Coaxial integrated rotor full flow direct combustion drive liquid rocket engine

Abstract

The present invention discloses a coaxial integrated rotor full-flow direct combustion driven liquid rocket engine, comprising: an outer shell, and a multi-power wheel installed in the outer shell. The present invention adopts a coaxial integrated multi-power wheel design, and arranges multiple key components coaxially, which greatly reduces the number of components and volume of the engine. Compared with traditional independent turbopumps and staged combustion rocket engines, the present invention does not require complex pipe connections and large turbopump components, effectively saving internal space in the rocket and reducing the cost of the rocket. In addition, the main combustion chamber of the present invention is connected to the third flow channel at almost 360 degrees, which effectively limits the premature discharge of gas from the main combustion chamber. The first propellant and the second propellant have sufficient time to mix with each other in the relatively closed main combustion chamber space, making the two mixed more evenly and improving the energy conversion efficiency.

Description

Technical Field

[0001] The invention relates to a coaxial integrated rotor full-flow direct-combustion driven liquid rocket engine. Background Art

[0002] The pump-type engines currently used in launch vehicles and spacecraft are usually composed of independent turbopumps, gas generators and thrust chambers. Their systems are complex and costly.

[0003] For example, the invention patent with publication number CN114060170A relates to an open staged combustion, pumped air cycle, coaxial integrated rotor, full-flow direct-fired liquid rocket engine, consisting of a set of turbopumps, a staged combustion thrust chamber, and corresponding control valves. The staged combustion thrust chamber adopts a two-stage combustion mode with an upper chamber and a lower chamber. Part of the oxidizer and the entire fuel are combined in a rich combustion in the upper chamber of the thrust chamber, forming a relatively low-temperature rich combustion zone. The resulting rich combustion gas is then introduced into the lower chamber of the thrust chamber for post-combustion combustion with the majority of the oxidizer introduced from the oxygen pump.

[0004] The above-mentioned invention patent still retains an independent turbopump and gas generator (the thrust chamber adopts an upper cavity), so the open-cycle coaxial integrated rotor full-flow direct-fired liquid rocket engine not only has turbine exhaust losses and relatively low performance, but also the system is still complex and the manufacturing cost is high.

[0005] This invention proposes a coaxial integrated rotor, full-flow, direct-fired liquid rocket engine that eliminates a separate turbopump and completely dispenses with a gas generator. By integrating the first and second impellers and turbine within the main combustion chamber, the engine achieves full functionality. This novel coaxial integrated rotor, full-flow, direct-fired liquid rocket engine features a simple and reliable system, strong adaptability, and ultra-low manufacturing costs, making it suitable for mass production of rocket engines. Summary of the Invention

[0006] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0007] A coaxial integrated rotor full-flow direct-combustion driven liquid rocket engine comprises: an outer shell, and a multi-element power wheel installed in the outer shell;

[0008] The multi-power wheel is composed of a rotor assembly, a combustion chamber outer wall, a combustion chamber inner wall, an intermediate shaft and a central shaft which are coaxially arranged in sequence; an annular bearing frame is fixedly installed in the middle section of the inner part of the outer shell, and the central shaft is rotatably connected to the center of the bearing frame through a bearing; a first flow channel is formed between the intermediate shaft and the central shaft, and the intermediate shaft is fixedly connected to the central shaft through a plurality of first impellers; a second flow channel is formed between the combustion chamber inner wall and the intermediate shaft, and the combustion chamber inner wall is fixedly connected to the intermediate shaft through a plurality of second impellers; the combustion chamber outer wall is a hollow structure, and its interior is communicated with the second flow channel; the rotor assembly is fixedly connected to the combustion chamber outer wall through a plurality of vortex vanes, and the outer side of the rotor assembly is rotatably connected to the side wall of the outer shell;

[0009] Preferably, the bearing frame is fixedly connected to the outer shell through a plurality of guide vanes;

