Multiple ignition device for hydrogen peroxide kerosene rotating detonation rocket combustor

Abstract

The application discloses a multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber and relates to the technical field of aerospace. The device comprises a combustion chamber and a propellant delivery device. The combustion chamber is a double-layer shell structure. A kerosene cooling channel is arranged between the shells. An annular kerosene collecting cavity is arranged around the tail of the shell and is connected with the inlet of the cooling channel. The hydrogen peroxide kerosene propellant ignition device enables the rotating detonation rocket engine to have multiple starting capabilities. The ignition and detonation can be realized by controlling the valve, and the reusable engineering application potential of the rotating detonation rocket engine is significantly improved. The kerosene is ignited by using hydrogen peroxide catalysis, the ignition process is realized, and no additional device such as a spark plug is needed, so that the structure is simple. The device can realize multiple ignitions by controlling the on-off of the propellant valve, and multiple ignition devices are not needed, so that the reliability of the system is significantly improved.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a multiple ignition device for the combustion chamber of a hydrogen peroxide kerosene rotating detonation rocket. Background Technology

[0002] 1. Currently, most rotating detonation rocket engines use pre-detonation tubes to ignite and detonate by pre-introducing propellant. No ignition device has been found that can enable multiple ignitions of the rotating detonation rocket combustion chamber. However, in the future application of rotating detonation rocket engines, whether for reusable use or high-precision orbital insertion, multiple ignitions will be an inevitable requirement.

[0003] 2. Current rocket technologies often employ the method of increasing the number of igniters to achieve multiple ignitions. On the one hand, this increases the weight of the propulsion system, resulting in limited payload capacity. On the other hand, too many components can reduce system reliability and easily lead to ignition and detonation failure during launch.

[0004] 3. Traditional rotating detonation engines mostly use gaseous propellants in their pre-detonation tubes, which limits their application in liquid rocket engines, especially for hydrogen peroxide / kerosene liquid rocket engines. In order to save volume and weight, it is difficult to carry excess gaseous propellant and related storage and transportation systems.

[0005] Although hydrogen peroxide / kerosene has self-ignition properties and the energy it releases meets the ignition and detonation requirements, compared to air or gaseous oxygen typically used in pre-detonation tubes, hydrogen peroxide has a higher specific heat capacity (approximately 2.6 kJ / kg·K, higher than air by 1.0 kJ / kg·K or gaseous oxygen by 0.9 kJ / kg·K) and undergoes a vaporization process. This makes it difficult for hydrogen peroxide and kerosene to quickly form a good mixture, resulting in a slightly longer ignition and detonation delay. Pre-detonation tubes require a rapid transition from slow combustion to detonation and need to quickly form a good mixture. Directly introducing hydrogen peroxide / kerosene makes it difficult to achieve ignition and detonation. Summary of the Invention

[0006] The purpose of this invention is to provide a multiple ignition device for the combustion chamber of a hydrogen peroxide kerosene rotating detonation rocket, in order to solve the above-mentioned problems.

[0007] To achieve the above objectives, the present invention provides the following technical solution: a multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber, comprising a combustion chamber and a propellant delivery device, wherein the combustion chamber is a double-shell structure, a kerosene cooling channel is provided between the shells, and an annular kerosene collection chamber is provided around the tail of the shell, and the kerosene collection chamber is connected to the inlet of the cooling channel. A kerosene inlet is provided on the shell of the kerosene collecting chamber for connecting to external pipelines; A conical plug is connected to the center of the combustion chamber, which together with the combustion chamber shell forms a plug-type nozzle; A pre-explosion pipe is connected to the side tangent of the combustion chamber via a flange. The injection end of the pre-explosion pipe is connected to the combustion chamber along the tangent direction of the side wall of the combustion chamber for ignition and starting, igniting the kerosene and hydrogen peroxide in the combustion chamber. The propellant delivery device includes a propellant storage chamber and multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles; the propellant storage chamber consists of two interconnected and independent cylindrical hydrogen peroxide chambers and kerosene chambers; a hydrogen peroxide inlet is provided on the hydrogen peroxide chamber; the rear end of the kerosene chamber is connected to the opening end of the kerosene cooling channel in the combustion chamber.

[0008] Preferably, the pre-explosion tube includes a cylindrical cavity, with a catalytic ignition hydrogen peroxide inlet nozzle at the front end and a flame guide tube coaxially connected and communicating with the rear end. A kerosene inlet nozzle is provided on the side, and the end of the flame guide tube is connected to the combustion chamber. A liquid flow equalization plate and a decomposition gas rectifier grid are arranged at intervals in front and behind the cylindrical cavity. The space between the liquid flow equalization plate and the decomposition gas rectifier grid is used to fill a catalytic bed, which is composed of several silver meshes.

