Liquid rocket engine nozzle backpressure cryogenic spray test system

Abstract

The present invention relates to a liquid rocket engine nozzle back-pressure low-temperature spray test system. A low-temperature helium medium is supplied via a helium cylinder, a helium delivery pipeline, a heat exchanger, and a low-temperature helium delivery pipeline. Cryogenic cooling of the helium is achieved via a nitrogen cylinder, a nitrogen booster delivery pipeline, a liquid nitrogen container, and a liquid nitrogen cooling delivery pipeline. A back-pressure chamber back-pressure environment is achieved via a nitrogen cylinder and a nitrogen back-pressure delivery pipeline. Liquid nitrogen test medium is supplied via a nitrogen cylinder, a nitrogen booster delivery pipeline, a liquid nitrogen container, and a liquid nitrogen test delivery pipeline. The back-pressure chamber is used to secure the product and create a low-temperature back-pressure spray environment, allowing for visual measurement of the spray field. This allows for measurement of the atomization characteristics of the nozzle in a low-temperature back-pressure environment.

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 oxygen in hydrogen-oxygen liquid rocket engines are atomized through nozzles at supercritical pressure. However, the atomization mechanism and state under supercritical and subcritical pressure conditions are different, and its combustion stability has become one of the key technologies in research and development. Therefore, studying the atomization characteristics of cryogenic fluids under supercritical conditions will have a significant guiding role in research and development. 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 studying 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 existing technology 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 in the low-temperature back-pressure environment can be measured.

[0004] The solution of the present invention is:

[0005] Liquid rocket engine nozzle backpressure cryogenic spray test system, including helium cylinder, nitrogen cylinder, liquid nitrogen container, backpressure chamber, heat exchanger, helium delivery pipeline, nitrogen booster delivery pipeline, nitrogen backpressure delivery pipeline, liquid nitrogen cooling delivery pipeline, liquid nitrogen test delivery pipeline, cryogenic helium delivery pipeline, liquid nitrogen discharge pipeline, and 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 increase the pressure of the liquid nitrogen container. The nitrogen back-pressure delivery pipeline also increases the pressure of the back-pressure chamber. The back-pressure chamber is used to simulate the low-temperature back-pressure environment of the test product. The liquid rocket engine nozzle 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 the refrigerant medium to the heat exchanger through the liquid nitrogen cooling delivery pipeline. On the other hand, the liquid nitrogen is delivered to the liquid rocket engine nozzle liquid inlet inside the back-pressure chamber through the 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 inlet inside the back-pressure chamber through the low-temperature helium delivery pipeline. After the liquid nitrogen and low-temperature helium are sprayed through the nozzle, an atomization field is formed in the low-temperature back-pressure environment inside the back-pressure chamber. The camera is used to capture the atomization field. The back-pressure chamber outlet is connected to the liquid nitrogen discharge pipeline.

[0008] The helium delivery pipeline, nitrogen boost delivery pipeline, nitrogen back pressure delivery pipeline, liquid nitrogen cooling delivery pipeline, liquid nitrogen test delivery pipeline, low-temperature helium delivery pipeline, and liquid nitrogen discharge pipeline are all equipped 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 both 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 utilizes a helium cylinder, a helium delivery pipeline, a heat exchanger, and a cryogenic helium delivery pipeline to achieve cryogenic cooling of the helium. A nitrogen cylinder, a nitrogen booster delivery pipeline, a liquid nitrogen container, and a liquid nitrogen cooling delivery pipeline are used to achieve cryogenic cooling of the helium. A back-pressure chamber environment is achieved through a nitrogen cylinder and a nitrogen back-pressure delivery pipeline. A 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 back-pressure chamber allows for product installation and securement, a low-temperature back-pressure spray environment, and visual measurement of the spray field. This allows for measurement of the nozzle's atomization characteristics in a low-temperature back-pressure environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Schematic diagram of the present invention. DETAILED DESCRIPTION

[0019] The present invention will be further described below with reference to 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 backpressure 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 boost delivery pipeline 10, a nitrogen backpressure delivery pipeline 11, a liquid nitrogen cooling delivery pipeline 12, a liquid nitrogen test delivery pipeline 13, a low-temperature helium delivery pipeline 14, a liquid nitrogen discharge pipeline 15, and a camera.

