Liquid rocket engine nozzle back-pressure low-temperature spray test system

Abstract

The invention relates to a liquid rocket engine nozzle back-pressure low-temperature spray test system. Low-temperature helium medium supply is achieved through a helium tank, a helium conveying pipeline, a heat exchanger and a low-temperature helium conveying pipeline. Low-temperature cooling of helium is achieved through the nitrogen cylinder, the nitrogen pressurizing conveying pipeline, the liquid nitrogen container and the liquid nitrogen cooling conveying pipeline. And a back pressure environment of the back pressure cabin is realized through a nitrogen cylinder and a nitrogen back pressure conveying pipeline. Liquid nitrogen test medium supply is achieved through a nitrogen cylinder, a nitrogen pressurization conveying pipeline, a liquid nitrogen container and a liquid nitrogen test conveying pipeline. The installation and fixation of the product and the low-temperature back-pressure spraying environment are realized through the back-pressure cabin, and the visual measurement of the spraying field is realized. Therefore, the atomization characteristic of the nozzle in the low-temperature back-pressure environment can be measured.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engine fluid testing, and relates to a liquid rocket engine nozzle back-pressure low-temperature spray testing system. Background Art

[0002] Liquid hydrogen and liquid oxygen in hydrogen-oxygen liquid rocket engines are atomized through nozzles at supercritical pressure. The atomization mechanism and state under supercritical and subcritical pressure conditions are different, and its combustion stability becomes one of the key technologies in research and development. Therefore, studying the atomization characteristics of cryogenic fluids under supercritical conditions will have a great guiding role in research and development work. In order to study the atomization mechanism and spray stability of liquid hydrogen and liquid oxygen under supercritical conditions and provide a basis for engine development, it is necessary to design a low-temperature back-pressure spray test method for liquid rocket engine nozzles that can meet the requirements for research on the spray process of nozzle products under supercritical conditions. At present, domestic spray test methods are mainly used for normal pressure spray test systems or back-pressure normal temperature spray test devices, and do not involve low-temperature back-pressure environment spray test systems. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a liquid rocket engine nozzle back-pressure low-temperature spray test system, which has the capabilities of liquid nitrogen medium pressurized delivery, helium medium pressurized delivery, helium cooling, low-temperature back-pressure environment, visualization, etc., so that the atomization characteristics of the nozzle low-temperature back-pressure environment can be measured.

[0004] The solution of the present invention is:

[0005] Liquid rocket engine nozzle back-pressure cryogenic spray test system, including helium cylinder, nitrogen cylinder, liquid nitrogen container, back-pressure chamber, heat exchanger, helium delivery pipeline, nitrogen booster delivery pipeline, nitrogen back-pressure delivery pipeline, liquid nitrogen cooling delivery pipeline, liquid nitrogen test delivery pipeline, cryogenic helium delivery pipeline, liquid nitrogen discharge pipeline, camera;

[0006] The helium cylinder delivers the helium medium to the heat exchanger through the helium delivery pipeline; the nitrogen cylinder is connected to the liquid nitrogen container through the nitrogen booster delivery pipeline to boost the pressure of the liquid nitrogen container; on the other hand, the back pressure chamber is boosted through the nitrogen back pressure delivery pipeline; the back pressure chamber is used to simulate the low temperature back pressure environment of the test product, and the nozzle of the liquid rocket engine is fixed inside the back pressure chamber;

[0007] The liquid nitrogen container is used to store liquid nitrogen medium for testing. The outlet of the liquid nitrogen container provides a refrigerant medium to the heat exchanger through a liquid nitrogen cooling delivery pipeline, and on the other hand, delivers the liquid nitrogen to the liquid rocket engine nozzle liquid path inlet inside the counter-pressure chamber through a liquid nitrogen test delivery pipeline; the low-temperature helium after heat exchange in the heat exchanger is delivered to the liquid rocket engine nozzle gas path inlet inside the counter-pressure chamber through a low-temperature helium delivery pipeline; the liquid nitrogen and the low-temperature helium are sprayed through the nozzle to form an atomization field in the low-temperature counter-pressure environment inside the counter-pressure chamber, and the camera is used to shoot the atomization field; the outlet of the counter-pressure chamber is connected to the liquid nitrogen discharge pipeline;

[0008] The helium gas delivery pipeline, nitrogen booster delivery pipeline, nitrogen back pressure delivery pipeline, liquid nitrogen cooling delivery pipeline, liquid nitrogen test delivery pipeline, cryogenic helium gas delivery pipeline and liquid nitrogen discharge pipeline are all provided with stop valves for controlling on and off.