[0009] Preferably, both the liquid flow equalization plate and the decomposition gas rectification grid are circular plates with multiple through holes evenly distributed on them. The multiple through holes are evenly spaced in the radial and circumferential directions to form multiple concentric circle structures; and the through holes on the decomposition gas rectification grid are larger than the through holes on the liquid flow equalization plate.

[0010] Preferably, a Shchelkin spiral tube is installed inside the flame guide tube; the length-to-diameter ratio of the Shchelkin spiral tube is approximately 6:1, and the ratio of the spiral diameter to the inner diameter of the pre-explosion tube is approximately 1:10.

[0011] Preferably, there are multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles, all connected to the propellant storage chamber, for injecting hydrogen peroxide and kerosene into the combustion chamber.

[0012] Preferably, the hydrogen peroxide / kerosene bicomponent centrifugal nozzle includes: a kerosene swirl chamber, which is formed by a conical shell; the kerosene swirl chamber is located in the kerosene cavity section, and kerosene tangential holes are spaced apart on the outer wall of the larger end of the shell of the kerosene swirl chamber, each kerosene tangential hole being connected to the kerosene cavity; an annular kerosene injection hole is formed circumferentially around the end of the smaller end of the shell of the kerosene swirl chamber; a hydrogen peroxide swirl chamber, which is formed by a columnar shell, and hydrogen peroxide tangential holes are spaced apart on the side wall of the front end of the shell, and a columnar hydrogen peroxide outlet pipe is connected to the rear end of the columnar shell for injecting hydrogen peroxide into the combustion chamber; as the outlet of hydrogen peroxide, the diameter of the hydrogen peroxide outlet pipe is smaller than the diameter of the hydrogen peroxide swirl chamber, and the hydrogen peroxide swirl chamber and the hydrogen peroxide outlet pipe are connected by a frustum transition; the hydrogen peroxide outlet pipe is coaxially sleeved in the cavity of the kerosene swirl chamber.

[0013] The technical effects and advantages of this invention are as follows: 1. The rotating detonation rocket engine has the ability to start multiple times through the hydrogen peroxide kerosene propellant ignition device. Ignition and detonation can be achieved by controlling the valve, which significantly improves its potential for reusable engineering applications. The ignition process is achieved by using hydrogen peroxide to catalyze and ignite kerosene, eliminating the need for additional devices such as spark plugs, resulting in a simple structure. Furthermore, the device can achieve multiple ignitions by controlling the on / off state of the propellant valve, eliminating the need for multiple ignition devices and significantly improving the reliability of the system. A hydrogen peroxide catalytic device was used, employing a silver-palladium alloy mesh-based propellant. This device pre-catalyzed the decomposition of a room-temperature high-specific-heat-capacity liquid (approximately 2.6 kJ / kg·K) into a high-temperature gas (specific-heat-capacity approximately 1.0 kJ / kg·K). Experimental results showed that the gas temperature after catalytic decomposition of 98% concentration hydrogen peroxide using the silver-palladium alloy mesh-based propellant was approximately 1200 K. In contrast, the catalytic decomposition temperature using a traditional manganese-based particulate catalyst under the same catalyst bed conditions (hydrogen peroxide flow rate per unit catalyst area) was approximately 1000 K. Therefore, this method produces a higher gas temperature, which is beneficial for the subsequent ignition and detonation process. Kerosene was then introduced. Under the impact of the high-temperature, high-velocity gas (the overall mass flow rate remained unchanged, but the volumetric flow rate increased dramatically due to the change of hydrogen peroxide from liquid to gas, while its density decreased, and its velocity increased according to the law of conservation of mass), the kerosene rapidly vaporized and mixed, thus forming favorable gas-gas mixing conditions. In summary, the use of a catalytic device increases the temperature and reduces the specific heat capacity from a physicochemical perspective, while also giving it a faster velocity and better diffusion capacity from a flow perspective. This helps to quickly form good gas mixing conditions and facilitates rapid initiation of detonation. Stable and efficient ignition and detonation: The pre-detonation tube is equipped with a Shchelkin spiral tube. When the flame and gas flow through it, they need to bypass the spiral structure to move forward, which stretches and twists the flame front, greatly increases the combustion reaction area, enhances turbulence, accelerates the transition from slow combustion to detonation, and achieves efficient detonation of the detonation engine. It adopts an integrated thrust chamber design, manufactured using 3D printing technology, and equipped with a multi-start ignition device. It can achieve efficient and stable ignition and detonation using its own hydrogen peroxide kerosene propellant, and has a simple structure. The combustion chamber shell is equipped with a cooling channel, which can achieve long-term stable operation through the regeneration and cooling of kerosene. The temperature of the kerosene increases after flowing through the cooling channel, which is beneficial to the subsequent ignition process. The nozzle adopts a plug nozzle with high compensation capability, which can achieve efficient propulsion over a wide range. Attached Figure Description

