Test configuration of a modular two-phase ramjet propulsion unit

Abstract

The application discloses a test structure of a modular two-phase ramjet propulsion device, which comprises an inner flow channel assembly, an air inlet assembly, a front assembly and a tail nozzle assembly; the air inlet assembly comprises a central passage, the inner flow channel assembly is coaxially embedded in the central passage in a detachable manner, one end of the front assembly is connected with the front end surface of the inner flow channel assembly and the air inlet assembly, and one end of the tail nozzle assembly is detachably connected with the rear end surface of the air inlet assembly, and the tail nozzle assembly comprises an inner flow channel coaxial with the central passage. The test structure of the modular two-phase ramjet propulsion device can effectively reduce the machining difficulty and improve the machining quality by decomposing the structure of the two-phase ramjet propulsion device, can realize the independent replacement of components, can reduce the machining quantity of the sample in the multi-parameter comparison and verification test process, can reduce the test cost, and can improve the research and development efficiency.

Description

Technical Field

[0001] This invention relates to the field of underwater propulsion devices, and in particular to an experimental structure for a modular two-phase ramjet propulsion device. Background Technology

[0002] The concept of underwater two-phase propulsion originates from air-jet propulsion devices, such as ramjet engines, pulse jet engines, and turbojet engines. The fuel for underwater two-phase propulsion is typically a compressible gas, and in some cases, a water-reactive compound. Underwater two-phase propulsion generates thrust by converting the potential energy of a gas into axial kinetic energy. Compressible bubbles are injected into the working medium, water; the bubbles expand and do work on the water. The two-phase mixture is then ejected at high speed through the nozzle, generating thrust. A significant advantage of this propulsion device is that it has no moving mechanical parts, eliminating the need for complex structures such as shafts and gears, allowing for flexible design within the ship's internal space. Underwater two-phase ramjet engines have no moving parts in contact with the water, making them a relatively simple system. After entering the expansion section, the water's velocity decreases and its static pressure increases. High-pressure gas is introduced at the mixing chamber inlet; the gas pressure is higher than the water pressure, causing the gas and water to mix and form a bubbly gas-liquid two-phase flow. Along the nozzle axis, the mixture pressure decreases, the bubbles expand, and the gas-liquid two-phase bubbly mixture accelerates. The expansion of the bubble does work on the water, forming a high-speed water jet, which in turn generates thrust.

[0003] The novel two-phase ramjet propulsion device uses steam as its power source, achieving propulsion based on the principle of direct steam-water contact condensation and pressurization. It further enhances propulsion efficiency and stability by injecting a small amount of air. This novel two-phase ramjet propulsion device has a complex structure, including intricate local structures such as air injection holes, steam nozzles, steam channels, air channels, and tail nozzles. Its compact arrangement makes integrated machining difficult, particularly the internal air exhaust holes. Furthermore, the current technology for this novel two-phase ramjet propulsion device is not yet mature, requiring multi-parameter comparative studies of different local structural designs. This necessitates the fabrication of multiple prototypes for testing during the multi-parameter comparative verification process, resulting in a large production volume requirement.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of the invention and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] The purpose of this invention is to provide a test structure for a modular two-phase ramjet propulsion device. By decomposing the two-phase ramjet propulsion device, it can effectively reduce the processing difficulty and improve the processing quality. It can also realize the individual replacement of components, reduce the number of sample processing in the multi-parameter comparison and verification test, reduce the test cost, and improve the R&D efficiency.

[0006] To achieve the above objectives, the present invention provides a test structure for a modular two-phase ramjet propulsion device, including an inner flow channel assembly, an air intake assembly, a front assembly, and a tail nozzle assembly; the air intake assembly includes a central channel, and the inner flow channel assembly is detachably and coaxially embedded in the central channel; one end face of the front assembly is simultaneously connected to the front end face of both the inner flow channel assembly and the air intake assembly; one end of the tail nozzle assembly is detachably connected to the rear end face of the air intake assembly, and the tail nozzle assembly includes an inner flow channel coaxial with the central channel.

[0007] In a preferred embodiment, the inner flow channel assembly includes multiple sets of air vents evenly arranged around the sidewall of the inner flow channel assembly, with each set of air vents arranged along the axial direction of the inner flow channel assembly.

[0008] In a preferred embodiment, the diameter of each set of air exhaust holes gradually increases from the front end to the rear end of the inner flow channel assembly.

[0009] In a preferred embodiment, the air intake assembly includes a steam flow channel, which is disposed perpendicularly to the axis of the air intake assembly on the side wall of the air intake assembly. The steam flow channel passes through the interior of the side wall of the air intake assembly and communicates with the inner flow channel at the outer circumference of the rear end face of the air intake assembly.

[0010] In a preferred embodiment, the air intake assembly further includes an air flow channel, which is disposed outside the steam flow channel. Air enters the inner wall of the air intake assembly through the space between the outer wall of the steam flow channel and the inner wall of the air flow channel, and then enters the interior of the inner flow channel assembly after passing through multiple sets of air exhaust holes, and finally enters the inner flow channel from the tail of the inner flow channel assembly.