[0009] Preferably, the helium delivery pipeline, the nitrogen boost delivery pipeline, and the nitrogen back-pressure delivery pipeline are all provided with pressure reducing valves, and the pressure reducing valves are used to adjust the outlet pressure of the pipelines.

[0010] Preferably, the liquid nitrogen cooling delivery pipeline, the liquid nitrogen test delivery pipeline, and the helium delivery pipeline are all provided with flow meters for measuring the medium flow.

[0011] Preferably, the back-pressure chamber can form a spray test condition with a stable ambient pressure, thereby simulating the back-pressure state in various combustion chambers.

[0012] Preferably, the counterpressure chamber has a visualization function and an optical coordinate system, which facilitates non-contact measurement using optical measuring equipment.

[0013] Preferably, the counter-pressure cabin is provided with a window, and the camera is located outside the counter-pressure cabin, and the atomization field is photographed through the window of the counter-pressure cabin.

[0014] Preferably, two stop valves are provided on the liquid nitrogen cooling delivery pipeline, the liquid nitrogen test delivery pipeline, and the helium delivery pipeline, respectively located on both sides of the flow meter.

[0015] Preferably, two stop valves are provided on the nitrogen boost delivery pipeline and the nitrogen back-pressure delivery pipeline, respectively located on both sides of the pressure reducing valve.

[0016] The beneficial effects of the present invention compared with the prior art are:

[0017] The present invention realizes the supply of low-temperature helium medium through a helium cylinder, a helium delivery pipeline, a heat exchanger, and a low-temperature helium delivery pipeline. The low-temperature cooling of helium is realized through a nitrogen cylinder, a nitrogen booster delivery pipeline, a liquid nitrogen container, and a liquid nitrogen cooling delivery pipeline. The back-pressure environment of the back-pressure cabin is realized through a nitrogen cylinder and a nitrogen back-pressure delivery pipeline. The liquid nitrogen test medium is supplied through a nitrogen cylinder, a nitrogen booster delivery pipeline, a liquid nitrogen container, and a liquid nitrogen test delivery pipeline. The installation and fixation of the product and the low-temperature back-pressure spray environment are realized through the back-pressure cabin, and the visual measurement of the spray field is realized. Therefore, the atomization characteristics of the low-temperature back-pressure environment of the nozzle can be measured. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the present invention. DETAILED DESCRIPTION

[0019] The present invention will be further described below in conjunction with the accompanying drawings.

[0020] The present invention can realize liquid nitrogen medium pressurized delivery, helium medium pressurized delivery, helium cooling, low-temperature counter-pressure environment and visualization.

[0021] like Figure 1 As shown, the present invention includes a helium cylinder 1, a nitrogen cylinder 2, a liquid nitrogen container 3, a back pressure cabin 4, a heat exchanger 5, a pressure reducing valve 6, a valve 7, a flow meter 8, a helium delivery pipeline 9, a nitrogen booster delivery pipeline 10, a nitrogen back pressure delivery pipeline 11, a liquid nitrogen cooling delivery pipeline 12, a liquid nitrogen test delivery pipeline 13, a cryogenic helium delivery pipeline 14, a liquid nitrogen discharge pipeline 15, and a camera.

[0022] The liquid nitrogen container 3 is used to store the liquid nitrogen medium for the test, and the liquid nitrogen container 3 is pressurized and transported through the nitrogen bottle 2 and the nitrogen pressurization delivery pipeline 10. The liquid nitrogen container 3 provides the refrigerant medium to the heat exchanger 5 through the liquid nitrogen cooling delivery pipeline 12 to perform low-temperature cooling on the helium; at the same time, the liquid nitrogen container 3 transports the liquid nitrogen medium to the back pressure cabin 4 through the liquid nitrogen test delivery pipeline 13 to provide liquid nitrogen as the test medium.

