[0020] Figure 1 Schematic diagram of the structure of the rocket engine injector fluid flow test system in an embodiment of the present invention.

[0021] Among them, the reference numerals in the above drawings are:

[0022] 1. High-pressure gas cylinder; 2. Pressure reducer front valve; 3. Release valve; 4. Pressure reducer; 5. Pressure reducer rear valve; 6. Medium storage tank; 7. Discharge / filling valve; 8. Filter; 9. Mass flow meter; 10. Injector switch; 11. Pressure sensor; 12. Injector. DETAILED DESCRIPTION

[0023] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0025] like Figure 1As shown, according to the rocket engine injector liquid flow test system in this embodiment, it includes: an injector measuring system and a liquid flow system. The injector measuring system includes an injector 12 and a measuring device connected to the injector 12; the liquid flow system is connected to the injector measuring system, and is used to provide a liquid flow with a set pressure value to the injector measuring system; the liquid flow system in this embodiment includes a high-pressure gas cylinder 1, one end of which is connected to the high-pressure gas cylinder 1, and the other end of which is connected to the injector measuring system. The medium storage tank 6, and the pressure reducer 4 arranged between the high-pressure gas cylinder 1 and the medium storage tank 6, the high-pressure gas cylinder 1 can provide a set pressure value to the medium in the medium storage tank 6 through the pressure reducer 4, and then the rocket engine injector liquid flow test system in this embodiment is adopted. By using the pressure reducer 4 in the liquid flow system A high-pressure gas cylinder 1 which is easy to purchase is arranged in the system, and a pressure reducer 4 and a medium storage tank 6 which can be used to store a medium are arranged downstream of the high-pressure gas cylinder 1. By adjusting the pressure reducer 4, the high-pressure gas cylinder 1 applies a set pressure to the medium storage tank 6, so that the liquid flow system can output a medium with a set pressure value which is lower than the gas pressure of the high-pressure gas cylinder 1. The medium with the set pressure value passes through the injector measurement system. While realizing the reliable operation of the entire test system, since there is no need to design a high-pressure pumping equipment separately, the relevant parts are easy to obtain or manufacture, so that the test cost of the entire test system is greatly reduced, and the cycle required for the test is also reduced.

[0026] Specifically, the liquid flow system in this embodiment also includes a pressure reducer front valve 2 arranged between the high-pressure gas cylinder 1 and the pressure reducer 4. The pressure reducer front valve 2 is used to control the on and off of the high-pressure gas cylinder 1. By controlling the pressure reducer front valve 2, the control of the rocket engine injector liquid flow test system can be facilitated, thereby simplifying the operating procedures of the rocket engine injector liquid flow test system.

[0027] Further participation Figure 1 The liquid flow system in this embodiment also includes a pressure reducer rear valve 5 arranged between the medium storage tank 6 and the pressure reducer 4. The pressure reducer rear valve 5 is used to control the on-off of the gas entering the medium storage tank 6, which facilitates the control of the rocket engine injector liquid flow test system and simplifies the operating process of the rocket engine injector liquid flow test system.

[0028] Preferably, the liquid flow system also includes a venting pipeline arranged between the pressure reducer 4 and the pressure reducer rear valve 5, and a venting valve 3 arranged on the venting pipeline, which can facilitate the venting and pressure relief of the high-pressure gas cylinder 1.

[0029] See also Figure 1 The liquid flow system in this embodiment also includes a discharge / filling pipeline arranged at the downstream end of the medium storage tank 6, and a discharge / filling valve 7 arranged on the discharge / filling pipeline. The discharge / filling pipeline can discharge the medium in the medium storage tank 6, or fill the medium when the medium is added to the medium storage tank 6.

[0030] Specifically, for the measuring device used to collect information of the injector 12 in this embodiment, the specific measuring device includes a mass flowmeter 9 connected to the injector 12, and a pressure sensor 11 connected to the injector 12. In the process of a medium with a set pressure value passing through the injector 12 through a liquid flow device, the mass flowmeter 9 and the pressure sensor 11 can detect and observe the pressure, flow rate and other information of the liquid flow flowing through the injector 12, thereby obtaining the flow characteristics, flow resistance characteristics and jet uniformity of the actual product and other information.

[0031] See also Figure 1 The injector measurement system in this embodiment also includes a filter 8 arranged upstream of the injector 12, so that the medium flowing through the injector 12 is filtered by the filter 8, thereby preventing impurities in the medium from clogging the injector 12, thereby ensuring the reliability of the subsequent operation of the injector 12.

[0032] The filter 8 is specifically arranged upstream of the measuring device, so as to filter the medium passing through the measuring device, thereby ensuring the accuracy of the measurement.

[0033] The injector measurement system in this embodiment also includes an injector switch 10 disposed upstream of the injector 12, which further facilitates the control of the rocket engine injector fluid flow test system and simplifies the operating procedures of the rocket engine injector fluid flow test system.

[0034] Combine the following Figure 1 The working process of the rocket engine injector liquid flow test system in this embodiment is explained.

