Mixed enhanced solid rocket engine jet pipe supplementary combustion device

Abstract

The utility model relates to a mixing enhanced solid rocket engine jet pipe supplementary combustion device which comprises a jet pipe, four air inlet channels are arranged on a shell of the jet pipe in an axial symmetry mode, sudden expansion structures are arranged at the connecting positions of the air inlet channels and an expansion section of the jet pipe, the sudden expansion structures are used for constructing a backflow area, and the backflow area enables gas and air to form vortexes in the backflow area. And more effective mixing and combustion are promoted. External air is compressed through the air inlet channel and introduced into the expansion section of the spray pipe, and a backflow area is constructed at the junction of the air and fuel gas through the sudden expansion structure at the joint of the air inlet channel and the spray pipe, so that fuel which is not fully combusted in the fuel gas can be fully combusted, and the afterburning efficiency of an engine is improved.

Description

Technical Field

[0001] The utility model relates to a supplementary combustion device, in particular to a mixed enhanced solid rocket engine nozzle supplementary combustion device. Background Art

[0002] In the field of aerospace propulsion technology, solid rocket engines are widely used in various aerospace missions due to their simple structure, high cost-effectiveness and rapid response. However, the combustion efficiency of solid rocket engines is limited by the inherent characteristics of solid fuels, especially the utilization rate of oxygen. In order to improve the combustion efficiency, a common method is to introduce atmospheric air through the air inlet and mix it with rocket gas for combustion. However, in the existing technology, there is still room for improvement in the uniformity of the gas and air mixing and the afterburning effect.

[0003] The core innovation of the utility model is that a special structure is designed at the connection between the nozzle and the air inlet of the solid rocket engine, which enhances the afterburning effect by constructing a recirculation zone. This design does not simply improve the mixing ratio of gas and air, but promotes the mixing and reaction between gas and air by creating a local recirculation flow, thereby improving the combustion efficiency and thrust output. Through the design of this recirculation zone, the oxygen in the atmosphere can be more effectively utilized to achieve more complete combustion.

[0004] This innovative structural design provides a new performance improvement method for solid rocket engines by enhancing the afterburning effect. It can not only meet the current higher requirements for rocket engine performance, but also provide a more efficient and reliable power solution for future space missions. Through this design, the utility model is expected to significantly enhance the application potential of solid rocket engines in the aerospace field while maintaining the original advantages of solid rocket engines. Utility Model Content

[0005] In view of the shortcomings of the prior art, the utility model aims to provide a mixing-enhanced solid rocket engine nozzle supplementary combustion device. While maintaining the advantages of the solid rocket engine, four air inlets are designed around the nozzle, and a sudden expansion structure is designed at the connection between the air inlets and the nozzle, so that the rocket nozzle supplementary combustion efficiency is higher, thereby introducing new ideas for the enhanced mixing design of the rocket nozzle supplementary combustion device.

[0006] The utility model is achieved through the following technical solutions.

[0007] A mixing-enhanced solid rocket engine nozzle supplementary combustion device comprises a nozzle, four air inlets are axially symmetrically arranged on the shell of the nozzle, a sudden expansion structure is arranged at the connection between the air inlet and the nozzle expansion section, the sudden expansion structure is used to construct a recirculation zone, and the recirculation zone allows the fuel gas and air to form a vortex in the recirculation zone, thereby promoting more effective mixing and combustion.

[0008] Furthermore, the nozzle is a Laval nozzle, which includes a nozzle inlet, a nozzle throat, and a nozzle outlet, and two ends of the nozzle throat are respectively connected to the nozzle inlet and the nozzle outlet.

[0009] Furthermore, the air intake passage comprises an air intake passage inlet and an air intake passage outlet.

[0010] Furthermore, the height of the sudden expansion structure is 0.1 times the nozzle throat diameter.

[0011] The significant advantage of the hybrid-enhanced solid rocket engine nozzle supplementary combustion device of the utility model is that it innovatively constructs a recirculation zone at the connection between the nozzle and the air inlet. This design significantly improves the mixing efficiency and supplementary combustion effect of the gas and air. The introduction of this recirculation zone not only enhances the thrust output, but also optimizes the flow dynamics, making the combustion process more uniform and sufficient. In addition, the structural design of the utility model is simple and easy to integrate with existing solid rocket engines without large-scale modification, thereby reducing costs and increasing its application potential in the commercial aerospace field. These comprehensive advantages make the utility model have significant competitiveness and practical value in improving the performance of solid rocket engines.

[0012] Compared with the traditional technology, the present invention improves the combustion efficiency and thrust output by enhancing the reflux mixing and combustion reaction instead of changing the mixing ratio. This design improves the performance of solid rocket engines to a certain extent, and is suitable for aerospace applications with specific requirements for fast response and high thrust, providing an efficient and reliable solution for improving the performance of solid rocket engines.