[0023] The back pressure chamber 4 is used to simulate the back pressure environment of the test product and meet the requirements of optical measurement of the product atomization mixing characteristics. A spray test condition with a stable ambient pressure can be formed to simulate the back pressure state in various combustion chambers, and it has a visualization function and an optical coordinate system, which is convenient for non-contact measurement using various optical measurement equipment. The nozzle product is fixed inside the back pressure chamber, and the liquid nitrogen and helium media transported by the liquid nitrogen test delivery pipeline 13 and the low-temperature helium delivery pipeline 14 are connected to the liquid inlet and gas inlet of the nozzle product through a metal hose. The spray forms an atomization field in the low-temperature back pressure environment inside the back pressure chamber, and the camera performs high-speed photography and measurement through the window of the back pressure chamber.

[0024] The heat exchanger 5 is a device that transfers part of the heat of the hot fluid to the cold fluid, and mainly uses low-temperature liquid nitrogen as a refrigerant to cool the working helium from room temperature to low-temperature helium.

[0025] The helium cylinder 1 realizes the helium supply, and the helium medium is transported to the heat exchanger 5 through the helium delivery pipeline 9 for low temperature cooling. After cooling, it enters the counter-pressure chamber through the low-temperature helium delivery pipeline 14 to provide the test medium helium. The nitrogen cylinder realizes the nitrogen supply, and the liquid nitrogen container 3 is pressurized through the nitrogen booster delivery pipeline 10, and the counter-pressure chamber 4 is pressurized through the nitrogen counter-pressure delivery pipeline 11 to realize the counter-pressure environment in the counter-pressure chamber.

[0026] The stop valve 7 is used to control the on-off of the helium delivery pipeline 9, the nitrogen boost delivery pipeline 10, the nitrogen back pressure delivery pipeline 11, the liquid nitrogen cooling delivery pipeline 12, the liquid nitrogen test delivery pipeline 13, the low temperature helium delivery pipeline 14, and the liquid nitrogen discharge pipeline 15.

[0027] The pressure reducing valve 6 is used to control the medium flow pressure of the helium delivery pipeline 9, the nitrogen boost delivery pipeline 10, and the nitrogen back pressure delivery pipeline 11, thereby controlling the pressure in the heat exchanger and realizing the flow regulation of the liquid nitrogen cooling delivery pipeline 12 and the liquid nitrogen test delivery pipeline 13.

[0028] The flowmeter 8 is used to measure the medium flow of the liquid nitrogen cooling delivery pipeline 12 , the liquid nitrogen test delivery pipeline 13 , and the helium delivery pipeline 9 .

[0029] Two stop valves are arranged on the liquid nitrogen cooling delivery pipeline 12, the liquid nitrogen test delivery pipeline 13 and the helium delivery pipeline 9, respectively located on both sides of the flow meter.

[0030] Two stop valves are arranged on the nitrogen boost delivery pipeline 10 and the nitrogen counter-pressure delivery pipeline 11, respectively located on both sides of the pressure reducing valve.

[0031] The test method of the test system of the present invention is as follows:

[0032] a. Install and fix the nozzle product in the back pressure chamber 4

[0033] b. The back pressure in the back pressure chamber is regulated by the pressure reducing valve 6 in the liquid nitrogen back pressure delivery pipeline 11.

[0034] c. Open the stop valve 7 in the liquid nitrogen cooling delivery pipeline 12 and the liquid nitrogen test delivery pipeline 13 to deliver liquid nitrogen medium to the heat exchanger 5 and the back pressure chamber 4.

[0035] d. The pressure in the liquid nitrogen container 3 is regulated by the pressure reducing valve 6 in the liquid nitrogen boosting and delivery pipeline 10, thereby achieving the liquid nitrogen medium flow regulation of the liquid nitrogen cooling and delivery pipeline 12 and the liquid nitrogen test delivery pipeline 13.

[0036] e. The flow rate and pressure of the helium medium are regulated by the pressure reducing valve in the helium delivery pipeline 9.

[0037] f. After adjusting the three parameters of liquid nitrogen medium flow, helium medium flow and back pressure in the back pressure chamber to the test requirements, the camera performs high-speed photography through the window of the back pressure chamber 4 to achieve visual measurement of the atomization field of the nozzle product under low temperature back pressure environment.

