A device for matching the pressurization flow rate and temperature during the thrust variation process of a rocket engine

Abstract

The present invention relates to a device for matching the pressurization flow rate and temperature during the variable thrust process of a rocket engine, which includes a mixer and a pressurized gas delivery system. One end of the mixer is provided with a pressurized liquid inlet conduit communicating with its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit communicating with its inner cavity. The surface of the mixer is provided with a pressurized gas inlet communicating with its inner cavity. The pressurized gas delivery system is communicated with the pressurized gas inlet. A flow disturbance structure is provided at a position in the mixer near the pressurized liquid inlet conduit, and a flow guiding structure is provided at a position in the mixer corresponding to the pressurized gas inlet. The flow guiding structure is used to guide the gas entering through the pressurized gas inlet towards the direction where the flow disturbance structure is located. Advantages: The structural design is simple and reasonable, which can help the engine match the current self-pressurization flow rate and temperature during the variable thrust process, so as to meet the pressurization requirements of the propellant tank of the launch vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engines, and particularly to a device for matching the pressurization flow rate and temperature during the variable thrust process of a rocket engine. Background Art

[0002] As the mainstream carrier device for humans to enter space, launch vehicles have significant characteristics such as short working time, large energy consumption, and high energy consumption power. Chemical fuel launch vehicles include solid launch vehicles, liquid launch vehicles, and solid-liquid hybrid launch vehicles. Among them, liquid launch vehicles refer to those in which the phase state of the propellant medium used is liquid. Common liquid propellants include nitrogen tetroxide, unsymmetrical dimethylhydrazine, hydrogen peroxide, liquid oxygen, kerosene, liquid methane, liquid hydrogen, etc. During the working process of a liquid launch vehicle, the liquid propellant medium is continuously consumed, and the liquid level in the propellant tank of the launch vehicle continuously drops. As the liquid volume in the tank decreases, the tank pressure will continuously drop. However, a rocket engine requires a certain inlet pressure to ensure the normal operation of the engine. Therefore, the pressurization system of the propellant tank of a launch vehicle needs to be specifically designed. Common pressurization methods include inert gas makeup pressure and self-pressurization of the rocket engine.

[0003] Self-pressurization of a rocket engine means that during the working process of the rocket engine, the liquid propellant is heated and raised to the gaseous state in the engine, and then returned to the propellant tank, using its own propellant medium to generate a pressurizing medium for the propellant tank, hence the name self-pressurization. For traditional liquid rocket engines operating in a fixed thrust mode, through means such as calibration tests, the pressurization flow rate and temperature at the rated operating point of the engine can be well matched. Through design and type approval, it can basically ensure that the flow rate and temperature at the design point meet the usage requirements, and no additional device settings are required.

[0004] Currently, with the development of launch vehicle technology, reusable launch vehicles have put forward new requirements for liquid rocket engines, such as multiple starts, thrust adjustment, online fault identification, etc. Since a liquid rocket engine is a typical non-linear system, during the process of thrust adjustment, the pressurization flow rate and temperature of the propellant inevitably deviate from the pressurization requirements of the current thrust condition. The traditional solution is to ensure through design that during the thrust adjustment condition, its pressurization ability is still not lower than the pressurization requirements of the current thrust. This has caused the tank pressure of the propellant tank during flight to be too high, resulting in many problems such as a large dead weight and poor performance of the launch vehicle. In severe cases, it may even cause waste of propellant and damage the performance of the launch vehicle.

[0005] Based on this, it is necessary to develop a device for matching the pressurization flow rate and temperature during the variable thrust process of a rocket engine to overcome the above technical problems. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a device for matching the pressurized flow rate and temperature during the variable thrust process of a rocket engine, which effectively overcomes the defects of the prior art.

[0007] The technical solution of the present invention to solve the above technical problems is as follows:

[0008] A device for matching the pressurized flow rate and temperature during the variable thrust process of a rocket engine includes a mixer and a pressurized gas delivery system. One end of the mixer is provided with a pressurized liquid inlet conduit communicating with its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit communicating with its inner cavity. The surface of the mixer is provided with a pressurized gas inlet communicating with its inner cavity. The pressurized gas delivery system is communicated with the pressurized gas inlet. A flow disturbing structure is provided at a position in the mixer close to the pressurized liquid inlet conduit, and a flow guiding structure is provided at a position in the mixer corresponding to the pressurized gas inlet. The flow guiding structure is used to guide the gas entering through the pressurized gas inlet towards the position where the flow disturbing structure is located.

[0009] On the basis of the above technical solution, the present invention can be further improved as follows.

[0010] Further, the mixer is a cylindrical container.

[0011] Further, the surface of the mixer is provided with an annular pressurized gas collecting chamber. The pressurized gas inlet is arranged inside the pressurized gas collecting chamber and is communicated with each other. The pressurized gas delivery system is connected to the inner cavity of the pressurized gas collecting chamber.