[0010] Preferably, a main combustion chamber is formed between the inner wall of the combustion chamber and the top of the outer shell;

[0011] Preferably, the top of the inner wall of the combustion chamber and the outer shell are sealed by a sealing ring;

[0012] Preferably, a third flow channel is formed between the outer wall of the combustion chamber and the outer shell, and the vortex sheet and the guide vane are located below the third flow channel;

[0013] Preferably, a first injection nozzle is provided on the circumference of the intermediate shaft, and the first injection nozzle is connected with the first flow channel and the main combustion chamber;

[0014] Preferably, a second injection nozzle is provided on the inner wall of the combustion chamber along the circumference, and the second injection nozzle is connected to the second flow channel and the main combustion chamber;

[0015] Preferably, the tilted setting direction of the vortex vanes is opposite to the tilted setting direction of the guide vanes.

[0016] The advantages of the present invention are: the present invention adopts a coaxially integrated multi-power wheel design, and multiple key components are coaxially arranged, which greatly reduces the number and volume of engine components. Compared with traditional independent turbopumps and staged combustion rocket engines, the present invention does not require complex pipeline connections and large turbopump components, effectively saving the internal space of the rocket and reducing the cost of the rocket; in addition, the main combustion chamber of the present invention and the third flow channel are connected at almost 360 degrees, which effectively limits the premature discharge of fuel gas from the main combustion chamber. The first propellant and the second propellant have sufficient time to mix with each other in the relatively closed main combustion chamber space, making the two mixed more evenly and improving the energy conversion efficiency.

[0017] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 It is a structural schematic diagram of the present invention.

[0020] Figure 2 yes Figure 1 Enlarged view of the area circled in center A.

[0021] Figure 3 It is a schematic diagram of the working principle of the present invention. DETAILED DESCRIPTION

[0022] The following is a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of the present invention.

[0023] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the present invention.

[0024] Furthermore, in the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; internal communication between two components; and wireless or wired connections. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0025] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0026] See also Figures 1 and 2In an embodiment of the present invention, a coaxial integrated rotor full-flow direct combustion drive liquid rocket engine includes: an outer shell 1, and a multi-element power wheel 2 installed in the outer shell 1;

[0027] In an embodiment of the present invention, the present invention adopts a coaxially integrated multi-power wheel 2 design, and the rotor assembly 28, the outer wall 26 of the combustion chamber, the inner wall 25 of the combustion chamber, the intermediate shaft 23 and the central shaft 21 and other components are coaxially arranged in sequence, and the first impeller 22 is installed between the intermediate shaft 23 and the central shaft 21, the second impeller 24 is installed between the outer wall 25 of the combustion chamber and the intermediate shaft 23, and the vortex vanes 27 are installed between the rotor assembly 28 and the outer wall 26 of the combustion chamber. The rotor assembly 28 is fixedly connected to the combustion chamber by multiple vortex vanes 27, and the outer side of the rotor assembly 28 is rotatably connected to the side wall of the outer shell 1.

[0028] The first propellant of the present invention is extracted and transported by the first impeller 22, which is mounted between the intermediate shaft 23 and the central shaft 21. The second propellant is extracted and transported by the second impeller 24, which is located between the combustion chamber inner wall 25 and the intermediate shaft 23. The two propellants enter the main combustion chamber 400 through the first and second injection nozzles 110 and 210, where they are thoroughly mixed and ignited to produce driving gas. The gas expands rapidly within the main combustion chamber 400, converting some of its energy into heat. This creates a significant pressure differential, driving the gas to flow at high speed into the third flow channel 300.

[0029] The high-speed flowing combustion gas impacts the vortex vanes 27 and guide vanes 12 installed between the rotor assembly 28 and the outer wall 26 of the combustion chamber, thereby generating a reaction force, pushing the vortex vanes 27 to drive the rotor assembly 28 to rotate, and drive the entire multi-power wheel 2 to work.