[0035] The first step is the purge step before the injector liquid flow test. Before the test, the entire test system is purged to remove impurities in the test system. Specifically, first close the vent valve 3, the injector switch 10, the pressure reducer rear valve 5, and the discharge / filling valve 7, then slowly open the pressure reducer front valve 2, adjust the pressure reducer 4 to 0.5MPa, and then slowly open the discharge / filling valve 7 to purge the system, purge for 2 minutes, close the discharge / filling valve 7, open the injector switch 10, purge for 2 minutes, close the injector switch 10, the pressure reducer front valve 2, open the discharge / filling valve 7, until the pressure of the pressure reducer 4 is 0MPa, and then install the injector 12 to the test system;

[0036] The second step is the medium filling step. Open the vent valve 3 and the pressure reducer rear valve 5, connect the deionized water outlet to the discharge / filling valve 7, raise the deionized water tank to a height higher than the medium storage tank 6, open the discharge / filling valve 7 to fill the deionized water until the medium storage tank 6 is full;

[0037] The third step is to increase the pressure of the medium. Close the vent valve 3, the rear valve 5 of the pressure reducer, and the discharge / filling valve 7, open the front valve 2 of the pressure reducer, adjust the pressure of the pressure reducer 4 to the working pressure, slowly open the rear valve 5 of the pressure reducer to increase the pressure of the medium storage tank 6, and the test can be carried out only after the pressure of the pressure reducer 4 is stable; (If there is not enough water in the test, repeat the above three steps)

[0038] The fourth step is to turn on the injector switch 10 to conduct a test, and collect and calculate the data obtained by the measuring device;

[0039] Step 5: Deflate and drain. After the test is completed, close the injector switch 10 and the front valve 2 of the pressure reducer, open the vent valve 3 until the pressure of the pressure reducer 4 is 0MPa, and then open the discharge / filling valve 7 to drain the water until all the water is drained;

[0040] Step 6: Blow off after the test. After the test, the test system needs to be cleaned of residual water, and the blowing off operation can be performed according to the first step.

[0041] In combination with the rocket engine injector liquid flow test system in this embodiment, the above steps can be adopted to reduce the high cost of the entire test process and shorten the test cycle required. At the same time, the increase of the blowing step makes the operation of the entire liquid flow test system more reliable.

[0042] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A rocket engine injector fluid flow test system, characterized in that: include: An injector measurement system comprises an injector (12) and a measurement device connected to the injector (12); a liquid flow system, connected to the injector measurement system, for providing a liquid flow with a set pressure value to the injector measurement system; The liquid flow system comprises a high-pressure gas cylinder (1), a medium storage tank (6) having one end connected to the high-pressure gas cylinder (1) and the other end connected to the injector measurement system, and a pressure reducer (4) arranged between the high-pressure gas cylinder (1) and the medium storage tank (6), wherein the high-pressure gas cylinder (1) can provide a set pressure value for the medium in the medium storage tank (6) through the pressure reducer (4); The fluid system further comprises a pressure reducer front valve (2) arranged between the high-pressure gas cylinder (1) and the pressure reducer (4), and the pressure reducer front valve (2) is used to control the on-off of the high-pressure gas cylinder (1); the fluid system further comprises a pressure reducer rear valve (5) arranged between the medium storage tank (6) and the pressure reducer (4), and the pressure reducer rear valve (5) is used to control the on-off of the gas entering the medium storage tank (6); the fluid system further comprises a venting pipeline arranged between the pressure reducer (4) and the pressure reducer rear valve (5), and a venting valve (3) arranged on the venting pipeline; the fluid system further comprises a discharge / filling pipeline arranged at the downstream end of the medium storage tank (6), and a discharge / filling valve (7) arranged on the discharge / filling pipeline; the injector measurement system further comprises an injector switch (10) arranged upstream of the injector (12); The first step is the purge step before the liquid flow test of the injector (12); before the test, the entire test system is purged to remove impurities in the test system; specifically, the vent valve (3), the injector (12) switch (10), the rear valve of the pressure reducer (4), and the discharge / filling valve (7) are first closed, and then the front valve (2) of the pressure reducer (4) is slowly opened, and the pressure of the pressure reducer (4) is adjusted to 0.5 MPa, and then the discharge / filling valve (7) is slowly opened to purge the system, purge for 2 minutes, close the discharge / filling valve (7), open the injector (12) switch (10), purge for 2 minutes, close the injector (12) switch (10), the front valve (2) of the pressure reducer (4), open the discharge / filling valve (7), until the pressure of the pressure reducer (4) is 0 MPa, and then install the injector (12) on the test system; The second step is the medium filling step; open the vent valve (3) and the rear valve of the pressure reducer (4), connect the deionized water outlet to the discharge / filling valve (7), raise the deionized water tank to a height higher than the medium storage tank (6), open the discharge / filling valve (7) to fill the deionized water until the medium storage tank (6) is full; The third step is to increase the pressure of the medium; close the vent valve (3), the rear valve of the pressure reducer (4), and the discharge / filling valve (7), open the front valve (2) of the pressure reducer (4), adjust the pressure of the pressure reducer (4) to the working pressure, slowly open the rear valve of the pressure reducer (4) to increase the pressure of the medium storage tank (6), and the test can be carried out only after the pressure of the pressure reducer (4) is stable; The fourth step is to turn on the injector (12) switch (10) 10 to conduct a test, and collect and calculate the data obtained by the measuring device.

2. The rocket engine injector fluid flow test system according to claim 1, characterized in that: The measuring device comprises a mass flow meter (9) in communication with the injector (12), and a pressure sensor (11) in communication with the injector (12).

3. The rocket engine injector fluid flow test system according to claim 1, characterized in that: The injector measurement system further comprises a filter (8) arranged upstream of the injector (12).

4. The rocket engine injector fluid flow test system according to claim 3, characterized in that: The filter (8) is arranged upstream of the measuring device.

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