[0012] Further, the flow guiding structure is a conical guiding cylinder. The conical end of the flow guiding structure faces the position where the flow disturbing structure is located. The conical bottom of the flow guiding structure is connected to the inner wall of the mixer. There are multiple pressurized gas inlets, which are distributed at intervals along the circumferential direction of the mixer.

[0013] Further, the flow guiding structure includes multiple flow guiding plates. There are multiple pressurized gas inlets, which are distributed at intervals along the circumferential direction of the mixer. The multiple flow guiding plates are connected to the inner wall of the mixer at equal intervals along the circumferential direction and are respectively distributed inside each pressurized gas inlet. Each flow guiding plate extends obliquely towards the position where the flow disturbing structure is located and the middle of the inner cavity of the mixer.

[0014] Further, the flow disturbing structure includes a partition plate arranged on the inner wall of the mixer, and the partition plate has a flow through hole in the middle.

[0015] Further, the partition plate is annular.

[0016] Further, the partition plate includes multiple fan-shaped annular plate surfaces, and the multiple fan-shaped annular plate surfaces are distributed on the inner wall of the mixer at equal intervals along the circumferential direction.

[0017] Further, the above-mentioned pressurized gas delivery system includes a delivery conduit, one end of which is in communication with the above-mentioned pressurized gas inlet, and the other end is connected to a gas source.

[0018] Further, a pressurized flow regulator is provided on the above-mentioned delivery conduit.

[0019] The beneficial effects of the present invention are as follows: The structure design is simple and reasonable, which can help the engine match the current self-pressurizing flow rate and temperature during the variable thrust process, so as to meet the pressurization requirements of the propellant tank of the launch vehicle. Description of the Drawings

[0020] Figure 1 It is a schematic structural diagram of the device for matching the pressurized flow rate and temperature during the variable thrust process of the rocket engine of the present invention.

[0021] In the drawings, the list of components represented by each reference numeral is as follows:

[0022] 1, mixer; 2, delivery conduit; 11, pressurized liquid inlet conduit; 12, pressurized mixed gas outlet conduit; 13, turbulence structure; 14, flow guiding structure; 15, pressurized gas collection chamber; 21, pressurized flow regulator. Detailed Embodiments

[0023] The principles and features of the present invention will be described below with reference to the drawings. The examples given are only used to explain the present invention and are not intended to limit the scope of the present invention.

[0024] Embodiment: As Figure 1 shown, the device for matching the pressurized flow rate and temperature during the variable thrust process of the rocket engine in this embodiment includes a mixer 1 and a pressurized gas delivery system. One end of the above-mentioned mixer 1 is provided with a pressurized liquid inlet conduit 11 communicating with its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit 12 communicating with its inner cavity. The surface of the above-mentioned mixer 1 is provided with a pressurized gas inlet communicating with its inner cavity. The above-mentioned pressurized gas delivery system is in communication with the above-mentioned pressurized gas inlet. A turbulence structure 13 is provided at a position in the above-mentioned mixer 1 close to the above-mentioned pressurized liquid inlet conduit 11, and a flow guiding structure 14 is provided at a position in the above-mentioned mixer 1 corresponding to the above-mentioned pressurized gas inlet. The above-mentioned flow guiding structure 14 is used to guide the gas entering through the pressurized gas inlet towards the position where the above-mentioned turbulence structure 13 is located.

[0025] In the boost flow and temperature matching device for the variable thrust process of a rocket engine of this embodiment, the flow of the boost liquid in the boost liquid inlet conduit 11 is generally drawn from the engine outlet, and the flow of the boost gas in the boost gas delivery system is generally drawn from the propellant after regenerative cooling, heat exchange and temperature increase in the engine thrust chamber (such as the thrust chamber cooling outlet collector). Inside the mixer 1, the boost liquid flows normally from upstream to downstream (that is, it flows from one end to the other end of the mixer 1). After being disturbed by the flow-turbulating structure 13, a local vortex is formed in the area between the flow-turbulating structure 13 and the flow-guiding structure 14. At the same time, the boost gas is injected from the boost gas inlet. Under the action of the flow-guiding structure 14, the flow direction of the gas after injection forms an obtuse angle with the normal flow direction of the boost liquid, which is similar to the boost gas injected in the reverse direction, and forms a mutual impact with the boost liquid, thereby enhancing the gas-liquid mixing effect. This configuration of the supercharged blender 1 significantly improves the mixing efficiency of the pressurized liquid and gas. While maintaining a constant mixing flow rate, it can significantly reduce the blender's size, facilitating a compact structural layout. This configuration ensures excellent blending efficiency over a wide range of varying pressurized liquid and gas flow rates during engine thrust variation, achieving essentially uniform mixing at the blender outlet. This structural design enhances gas-liquid mixing, shortens the mixing zone, and significantly improves structural compactness.

