A supersonic shock wave nozzle pressure reducing device

Abstract

The application belongs to the technical field of aircraft structure design, and particularly relates to a supersonic shock wave nozzle pressure reducing device. The rear end of the device is detachably installed at the supersonic shock wave nozzle, and the pipe wall of the supersonic shock wave nozzle pressure reducing device is provided with fuselage shielding nozzles (3) and lateral expansion nozzles (4). At least one fuselage shielding nozzle (3) is located on the side of the supersonic shock wave nozzle pressure reducing device close to the aircraft fuselage, the lateral expansion nozzles (4) and the fuselage shielding nozzles (3) are spaced apart by a set angle along the circumferential direction of the pipeline, and the lateral expansion nozzles (4) and the fuselage shielding nozzles (3) both have airflow passages (1). The airflow passages (1) are communicated with the internal pipeline at the rear end of the supersonic shock wave nozzle pressure reducing device, and the airflow passages (1) have outwardly expanding openings at the rear end of the supersonic shock wave nozzle pressure reducing device. The application reduces the pressure impact intensity on the side of the fuselage, and ensures the safety of the fuselage structure and equipment cabin.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design technology, and specifically relates to a supersonic shock wave nozzle decompression device. Background Technology

[0002] Modern aircraft are equipped with a device that can generate high-intensity transient continuous impacts. This device can generate supersonic shock wave gas. The nozzle that emits the shock wave gas is close to the fuselage. During the process of the shock wave gas being ejected, due to flow separation, shock wave motion and coupling, continuous high-intensity pressure and velocity pulsation impacts are generated, which have a serious safety impact on the structures and airborne equipment near the aircraft.

[0003] Currently, the main purpose of supersonic shock wave nozzle decompression devices is to reduce the impact of noise on the surrounding environment and users; there are no decompression devices for reducing noise at close range on aircraft structures. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a supersonic shock wave nozzle decompression device for controlling and improving the shock pressure field distribution at extremely close range of the shock wave nozzle, thereby resolving safety issues related to the fuselage structure and equipment compartment caused by supersonic shock waves.

[0005] The supersonic shock wave nozzle decompression device provided in this application has a rear end that is detachably installed at the supersonic shock wave nozzle. It has a pipe through which the supersonic shock wave passes. A fuselage shielding nozzle and a lateral expansion nozzle are arranged on the pipe wall of the supersonic shock wave nozzle decompression device along the circumference of the pipe. At least one fuselage shielding nozzle is located on the side of the supersonic shock wave nozzle decompression device closer to the aircraft fuselage. The lateral expansion nozzle and the fuselage shielding nozzle are spaced at an angle along the circumference of the pipe. Both the lateral expansion nozzle and the fuselage shielding nozzle have airflow channels. The airflow channels are connected to the pipe at the rear end of the supersonic shock wave nozzle decompression device. The airflow channels have outwardly expanding openings at the rear end of the supersonic shock wave nozzle decompression device.

[0006] Preferably, the fuselage shielding nozzle comprises two nozzles, which are symmetrically distributed circumferentially along the pipe, and the lateral expansion nozzle comprises two nozzles, which are symmetrically distributed circumferentially along the pipe.

[0007] Preferably, the airflow channel is a labyrinth-type loop channel, which includes at least a return channel for guiding the airflow in the opposite direction to the airflow in the pipe.

[0008] Preferably, the tube wall of the supersonic shock wave nozzle decompression device is provided with a bypass pressure relief hole that connects the airflow channel to the outside.

[0009] Preferably, the bypass pressure relief holes include multiple holes, each extending along the axial direction of the pipeline and arranged near the rear end of the supersonic shock wave nozzle pressure relief device.

[0010] Preferably, the supersonic shock wave nozzle decompression device has a connecting thread at its rear end, which is used to connect to the supersonic shock wave nozzle.

[0011] This application reduces the pressure impact intensity on the fuselage side, ensuring the safety of the fuselage structure and equipment bay. Attached Figure Description

[0012] Figure 1 This is a schematic diagram along the pipeline direction of a preferred embodiment of the supersonic shock wave nozzle pressure reducing device of this application.

[0013] Figure 2 For this application Figure 1 The diagram shows a cross-sectional view of the structure shown.

[0014] Figure 3 For this application Figure 1 BB cross-sectional diagram of the structure shown.

[0015] Among them, 1-airflow channel, 11-return channel, 2-bypass pressure relief hole, 3-body shield nozzle, 4-lateral expansion nozzle, and 5-connecting thread. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0017] This application provides a supersonic shock wave nozzle pressure reduction device, such as... Figures 1 to 3As shown, the rear end of the supersonic shock wave nozzle decompression device is detachably installed at the supersonic shock wave nozzle. It has a pipe through which the supersonic shock wave passes. A fuselage shielding nozzle 3 and a lateral expansion nozzle 4 are arranged on the pipe wall of the supersonic shock wave nozzle decompression device along the circumference of the pipe. At least one fuselage shielding nozzle 3 is located on the side of the supersonic shock wave nozzle decompression device closer to the aircraft fuselage. The lateral expansion nozzle 4 and the fuselage shielding nozzle 3 are spaced at an angle along the circumference of the pipe. Both the lateral expansion nozzle 4 and the fuselage shielding nozzle 3 have an airflow channel 1. The airflow channel 1 is connected to the pipe at the rear end of the supersonic shock wave nozzle decompression device. The airflow channel 1 has an outwardly expanding opening at the rear end of the supersonic shock wave nozzle decompression device.