[0013] Compared with the prior art, the advantages of the utility model are: the utility model compresses the external air and introduces it into the nozzle expansion section through the air intake duct, and constructs a reflow zone at the junction of air and fuel gas through the sudden expansion structure at the connection between the air intake duct and the nozzle, so that the fuel that is not fully burned in the fuel gas can be burned more fully, thereby improving the engine's afterburning efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0015] Figure 2 It is a rear view of the utility model;

[0016] Figure 3 It is a cross-sectional view of the utility model;

[0017] Figure 4 It is the streamline principle diagram of the utility model;

[0018] Figure 5 The utility model Figure 3 A partial enlarged view of the middle I expansion structure;

[0019] Figure 6 It is a conventional nozzle with an air inlet (without a sudden expansion structure);

[0020] In the figure: 1. nozzle, 2. air inlet, 3. sudden expansion structure, 4. recirculation area, 5. streamline;

[0021] 101, nozzle inlet, 102, nozzle throat, 103, nozzle outlet;

[0022] 201, air intake duct inlet, 202, air intake duct outlet. DETAILED DESCRIPTION

[0023] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0024] like Figures 1 to 5 As shown, a mixing-enhanced solid rocket engine nozzle supplementary combustion device includes a nozzle 1, four air inlets 2 are axially symmetrically arranged on the shell of the nozzle 1, and a sudden expansion structure 3 is arranged at the connection between the air inlet 2 and the expansion section of the nozzle 1. The sudden expansion structure 3 is used to construct a recirculation zone 4. The recirculation zone 4 allows the fuel gas and air to form a vortex in the recirculation zone to promote more effective mixing and combustion.

[0025] Furthermore, the nozzle 1 is a Laval nozzle, and the nozzle 1 comprises a nozzle inlet 101, a nozzle throat 102, and a nozzle outlet 103, and two ends of the nozzle throat 102 are connected to the nozzle inlet 101 and the nozzle outlet 103 respectively.

[0026] Furthermore, the air intake passage 2 includes an air intake passage inlet 201 and an air intake passage outlet 202 .

[0027] Furthermore, the height of the sudden expansion structure 3 is 0.1 times the diameter of the nozzle throat 102 .

[0028] The utility model designs four air inlets 2 symmetrically on the shell of the nozzle 1. The air inlet 201 of the air inlet 2 sucks air, and it reaches the air inlet outlet 202 after isentropic compression inside the air inlet 2. A part of the air is affected by the sudden expansion structure 3, and mixes with the fuel gas in the nozzle 1 downstream of the sudden expansion structure 3 to form a recirculation zone 4, and achieves stable combustion in the recirculation zone 4. The other part of the air moves normally toward the nozzle outlet 103, and is mixed and burned with the fuel gas in the nozzle 1 during the process. The utility model adds the sudden expansion structure 3 to construct a recirculation zone 4 for stable combustion, which further improves the supplementary combustion efficiency on the basis of the conventional scheme and enhances the performance of the solid rocket engine. The following are specific steps and methods for implementing the device:

[0029] 1. Nozzle design: It adopts the design of conventional Laval nozzle, which includes a convergent-divergent flow path, aiming to accelerate the high-temperature and high-pressure combustion gas generated in the combustion chamber to supersonic speed, thereby generating thrust.

[0030] 2. Inlet duct arrangement: At appropriate positions of the Laval nozzle, four inlet ducts are arranged symmetrically along the axis. These inlet ducts introduce air from the atmosphere into the nozzle to provide sufficient oxygen for supplementary combustion.

[0031] 3. Sudden expansion structure design: A sudden expansion structure is designed at the connection between each air inlet and the nozzle expansion section. While ensuring the formation of a recirculation zone, the gas flow loss in the nozzle is small, and the performance of the supplementary combustion device is better. In the sudden expansion structure designed in the utility model, the device performance is best when the sudden expansion height is 0.1 times the nozzle throat diameter.

[0032] 4. Construction of reflux zone: Through the design of the sudden expansion structure, the flow path of the gas in the nozzle expansion section is changed to form a local reflux area. This design uses the principle of fluid dynamics to guide part of the gas to reflux and mix with the introduced air to form a vortex.

[0033] 5. Vortex formation: In the recirculation area, the mixing of gas and air is more complete due to the effect of vortex, which enhances the afterburning effect. This mixing not only improves the combustion efficiency, but also increases the thrust output.

[0034] Through the above steps, the hybrid-enhanced solid rocket engine nozzle supplementary combustion device of the utility model can significantly improve the performance of the solid rocket engine and meet the requirements for high thrust and high combustion efficiency.

[0035] like Figure 6 As shown, a conventional nozzle is given, in which the air inlet is symmetrically arranged on the nozzle axis, but no sudden expansion structure is arranged at the connection between the air inlet and the nozzle expansion section. The air inlet and the nozzle expansion section are smoothly connected, and a reflow zone cannot be formed, and the effect of supplementary combustion enhancement cannot be achieved.

[0036] The above description is only a preferred embodiment of the present invention, and does not limit the implementation mode and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A mixing enhanced solid rocket engine nozzle supplementary combustion device, characterized in that: The invention comprises a nozzle (1), four air inlet passages (2) are axially symmetrically arranged on the shell of the nozzle (1), a sudden expansion structure (3) is arranged at the connection between the air inlet passages (2) and the expansion section of the nozzle (1), and the sudden expansion structure (3) is used to construct a recirculation zone (4). The recirculation zone (4) allows the gas and air to form a vortex in the recirculation zone, thereby promoting more effective mixing and combustion.

2. A mixing enhanced solid rocket engine nozzle supplementary combustion device according to claim 1, characterized in that: The nozzle (1) is a Laval nozzle, comprising a nozzle inlet (101), a nozzle throat (102), and a nozzle outlet (103), wherein both ends of the nozzle throat (102) are respectively connected to the nozzle inlet (101) and the nozzle outlet (103).

3. A mixing enhanced solid rocket engine nozzle supplementary combustion device according to claim 1, characterized in that: The air intake passage (2) comprises an air intake passage inlet (201) and an air intake passage outlet (202).

4. A mixing enhanced solid rocket engine nozzle supplementary combustion device according to any one of claims 1 to 3, characterized in that: The height of the sudden expansion structure (3) is 0.1 times the diameter of the nozzle throat (102).

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