[0026] In this embodiment, the blender 1 is a cylindrical container with a simple shape and a clear internal flow channel.

[0027] As a preferred embodiment, the surface of the mixer 1 is provided with an annular pressurized gas collecting chamber 15, the pressurized gas inlet is arranged inside the pressurized gas collecting chamber 15 and is interconnected, and the pressurized gas delivery system is connected to the inner cavity of the pressurized gas collecting chamber 15.

[0028] In the above embodiment, the design of the pressurized gas collecting chamber 15 enables the incoming pressurized gas to be evenly dispersed in the pressurized gas collecting chamber 15 and sprayed into the inner cavity of the blender 1 through the pressurized gas inlet.

[0029] In this embodiment, the flow guiding structure 15 includes at least the following two structural forms:

[0030] 1) The above-mentioned guide structure 14 is a conical guide cylinder, the conical end of the guide structure 14 is facing the direction of the above-mentioned flow-disturbing structure 13, and the conical bottom of the guide structure 14 is connected to the inner wall of the above-mentioned blender 1. The above-mentioned pressurized gas inlet is provided with multiple and distributed at intervals along the circumference of the above-mentioned blender 2.

[0031] In the above solution 1), the flow guiding structure 14 is an integral conical cylinder member, which is hermetically installed on the inner wall of the mixer 1, and the angle between its conical surface and the center line forms an obtuse angle. Cooperating with a plurality of pressurized gas inlets evenly distributed at circumferential intervals on the inner wall of the mixer 1, it can enable the pressurized gas to be evenly sprayed into all directions of the inner wall of the mixer 1, which is beneficial to subsequent uniform mixing.

[0032] 2) The above flow guiding structure 14 includes a plurality of flow guiding plates. The above pressurized gas inlets are provided with a plurality of them and are distributed at intervals along the circumference of the mixer 2. The plurality of the above flow guiding plates are connected to the inner wall of the mixer 1 at equal circumferential intervals and are respectively distributed inside each of the above pressurized gas inlets. Each of the above flow guiding plates extends obliquely towards the position where the turbulence structure 13 is located and the middle part of the inner cavity of the mixer 2.

[0033] In the above solution 2), the flow guiding structure 14 adopts a plurality of separately designed flow guiding plates, which can be distributed corresponding to each pressurized gas inlet. An obtuse angle is formed between the flow guiding plate and the center line of the mixer 1, ensuring that the pressurized gas sprayed into each pressurized gas inlet can be guided to the turbulent vortex formed after the pressurized liquid is turbulently disturbed, realizing effective mixing.

[0034] In this embodiment, the turbulence structure 13 includes at least the following two structural forms:

[0035] ① The above turbulence structure 13 includes a partition plate arranged on the inner wall of the mixer 1, and there is a flow through hole in the middle of the partition plate.

[0036] More specifically, the above partition plate is annular.

[0037] ② The above partition plate includes a plurality of fan-shaped annular plate surfaces, and the plurality of fan-shaped annular plate surfaces are distributed on the inner wall of the mixer 1 at equal circumferential intervals.

[0038] After the pressurized liquid passes through the turbulence structure 13, a turbulent vortex can be generated in the area between the turbulence structure 3 and the flow guiding structure 14.

[0039] In this embodiment, the above pressurized gas delivery system includes a delivery conduit 2. One end of the delivery conduit 2 is communicated with the above pressurized gas inlet, and the other end is connected to a gas source.

[0040] In this embodiment, a pressure-boosting flow regulator 21 is provided on the above-mentioned delivery catheter 2, which can avoid the problem that the pressure-boosting liquid may be a cryogenic propellant (such as liquid oxygen, liquid methane, etc.). The pressure-boosting flow regulator 21 can adopt a conventional flow valve on the pipeline, aiming to accurately control the total pressure-boosting flow rate, the flow rates of the pressure-boosting liquid and gas. Among them, at the engine extraction port of the pressure-boosting liquid flow rate, a throttling element needs to be set to limit the flow rate, and with the variable thrust process of the engine, the pressure-boosting liquid flow rate changes following the changes of the pressure and temperature at the inlet of the throttling element. The flow rate of the pressure-boosting gas also needs to be limited, and the flow rate control can also be directly completed through the pressure-boosting flow regulator 21. During the variable thrust process of the rocket engine, the pressure-boosting flow regulator 21 adjusts the flow rate of the pressure-boosting gas to ensure that the temperature of the pressure-boosting mixed gas does not change significantly during the variable thrust process of the rocket engine. The mixed pressure-boosting gas finally flows into the rocket storage tank through the pressure-boosting mixed gas outlet catheter 12 to boost the liquid propellant in the rocket storage tank. In addition, during the variable thrust process of the rocket engine, due to the mismatch of the pressure and temperature at the extraction positions of the pressure-boosting liquid and gas during the variable thrust process of the engine, the flow rate ratio of the pressure-boosting liquid and gas will change, and at the same time, the temperature of the pressure-boosting gas may also change. Among different variable thrust characteristic points of the engine, the pressure-boosting flow regulator 21 works at different opening positions to adjust the flow rate of the pressure-boosting gas to ensure that the final flow rate of the pressure-boosting mixed gas changes according to the variable thrust ratio and the temperature remains basically unchanged.