[0011] In a preferred embodiment, the steam flow path and the air flow path are not connected inside the air intake assembly.

[0012] In a preferred embodiment, the front end face of the front component is an arc surface and the rear end face is a stepped surface, the stepped surface being used to connect with the front end faces of the inner flow channel component and the air intake component, respectively.

[0013] In a preferred embodiment, the test structure of the modular two-phase ramjet propulsion device further includes a first connecting screw, a second connecting screw, and a third connecting screw; the first connecting screw is used to connect the stepped surface to the front end face of the inner flow channel assembly; the second connecting screw is used to connect the stepped surface to the front end face of the air intake assembly; and the third connecting screw is used to connect the front end face of the tail nozzle assembly to the rear end face of the air intake assembly.

[0014] Compared with the prior art, the test structure of the modular two-phase ramjet propulsion device of the present invention has the following beneficial effects: by reasonably disassembling the structure, the two-phase ramjet propulsion device is disassembled into four parts, and the key components such as the air exhaust port, steam nozzle, and tail nozzle are separated and assembled by screw connection. On the one hand, it can effectively reduce the processing difficulty and improve the processing quality. On the other hand, it can realize the individual replacement of components, reduce the number of sample processing in the multi-parameter comparison and verification test, reduce the test cost, and improve the R&D efficiency. Attached Figure Description

[0015] Figure 1 This is a front cross-sectional schematic diagram of an experimental structure according to an embodiment of the present invention;

[0016] Figure 2 This is a side view schematic diagram of the test structure according to an embodiment of the present invention;

[0017] Figure 3 This is a top view schematic diagram of the test structure according to an embodiment of the present invention;

[0018] Figure 4 yes Figure 1 A magnified view of a portion of point I;

[0019] Figure 5 yes Figure 1 A magnified view of part II.

[0020] Explanation of key figure labels:

[0021] 1-Inner flow channel assembly, 2-Front assembly, 3-First connecting screw, 4-Second connecting screw, 5-Intake assembly, 6-Steam flow channel, 7-Air flow channel, 8-Third connecting screw, 9-Tail nozzle assembly, 10-Inner flow channel, 11-Air exhaust port. Detailed Implementation

[0022] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings, but it should be understood that the scope of protection of the present invention is not limited to the specific embodiments.

[0023] Unless otherwise expressly stated, throughout the specification and claims, the term "comprising" or its variations such as "including" or "comprises" shall be understood to include the stated elements or components without excluding other elements or other components.

[0024] like Figures 1 to 3As shown, a test structure of a modular two-phase ramjet propulsion device according to a preferred embodiment of the present invention mainly includes an inner flow channel assembly 1, an air intake assembly 5, a front assembly 2, and a tail nozzle assembly 9, etc.; the air intake assembly 5 includes a central channel, and the inner flow channel assembly 1 is detachably and coaxially embedded in the central channel; one end face of the front assembly 2 is simultaneously connected to the front end face of both the inner flow channel assembly 1 and the air intake assembly 5; one end of the tail nozzle assembly 9 is detachably connected to the rear end face of the air intake assembly 5, and the tail nozzle assembly 9 includes an inner flow channel 10 coaxial with the central channel.

[0025] In some embodiments, the inner flow channel assembly 1 includes multiple sets of air vent holes 11, which are arranged parallel to each other and uniformly in a ring around the side wall of the inner flow channel assembly 1. Each set of air vent holes 11 includes multiple vent holes arranged along the axial direction of the inner flow channel assembly 1, and the diameter of each set of air vent holes 11 gradually increases from the front end to the rear end of the inner flow channel assembly 1.

[0026] In some embodiments, the air intake assembly 5 includes a steam channel 6, which is disposed perpendicularly to the axis of the air intake assembly 5 on the side wall of the air intake assembly 5. After passing through the inside of the side wall of the air intake assembly 5, the steam channel 6 communicates with the inner channel 10 at the outer circumference of the rear end face of the air intake assembly 5.

[0027] In some embodiments, the intake assembly 5 further includes an airflow channel 7, which surrounds the steam flow channel 6. Air enters the inner wall of the intake assembly 5 through the space between the outer wall of the steam flow channel 6 and the inner wall of the airflow channel 7, then passes through multiple sets of air exhaust holes 11 before entering the interior of the inner flow channel assembly 1, and finally enters the inner flow channel 10 from the tail end of the inner flow channel assembly 1. The steam flow channel 6 and the airflow channel 7 are not connected inside the intake assembly 5.

[0028] In some embodiments, the front end face of the front component 2 is an arc surface and the rear end face is a stepped surface, the stepped surface being used to connect with the front end faces of the inner flow channel component 1 and the air intake component 5, respectively.