[0014] Figure 1 This is an exploded view of the combustion chamber structure of a hydrogen peroxide kerosene rotating detonation rocket. Figure 2 A three-dimensional diagram of the multiple ignition device and combustion chamber structure of a hydrogen peroxide kerosene rotating detonation rocket combustion chamber; Figure 3 This is a schematic diagram of the pre-explosion tube structure; Figure 4 This is a schematic diagram of a coaxial dual-component centrifugal nozzle. Figure 5 This is a schematic diagram of the pre-explosion tube connection.

[0015] In the diagram: 1. Pre-explosion pipe; 2. Hydrogen peroxide inlet; 3. Hydrogen peroxide / kerosene bicomponent centrifugal nozzle; 4. Hydrogen peroxide chamber; 5. Kerosene chamber; 6. Combustion chamber; 7. Kerosene cooling channel; 8. Conical plug; 9. Kerosene inlet; 10. Kerosene collecting chamber; 11. Connecting flange; 1-1. Hydrogen peroxide inlet; 1-2. Liquid flow equalization plate; 1-3. Catalytic bed; 1-4. Decomposition gas rectifier grid; 1-5. Flame guide tube; 1-6. Shchelkin spiral tube; 1-7. Flange; 1-8. Kerosene inlet; 1-9. Kerosene flow equalization plate; 3-1. Hydrogen peroxide swirl chamber; 3-2. Hydrogen peroxide tangential hole; 3-3. Kerosene swirl chamber; 3-4. Kerosene tangential hole; 3-5. Hydrogen peroxide outlet pipe; 3-6. Annular kerosene injection hole. Detailed Implementation

[0016] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0017] This invention provides, for example Figures 1-5 The multi-ignition device shown is for the combustion chamber of a hydrogen peroxide kerosene rotating detonation rocket, such as Figure 1 As shown, it includes: a propellant delivery device connected to the propellant supply system for supplying kerosene and hydrogen peroxide into the combustion chamber 6; and a pre-explosion tube 1, tangentially installed on the side of the combustion chamber 6 and connected to the flange of the combustion chamber 6, with its injection end tangentially inserted into the combustion chamber for ignition, igniting the kerosene and hydrogen peroxide in the combustion chamber. After ignition, the kerosene and hydrogen peroxide injected into the combustion chamber 6 continue to burn, and the pre-explosion tube 1 stops working; when re-ignition is required, the pre-explosion tube 1 is restarted and shut off after ignition.

[0018] The structure of the aforementioned pre-explosion tube 1 is as follows: Figure 3 As shown, the system includes: a cylindrical cavity with a catalytic ignition hydrogen peroxide inlet nozzle 1-1 at its front end and a flame guide tube 1-5 coaxially connected to its rear end, the end of which is connected to a combustion chamber 6. Within the cylindrical cavity, a liquid flow equalization plate 1-2 and a decomposition gas rectifier grid 1-4 are spaced apart at their front and rear ends. Both the liquid flow equalization plate 1-2 and the decomposition gas rectifier grid 1-4 are circular plates with multiple through holes evenly distributed on them. These through holes are arranged radially and circumferentially at intervals, forming multiple concentric circles; and the through holes on the decomposition gas rectifier grid 1-4 are larger than those on the liquid flow equalization plate 1-2. A catalytic bed 1-3 is filled between the liquid flow equalization plate 1-2 and the decomposition gas rectifier grid 1-4. The catalytic bed 1-3 is generally composed of several silver-palladium alloy meshes, used to catalytically decompose a small amount of hydrogen peroxide into high-temperature oxygen and water vapor. A kerosene inlet nozzle is located on the side. Kerosene enters the pre-detonation tube through kerosene inlet 1-8. After passing through the kerosene flow equalization plate 1-9, it comes into full contact with the catalyzed high-temperature oxygen and water vapor in the flame guide tube 1-5 and combusts. The Shchelkin spiral tube 1-6 is located in the flame guide tube 1-5. In this design, the length-to-diameter ratio of the Shchelkin spiral tube is approximately 6:1, and the ratio of the spiral diameter to the inner diameter of the pre-detonation tube is approximately 1:10. It can accelerate the flame propagation by increasing the airflow turbulence and achieving the transition from slow combustion to detonation. The detonation wave is guided into the combustion chamber 6 through the flame guide tube 1-5, efficiently igniting the fuel entering the combustion chamber 6. The flow equalization plate 1-2 ensures that hydrogen peroxide flows evenly to the catalytic bed 1-3. After catalysis in the catalytic bed 1-3, the hydrogen peroxide decomposes into high-temperature oxygen and water vapor. At approximately 1200 K, the decomposed gas flows through the rectifier grid 1-4. The main function of the rectifier grid 1-4 is to regulate the flow direction of the high-temperature oxygen and water vapor from the catalytic decomposition in the catalytic bed, eliminating the influence of secondary flows and eddies. The specific connection structure between the pre-explosion tube and the combustion chamber is as follows... Figure 5 As shown.