[0041] It should be supplemented and explained that: in this embodiment, the requirements for the pressure-boosting flow regulator 21 are significantly reduced. During use, there is no working condition where the pressure-boosting flow regulator 21 is completely closed, and there is no requirement for controlling the leakage rate of internal leakage at the inlet and outlet of the pressure-boosting flow regulator.

[0042] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0043] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0044] In the present invention, unless otherwise clearly defined and limited, the terms such as "mounted", "connected", "coupled", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0045] In the present invention, unless otherwise clearly defined and limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0046] In the description of this specification, the descriptions with reference to terms such as "an embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0047] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A device for matching the pressurization flow rate and temperature during the thrust variation process of a rocket engine, characterized in that: It includes a blender (1) and a pressurized gas delivery system. One end of the blender (1) is provided with a pressurized liquid inlet conduit (11) communicating with its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit (12) communicating with its inner cavity. The surface of the blender (1) is provided with a pressurized gas inlet communicating with its inner cavity. The pressurized gas delivery system is communicated with the pressurized gas inlet. A flow disturbance structure (13) is provided at a position in the blender (1) close to the pressurized liquid inlet conduit (11), and a flow guiding structure (14) is provided at a position in the blender (1) corresponding to the pressurized gas inlet. The flow guiding structure (14) is used to guide the gas entering through the pressurized gas inlet towards the position where the flow disturbance structure (13) is located.

2. The pressure-increasing flow rate and temperature matching device for the variable thrust process of a rocket engine according to claim 1, wherein: The blender (1) is a cylindrical container.

3. A pressurization flow rate and temperature matching device for a variable thrust process of a rocket engine according to claim 2, characterized in that: An annular pressurized gas collecting cavity (15) is provided on the surface of the blender (1). The pressurized gas inlet is arranged inside the pressurized gas collecting cavity (15) and is communicated with each other. The pressurized gas delivery system is connected to the inner cavity of the pressurized gas collecting cavity (15).

4. A pressure increase flow rate and temperature matching device for a variable thrust process of a rocket engine according to claim 2, characterized in that: The flow guiding structure (14) is a conical guiding cylinder. The conical end of the flow guiding structure (14) faces the position where the flow disturbance structure (13) is located. The conical bottom of the flow guiding structure (14) is connected to the inner wall of the blender (1). There are multiple pressurized gas inlets, which are distributed at intervals along the circumference of the blender (1).

5. A boosting flow rate and temperature matching device for a rocket engine during variable thrust process according to claim 2, characterized in that: The flow guiding structure (14) includes multiple flow guiding plates. There are multiple pressurized gas inlets, which are distributed at intervals along the circumference of the blender (1). The multiple flow guiding plates are connected to the inner wall of the blender (1) at equal intervals in the circumferential direction and are respectively distributed inside each pressurized gas inlet. Each flow guiding plate extends obliquely towards the position where the flow disturbance structure (13) is located and the middle of the inner cavity of the blender (1).

6. The boost flow rate and temperature matching device during the variable thrust process of a rocket engine according to claim 2, wherein: The flow disturbance structure (13) includes a partition plate arranged on the inner wall of the blender (1). There is a flow through hole in the middle of the partition plate.

7. A device for matching the pressurization flow rate and temperature during the thrust variation process of a rocket engine according to claim 6, characterized in that: The partition plate is annular.

8. A boosting flow rate and temperature matching device for a variable thrust process of a rocket engine according to claim 6, characterized in that: The partition plate includes multiple fan-shaped annular plate surfaces, and the multiple fan-shaped annular plate surfaces are distributed on the inner wall of the blender (1) at equal intervals in the circumferential direction.

9. A device for matching the pressurization flow rate and temperature during the variable thrust process of a rocket engine according to any one of claims 1 to 8, characterized in that: The pressurized gas delivery system includes a delivery conduit (2). One end of the delivery conduit (2) is communicated with the pressurized gas inlet, and the other end is connected to a gas source.

10. A device for matching the pressurization flow rate and temperature during the variable thrust process of a rocket engine according to claim 9, characterized in that: A pressurized flow regulator (21) is provided on the delivery conduit (2).

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