[0022] Liquid nitrogen container 3 is used to store liquid nitrogen for testing. It is pressurized and delivered to the container via nitrogen cylinder 2 and nitrogen pressurization delivery pipeline 10. Liquid nitrogen container 3 provides refrigerant to heat exchanger 5 via liquid nitrogen cooling delivery pipeline 12, cryogenically cooling the helium. Simultaneously, liquid nitrogen container 3 delivers liquid nitrogen to backpressure chamber 4 via liquid nitrogen test delivery pipeline 13, providing liquid nitrogen for testing.

[0023] The back-pressure chamber 4 is used to simulate the back-pressure environment of the test product while meeting the requirements for optical measurement of the product's atomization and mixing characteristics. It can create a spray test condition with a stable ambient pressure, thereby simulating the back-pressure state within various combustion chambers. It also features visualization capabilities and an optical coordinate system, facilitating non-contact measurement using various optical measurement equipment. The nozzle product is fixed within the back-pressure chamber. Liquid nitrogen and helium media delivered by the liquid nitrogen test delivery line 13 and cryogenic helium delivery line 14 are connected to the liquid and gas inlets of the nozzle product, respectively, via metal hoses. Spray forms an atomization field within the low-temperature, back-pressure environment within the back-pressure chamber, and a camera performs high-speed photography and measurement through the back-pressure chamber's window.

[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] Helium cylinder 1 supplies helium, which is transported to heat exchanger 5 via helium delivery line 9 for cryogenic cooling. After cooling, the helium enters the back-pressure chamber via cryogenic helium delivery line 14, providing the test medium helium. Nitrogen cylinders supply nitrogen, pressurizing liquid nitrogen container 3 via nitrogen booster delivery line 10 and back-pressure chamber 4 via nitrogen back-pressure delivery line 11, creating a counter-pressure environment within the chamber.

[0026] The stop valves 7 are 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, respectively, 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 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.

[0030] Two stop valves are provided on both the nitrogen boost delivery pipeline 10 and the nitrogen counter-pressure delivery pipeline 11, which are 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 counter-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 cabin 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 regulating the flow of liquid nitrogen medium in the liquid nitrogen cooling and delivery pipeline 12 and the liquid nitrogen test delivery pipeline 13.

[0036] e. The helium medium flow pressure is regulated by the pressure reducing valve in the helium delivery pipeline 9.

[0037] f. After simultaneously adjusting the three parameters of liquid nitrogen medium flow, helium medium flow, and back pressure in the back-pressure chamber to the required test conditions, a 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 in a low-temperature back-pressure environment.

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

[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 delivery pipeline (9), a nitrogen boost 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 delivery pipeline (14), a liquid nitrogen discharge pipeline (15), and a camera; The helium cylinder (1) delivers 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 on the other hand, 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 liquid rocket engine nozzle 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 refrigerant medium to the heat exchanger (5) through a liquid nitrogen cooling delivery pipeline (12). On the other hand, the liquid nitrogen is delivered to the liquid rocket engine nozzle liquid path inlet inside the back 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 back 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 back pressure environment inside the back pressure chamber, and the camera is used to photograph the atomization field; the outlet of the back pressure chamber (4) is connected to a liquid nitrogen discharge pipeline (15); The helium 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 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 cabin (4) can form a spray test working 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 counter-pressure cabin is provided with a viewing window, and the camera is located outside the counter-pressure cabin and films the atomization field through the viewing window of the counter-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 each of the liquid nitrogen cooling delivery pipeline (12), the liquid nitrogen test delivery pipeline (13), and the helium delivery pipeline (9), and are located on both sides of the flow meter respectively.

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

Images