[0018] Both the lateral expansion nozzle 4 and the fuselage shield nozzle 3 of this application may include multiple nozzles. For example, in some optional embodiments, the fuselage shield nozzle 3 includes two nozzles, which are symmetrically distributed along the circumference of the pipe. The lateral expansion nozzle 4 includes two nozzles, which are symmetrically distributed along the circumference of the pipe.

[0019] refer to Figure 1 The fuselage shielding nozzle 3 is a Laval-shaped nozzle arranged near the fuselage side and symmetrically on the pressure reducing device. After the high-pressure airflow is ejected from the nozzle, it forms a supersonic airflow barrier, thereby shielding the main jet flow from expanding towards the fuselage and reducing the intensity of the shock wave on the fuselage side. The lateral expansion nozzle 4 is a Laval-shaped nozzle arranged in the vertical direction. After the high-pressure airflow is ejected obliquely outward from the nozzle, it forms an obliquely outward supersonic airflow. Its ejection effect and the shielding effect of the fuselage shielding nozzle together guide the supersonic high-pressure airflow to expand in the vertical direction.

[0020] In some alternative embodiments, the airflow channel 1 is a labyrinthine loop channel, which includes at least a return channel 11 for guiding the airflow in the opposite direction to the airflow in the pipe.

[0021] In this embodiment, the purpose of the labyrinth-shaped loop channel is to reduce the energy of the high-pressure airflow while changing the flow direction of the nozzle flow field and increasing the flow distance of the high-pressure airflow to delay the arrival time at the outlet, thereby mitigating or avoiding the impact of the shock wave on the accuracy of the airborne equipment.

[0022] In some alternative implementations, such as Figure 2 and Figure 3 As shown, the supersonic shock wave nozzle depressurization device has a bypass pressure relief hole 2 on its pipe wall, connecting the airflow channel 1 to the outside. The bypass pressure relief hole 2 allows some high-pressure airflow to pass through.

[0023] In some alternative embodiments, the bypass pressure relief hole 2 includes a plurality of bypass pressure relief holes 2, each of which extends along the axial direction of the pipeline and is arranged near the rear end of the supersonic shock wave nozzle pressure relief device.

[0024] In some alternative embodiments, the rear end of the supersonic shock wave nozzle decompression device is provided with a connecting thread 5, which is used to connect to the supersonic shock wave nozzle. Figure 2 and Figure 3 In the given example, the connecting thread 5 is an internal thread, and the corresponding rear end of the supersonic shock wave nozzle decompression device is sleeved on the outside of the supersonic shock wave nozzle.

[0025] This application reduces the pressure impact intensity on the fuselage side due to the shielding and ejection effect of the supersonic airflow from the fuselage shielding nozzles and lateral expansion nozzles. The symmetrical arrangement of the fuselage shielding nozzles also symmetrically reduces or avoids the impact on design accuracy. Since the main flow direction remains unchanged, the structural stress is not altered. The labyrinth design delays the airflow arrival time at the nozzle, reducing or avoiding impact on the ejected material and not affecting the operational accuracy of airborne equipment. The above design solves the problem of the impact of supersonic shock wave jets on the structural safety of the fuselage.

[0026] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A supersonic shock wave nozzle decompression device, characterized in that, The supersonic shock wave nozzle decompression device is detachably installed at the rear end of the supersonic shock wave nozzle. It has a pipe through which the supersonic shock wave passes. A fuselage shielding nozzle (3) and a lateral expansion nozzle (4) are provided on the pipe wall of the supersonic shock wave nozzle decompression device along the circumference of the pipe. At least one fuselage shielding nozzle (3) is located on the side of the supersonic shock wave nozzle decompression device close to the aircraft fuselage. The lateral expansion nozzle (4) and the fuselage shielding nozzle (3) are spaced at an angle along the circumference of the pipe. Both the lateral expansion nozzle (4) and the fuselage shielding nozzle (3) have airflow channels (1). The airflow channels (1) are connected to the pipe at the rear end of the supersonic shock wave nozzle decompression device. The airflow channels (1) have outwardly expanding openings at the rear end of the supersonic shock wave nozzle decompression device.

2. The supersonic shock wave nozzle decompression device as described in claim 1, characterized in that, The fuselage shielding nozzle (3) comprises two nozzles, which are symmetrically distributed along the circumference of the pipe. The lateral expansion nozzle (4) comprises two nozzles, which are symmetrically distributed along the circumference of the pipe.

3. The supersonic shock wave nozzle decompression device as described in claim 1, characterized in that, The airflow channel (1) is a labyrinth-type loop channel, which includes at least a return channel (11) for guiding the airflow in the opposite direction to the airflow in the pipe.

4. The supersonic shock wave nozzle decompression device as described in claim 1, characterized in that, The supersonic shock wave nozzle pressure reducing device has a bypass pressure relief hole (2) on its pipe wall that connects the airflow channel (1) to the outside.

5. The supersonic shock wave nozzle decompression device as described in claim 4, characterized in that, The bypass pressure relief hole (2) includes multiple holes, each of which extends along the axial direction of the pipeline and is arranged near the rear end of the supersonic shock wave nozzle pressure relief device.

6. The supersonic shock wave nozzle decompression device as described in claim 1, characterized in that, The supersonic shock wave nozzle decompression device is provided with a connecting thread (5) at the rear end, and the supersonic shock wave nozzle is connected through the connecting thread (5).

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