[0029] In some embodiments, the test structure of the modular two-phase ramjet propulsion device further includes a first connecting screw 3, a second connecting screw 4, and a third connecting screw 8; the first connecting screw 3 is used to connect the stepped surface to the front end face of the inner flow channel assembly 1; the second connecting screw 4 is used to connect the stepped surface to the front end face of the air intake assembly 5; and the third connecting screw 8 is used to connect the front end face of the tail nozzle assembly 9 to the rear end face of the air intake assembly 5.

[0030] In some embodiments, the working principle of the test structure of the modular two-phase ramjet propulsion device of the present invention is roughly as follows: water flows into the inner flow channel assembly 1 from the front assembly 2, high-pressure air passes through the air flow channel 7 and multiple sets of air exhaust holes 11 to form bubbles, which enter the inner flow channel assembly 1 and mix with the water flow. High-temperature and high-pressure steam enters the inner flow channel 10 of the tail nozzle assembly 9 from the tail of the inner flow channel assembly 1 through the steam flow channel 6. In the inner flow channel 10, it mixes again with the mixture of water flow and bubbles to generate thrust and is ejected from the tail of the tail nozzle assembly 9.

[0031] In summary, the experimental structure of the modular two-phase ramjet propulsion device of the present invention has the following advantages: by reasonably disassembling the structure, the two-phase ramjet propulsion device is disassembled into four parts, and key components such as the air exhaust port, steam nozzle, and tail nozzle are separated and assembled by screw connection. On the one hand, this can effectively reduce the processing difficulty and improve the processing quality. On the other hand, it can realize the individual replacement of components, reduce the number of sample processing in the multi-parameter comparison and verification test, reduce the test cost, and improve the R&D efficiency.

[0032] The foregoing description of specific exemplary embodiments of the invention is for illustrative and explanatory purposes. These descriptions are not intended to limit the invention to the precise forms disclosed, and it will be apparent that many changes and variations can be made in accordance with the foregoing teachings. The exemplary embodiments were chosen and described in order to explain the specific principles of the invention and its practical application, thereby enabling those skilled in the art to implement and utilize various different exemplary embodiments of the invention, as well as various different choices and variations. The scope of the invention is intended to be defined by the claims and their equivalents.

Claims

1. A test structure for a modular two-phase ramjet propulsion device, characterized in that, include: Internal flow channel assembly; An intake assembly includes a central channel, wherein the inner flow channel assembly is detachably and coaxially embedded within the central channel; The front assembly, one end face of which is connected to both the inner flow channel assembly and the front end face of the intake assembly; and The tail nozzle assembly has one end detachably connected to the rear end face of the air intake assembly, and the tail nozzle assembly includes an inner flow channel coaxial with the central channel. The inner flow channel assembly includes multiple sets of air exhaust holes, which are evenly arranged around the side wall of the inner flow channel assembly, and each set of air exhaust holes is arranged along the axial direction of the inner flow channel assembly. The air intake assembly includes a steam flow channel, which is disposed perpendicularly to the axis of the air intake assembly on the side wall of the air intake assembly. The steam flow channel passes through the interior of the side wall of the air intake assembly and then communicates with the inner flow channel at the outer circumference of the rear end face of the air intake assembly. The air intake assembly further includes an air flow channel, which is disposed outside the steam flow channel. Air enters the inner wall of the air intake assembly through the space between the outer wall of the steam flow channel and the inner wall of the air flow channel, and then enters the interior of the inner flow channel assembly after passing through the multiple sets of air exhaust holes. Finally, it enters the inner flow channel from the tail of the inner flow channel assembly. Water flows into the inner flow channel assembly from the front component. High-pressure air passes through the air channel and the multiple sets of air exhaust holes to form bubbles, which then enter the inner flow channel assembly and mix with the water. High-temperature and high-pressure steam enters the inner flow channel of the tail nozzle assembly from the tail of the inner flow channel assembly through the steam channel. Inside the inner flow channel, the steam mixes again with the water and bubble mixture, generating thrust that is ejected from the tail of the tail nozzle assembly.

2. The experimental structure of the modular two-phase ramjet propulsion device as described in claim 1, characterized in that, The diameter of each set of air exhaust holes gradually increases from the front end to the rear end of the inner flow channel assembly.

3. The experimental structure of the modular two-phase ramjet propulsion device as described in claim 1, characterized in that, The steam flow channel and the air flow channel are not connected inside the air intake assembly.

4. The experimental structure of the modular two-phase ramjet propulsion device as described in claim 1, characterized in that, The front end face of the front component is an arc surface, and the rear end face is a stepped surface. The stepped surface is used to connect with the front end faces of the inner flow channel component and the air intake component, respectively.

5. The test structure of the modular two-phase ramjet propulsion device as described in claim 4, characterized in that, Also includes: A first connecting screw is used to connect the stepped surface to the front end face of the inner flow channel assembly; A second connecting screw is used to connect the stepped surface to the front end face of the intake assembly; and The third connecting screw is used to connect the front end face of the tail nozzle assembly to the rear end face of the air intake assembly.

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