[0030] This invention utilizes a coaxially integrated multi-element power wheel design, coaxially arranging multiple key components, significantly reducing the number of engine components and size. Compared to traditional independent turbopumps and staged combustion rocket engines, this invention eliminates the need for complex piping and bulky turbopump assemblies, effectively saving space within the rocket and reducing costs.

[0031] In an embodiment of the present invention, the bearing frame 11 is fixedly connected to the outer shell 1 through a plurality of guide vanes 12, so that the annular bearing frame 11 is fixed in the middle position inside the outer shell 1, and the central shaft 21 is rotatably connected to the center of the bearing frame 11 through the bearing 13, and the rotor assembly 28 is rotatably connected to the outer shell 1, so that the entire multi-power wheel 2 maintains rotational stability when rotating at high speed, making the entire engine run more smoothly and reliably.

[0032] like Figure 3As shown, in this embodiment of the present invention, a first flow channel 100 is formed between the intermediate shaft 23 and the central shaft 21, a second flow channel 200 is formed between the combustion chamber inner wall 25 and the intermediate shaft 23, the combustion chamber outer wall 26 is a hollow structure, its interior communicating with the second flow channel 200, a main combustion chamber 400 is formed between the combustion chamber outer wall 26, the combustion chamber inner wall 25, and the top of the outer shell 1, and a third flow channel 300 is formed between the combustion chamber outer wall 26 and the outer shell 1. A first injection nozzle 110 is provided on the circumference of the intermediate shaft 23, connecting the first flow channel 100 and the main combustion chamber 400. A second injection nozzle 210 is provided on the circumference of the combustion chamber inner wall 25, connecting the second flow channel 200 and the main combustion chamber 400.

[0033] The operating principle of the above-described structure is as follows: when the rocket engine is in operation, the centrifugal force of the rapidly rotating first impeller 22 causes the first propellant to flow along the first flow channel 100 between the central axis 21 and the intermediate axis 23. The first propellant is ejected from the first injection nozzles 110 along the circumference of the intermediate axis 23 and directed into the main combustion chamber 400. Simultaneously, the rapidly rotating second impeller 24 forces the second propellant into the second flow channel 200 between the combustion chamber inner wall 25 and the intermediate axis 23. The second impeller 24 pressurizes the second propellant, causing it to be ejected from the second injection nozzles 210 around the combustion chamber inner wall 25 into the main combustion chamber 400. The two propellants intersect and mix thoroughly within the main combustion chamber 400. After being ignited by the ignition device, they combust, releasing a large amount of heat and producing high-temperature, high-pressure combustion gases. Driven by the high temperature and pressure, the combustion gases within the main combustion chamber 400 rapidly expand, and the significant pressure differential causes the gases to flow into the third flow channel 300 between the combustion chamber outer wall 26 and the outer casing 1.

[0034] In this embodiment of the present invention, the combustion chamber outer wall 26 is hollow and communicates with the second flow channel 200. During delivery, the second propellant absorbs heat from the combustion chamber outer wall 26, preventing the outer wall from being overheated, which could lead to degradation of material properties and structural damage, thereby ensuring stable operation of the combustion chamber even at high temperatures.

[0035] In an embodiment of the present invention, a main combustion chamber 400 is formed between the outer wall 26 of the combustion chamber, the inner wall 25 of the combustion chamber and the top of the outer shell 1, and the third flow channel 300 between the outer wall 26 of the combustion chamber and the outer shell 1. It is worth noting that the main combustion chamber 400 and the third flow channel 300 are almost connected at 360 degrees, which effectively limits the premature discharge of the gas from the main combustion chamber 400. The first propellant and the second propellant have sufficient time to mix with each other in the relatively closed space of the main combustion chamber 400, making the mixing of the two more uniform and improving the energy conversion efficiency.