[0019] The aforementioned propellant delivery device includes a propellant storage chamber and multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles 3. The propellant storage chamber consists of two interconnected and independent cylindrical chambers: a hydrogen peroxide chamber 4 and a kerosene chamber 5. A hydrogen peroxide inlet 2 is provided on the hydrogen peroxide chamber 4. The rear end of the kerosene chamber 5 is connected to the front end of the combustion chamber 6. Multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles 3 are connected to the propellant storage chamber and are used to inject hydrogen peroxide and kerosene into the combustion chamber 6.

[0020] like Figure 4 As shown, the aforementioned hydrogen peroxide / kerosene bicomponent centrifugal nozzle 3 includes: a kerosene swirl chamber 3-3, which is formed by a conical shell; the kerosene swirl chamber 3-3 is located in the kerosene chamber 5 section, and kerosene tangential holes 3-4 are spaced apart on the outer wall of the larger end of the shell of the kerosene swirl chamber 3-3, each of which is connected to the kerosene chamber 5; an annular kerosene injection hole 3-6 is circumferentially formed at the end of the smaller end of the shell of the kerosene swirl chamber 3-3. A hydrogen peroxide swirl chamber 3-1 is formed by a columnar shell, and hydrogen peroxide tangential holes 3-2 are spaced apart on the side wall of the front end of the shell. A columnar hydrogen peroxide outlet pipe 3-5 is connected to the rear end of the columnar shell for injecting hydrogen peroxide into the combustion chamber. As the outlet for hydrogen peroxide, the diameter of the hydrogen peroxide outlet pipe 3-5 is smaller than the diameter of the hydrogen peroxide swirl chamber 3-1, and the hydrogen peroxide swirl chamber 3-1 and the hydrogen peroxide outlet pipe 3-5 are connected by a frustum-shaped transition. The hydrogen peroxide outlet pipe 3-5 is coaxially fitted into the cavity of the kerosene swirl chamber 3-3. Both hydrogen peroxide and kerosene are centrifugally sprayed out from the centrifugal nozzle, allowing for pre-mixing and uniform combustion at the head of the combustion chamber.

[0021] A conical plug 8 is connected to the combustion chamber 6, forming a plug-type nozzle together with the combustion chamber shell. As the flight altitude increases, the combustion gas automatically expands outward, thus maintaining high nozzle efficiency. The combustion chamber 6 has a double-shell structure, with kerosene cooling channels 7 arranged between the shells. An annular kerosene collecting chamber 10 is arranged around the tail of the shell, connected to the inlet of the cooling channel 7. A kerosene inlet 9 is opened on the shell of the kerosene collecting chamber 10 for connection with external pipelines. The opening end of the kerosene cooling channel 7 in the combustion chamber 6 is connected to the kerosene chamber 5. The cooling channel 7 is designed with multiple columnar channels, resulting in high heat exchange efficiency and strong flow stability.