[0038] The low temperature in the present invention refers to the liquid nitrogen temperature (-196°C), and the back pressure refers to 0-4MPaA. The present invention has the capabilities of liquid nitrogen medium pressurized delivery, helium medium pressurized delivery, helium cooling, low temperature back pressure environment, visualization, etc., so that the atomization characteristics of the nozzle low temperature back pressure environment can be measured.

[0039] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. Liquid rocket engine nozzle back pressure low temperature spray test system, characterized by: It comprises a helium cylinder (1), a nitrogen cylinder (2), a liquid nitrogen container (3), a back pressure chamber (4), a heat exchanger (5), a helium gas delivery pipeline (9), a nitrogen booster delivery pipeline (10), a nitrogen back pressure delivery pipeline (11), a liquid nitrogen cooling delivery pipeline (12), a liquid nitrogen test delivery pipeline (13), a low temperature helium gas delivery pipeline (14), a liquid nitrogen discharge pipeline (15), and a camera; The helium cylinder (1) conveys the helium medium to the heat exchanger (5) through the helium delivery pipeline (9); the nitrogen cylinder (2) is connected to the liquid nitrogen container (3) through the nitrogen booster delivery pipeline (10) to boost the pressure of the liquid nitrogen container (3); and the back pressure chamber (4) is boosted through the nitrogen back pressure delivery pipeline (11); the back pressure chamber (4) is used to simulate the low temperature back pressure environment of the test product, and the nozzle of the liquid rocket engine is fixed inside the back pressure chamber; The liquid nitrogen container (3) is used to store liquid nitrogen medium for testing. The outlet of the liquid nitrogen container (3) provides a cooling medium to the heat exchanger (5) through a liquid nitrogen cooling delivery pipeline (12), and on the other hand, delivers the liquid nitrogen to the liquid rocket engine nozzle liquid path inlet inside the counter-pressure chamber (4) through a liquid nitrogen test delivery pipeline (13); the low-temperature helium after heat exchange in the heat exchanger (5) is delivered to the liquid rocket engine nozzle gas path inlet inside the counter-pressure chamber (4) through a low-temperature helium delivery pipeline (14); the liquid nitrogen and the low-temperature helium are sprayed through the nozzle to form an atomization field in the low-temperature counter-pressure environment inside the counter-pressure chamber, and the camera is used to take pictures of the atomization field; the outlet of the counter-pressure chamber (4) is connected to a liquid nitrogen discharge pipeline (15); The helium gas delivery pipeline (9), the nitrogen boost delivery pipeline (10), the nitrogen counter-pressure delivery pipeline (11), the liquid nitrogen cooling delivery pipeline (12), the liquid nitrogen test delivery pipeline (13), the low-temperature helium gas delivery pipeline (14), and the liquid nitrogen discharge pipeline (15) are all provided with stop valves for controlling on and off.

2. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 1, characterized in that: The helium delivery pipeline (9), the nitrogen boost delivery pipeline (10), and the nitrogen counter-pressure delivery pipeline (11) are all provided with pressure reducing valves, which are used to adjust the outlet pressure of the pipelines.

3. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 1, characterized in that: The liquid nitrogen cooling delivery pipeline (12), the liquid nitrogen test delivery pipeline (13) and the helium delivery pipeline (9) are all provided with flow meters for measuring the medium flow.

4. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 1, characterized in that: The back pressure chamber (4) can form a spray test condition with a stable ambient pressure, thereby simulating the back pressure state in various combustion chambers.

5. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 1, characterized in that: The anti-pressure chamber (4) has a visualization function and an optical coordinate system, which facilitates non-contact measurement using optical measuring equipment.

6. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 1, characterized in that: The anti-pressure cabin is provided with a viewing window, and the camera is located outside the anti-pressure cabin, and the atomization field is photographed through the viewing window of the anti-pressure cabin.

7. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 3, characterized in that: Two stop valves are provided on the liquid nitrogen cooling delivery pipeline (12), the liquid nitrogen test delivery pipeline (13) and the helium delivery pipeline (9), respectively located on both sides of the flow meter.

8. The liquid rocket engine nozzle back pressure low temperature spray test system according to claim 2, characterized in that: Two stop valves are arranged on the nitrogen boosting delivery pipeline (10) and the nitrogen counter-pressure delivery pipeline (11), respectively located on both sides of the pressure reducing valve.

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