[0036] In this embodiment of the present invention, a third flow channel 300 is formed between the outer wall 26 of the combustion chamber and the outer casing 1. The vortex vanes 27 and guide vanes 12 are located below the third flow channel 300. After the combustion gas flows into the third flow channel 300, it impacts the vortex vanes 27, which are tilted and mounted between the rotor assembly 28 and the outer wall 26 of the combustion chamber. Due to the tilt angle of the vortex vanes 27, the impact of the combustion gas generates a reaction force, which pushes the vortex vanes 27 and drives the rotor assembly 28 to rotate at high speed.

[0037] In this embodiment of the present invention, the high-temperature, high-pressure gas generated by the combustion of the propellant in the main combustion chamber 400 enters the area where the vortex vanes 27 and guide vanes 12 are located. Because the vortex vanes 27 are tilted, and the guide vanes 12 are tilted in the opposite direction to the vortex vanes 27, when the high-temperature, high-pressure gas flows out from between adjacent vortex vanes 27, the gas flow direction forms an angle with the surface of the guide vanes 12. According to Newton's third law, the gas generates a reaction force on the guide vanes 12. The tangential component of this reaction force propels the vortex vanes 27 to rotate about the central axis 21. The vortex vanes 27 are connected to the rotor assembly 28, which in turn drives the entire multi-element power wheel 2 to rotate, converting the internal energy of the gas into mechanical energy.

[0038] In another embodiment, the top of the combustion chamber inner wall 25 and the outer shell 1 are sealed by a sealing ring 14, which effectively prevents the high-temperature and high-pressure gas in the main combustion chamber 400 from reversely impacting the fuel inlet.

[0039] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations that come within the meaning and range of equivalents of the claims be embraced therein.

Claims

1. A coaxial integrated rotor full-flow direct-ignition drive liquid rocket engine, comprising: An outer shell, and a multi-power wheel installed in the outer shell; characterized in that: The multi-power wheel is composed of a rotor assembly, a combustion chamber outer wall, a combustion chamber inner wall, an intermediate shaft and a central shaft which are coaxially arranged in sequence; an annular bearing frame is fixedly installed in the middle section of the inner part of the outer shell, and the central shaft is rotatably connected to the center of the bearing frame through a bearing; a first flow channel is formed between the intermediate shaft and the central shaft, and the intermediate shaft is fixedly connected to the central shaft through a plurality of first impellers; a second flow channel is formed between the combustion chamber inner wall and the intermediate shaft, and the combustion chamber inner wall is fixedly connected to the intermediate shaft through a plurality of second impellers; the combustion chamber outer wall is a hollow structure, and its interior is communicated with the second flow channel; the rotor assembly is fixedly connected to the combustion chamber outer wall through a plurality of vortex vanes, and the outer side of the rotor assembly is rotatably connected to the side wall of the outer shell; A first injection nozzle is provided on the circumference of the intermediate shaft, and the first injection nozzle is connected to the first flow channel and the main combustion chamber; A second injection nozzle is provided on the inner wall of the combustion chamber along the circumference, and the second injection nozzle is connected with the second flow channel and the main combustion chamber.

2. The coaxial integrated rotor full flow direct combustion driven liquid rocket engine according to claim 1, characterized in that: The bearing frame is fixedly connected to the outer shell through a plurality of guide vanes.

3. The coaxial integrated rotor full flow direct combustion driven liquid rocket engine according to claim 1, characterized in that: A main combustion chamber is formed between the inner wall of the combustion chamber and the top of the outer shell.

4. The coaxial integrated rotor full flow direct combustion driven liquid rocket engine according to claim 1, characterized in that: The top of the inner wall of the combustion chamber and the outer shell are sealed and connected via a sealing ring.

5. The coaxial integrated rotor full flow direct combustion driven liquid rocket engine according to claim 2, characterized in that: A third flow channel is formed between the outer wall of the combustion chamber and the outer shell, and the vortex sheet and the guide vane are located below the third flow channel.

6. The coaxial integrated rotor full flow direct combustion driven liquid rocket engine according to claim 2, characterized in that: The tilted setting direction of the vortex sheet is opposite to the tilted setting direction of the guide vane.

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