[0022] The length-to-diameter ratio of the Shchelkin helical tube is approximately 6:1, and the ratio of the helix diameter to the inner diameter of the pre-detonation tube is approximately 1:10. Under these conditions, the slow-burn to detonation process can be completed quickly and effectively. If the length-to-diameter ratio of the Shchelkin helical tube is too large, the pre-detonation tube will be too long, resulting in an insufficiently compact structure and energy loss. If the length-to-diameter ratio is too short, it will be insufficient to complete the slow-burn to detonation process. Therefore, this solution sets it to 6:1. In the preferred embodiment of this invention, the length-to-diameter ratio is set between 6:1 and 8:1. In addition, the ratio of the helix diameter to the inner diameter of the pre-detonation tube will also significantly affect the slow-burn to detonation process. If the helix diameter is too large, excessive propagation resistance will be generated, leading to the dissipation of gas energy and insufficient generation of a detonation wave. If the helix diameter is too small, the propagation resistance is very small, failing to promote mixing effectively, resulting in a slower slow-burn to detonation process. Therefore, this solution sets it to 1:10 of the inner diameter of the pre-detonation tube. At this time, the slow-burn to detonation process is very fast, approximately 1 ms. In addition, the pre-detonation tube is tangentially connected to the side of the combustion chamber, and the detonation wave enters the annular combustion chamber in a tangential direction, which reduces the shock wave reflection caused by frontal impact on the combustion chamber, while maintaining the rotational shape of the detonation wave, which is conducive to establishing the stable section of rotating detonation wave more quickly, shortening the start-up time, and reducing the start-up failure rate. Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber, comprising a combustion chamber and a propellant delivery device, characterized in that: The combustion chamber has a double-shell structure with a kerosene cooling channel between the shells and an annular kerosene collection chamber at the tail of the shell, which is connected to the inlet of the cooling channel. A kerosene inlet is provided on the shell of the kerosene collecting chamber for connecting to external pipelines; A conical plug is connected to the center of the combustion chamber, which together with the combustion chamber shell forms a plug-type nozzle; A pre-explosion pipe is connected to the side tangent of the combustion chamber via a flange. The injection end of the pre-explosion pipe is connected to the combustion chamber along the tangent direction of the side wall of the combustion chamber for ignition and starting, igniting the kerosene and hydrogen peroxide in the combustion chamber. The propellant delivery device includes a propellant storage chamber and multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles; the propellant storage chamber consists of two interconnected and independent cylindrical hydrogen peroxide chambers and kerosene chambers; a hydrogen peroxide inlet is provided on the hydrogen peroxide chamber; the rear end of the kerosene chamber is connected to the opening end of the kerosene cooling channel in the combustion chamber.

2. The multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber according to claim 1, characterized in that: The pre-explosion tube includes a cylindrical cavity with a catalytic ignition hydrogen peroxide inlet nozzle at the front end and a flame guide tube coaxially connected to the rear end. A kerosene inlet nozzle is located on the side, and the end of the flame guide tube is connected to the combustion chamber. A liquid flow equalization plate and a decomposition gas rectifier grid are arranged at intervals in front and behind the cylindrical cavity. The space between the liquid flow equalization plate and the decomposition gas rectifier grid is used to fill the catalytic bed, which consists of several silver meshes.

3. The multiple ignition device for the combustion chamber of a hydrogen peroxide kerosene rotating detonation rocket according to claim 2, characterized in that: Both the liquid flow equalization plate and the decomposition gas rectifier are circular plates with multiple through holes evenly distributed on them. The through holes are evenly spaced in the radial and circumferential directions to form multiple concentric circle structures; and the through holes on the decomposition gas rectifier are larger than the through holes on the liquid flow equalization plate.

4. The multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber according to claim 1, characterized in that: The flame guide tube is equipped with a Shchelkin spiral tube; the length-to-diameter ratio of the Shchelkin spiral tube is approximately 6:1, and the ratio of the spiral diameter to the inner diameter of the pre-explosion tube is approximately 1:

10.

5. The multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber according to claim 1, characterized in that: Multiple hydrogen peroxide / kerosene bicomponent centrifugal nozzles are connected to the propellant storage chamber and are used to inject hydrogen peroxide and kerosene into the combustion chamber.

6. The multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber according to claim 1, characterized in that: The hydrogen peroxide / kerosene bicomponent centrifugal nozzle includes: a kerosene swirl chamber, which is formed by a conical shell; the kerosene swirl chamber is located in the kerosene cavity section, and kerosene tangential holes are spaced apart on the outer wall of the larger end of the shell of the kerosene swirl chamber, each kerosene tangential hole being connected to the kerosene cavity; an annular kerosene injection hole is opened circumferentially around the end of the smaller end of the shell of the kerosene swirl chamber; a hydrogen peroxide swirl chamber, which is formed by a cylindrical shell, and hydrogen peroxide tangential holes are spaced apart on the side wall of the front end of the shell, and a cylindrical hydrogen peroxide outlet pipe is connected to the rear end of the cylindrical shell for injecting hydrogen peroxide into the combustion chamber; as the outlet of hydrogen peroxide, the diameter of the hydrogen peroxide outlet pipe is smaller than the diameter of the hydrogen peroxide swirl chamber, and the hydrogen peroxide swirl chamber and the hydrogen peroxide outlet pipe are connected by a frustum transition; the hydrogen peroxide outlet pipe is coaxially sleeved in the cavity of the kerosene swirl chamber.

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