Supercharging flow and temperature matching device in variable thrust process of rocket engine

Abstract

The invention relates to a rocket engine variable thrust process pressurized flow and temperature matching device which comprises a mixer and a pressurized gas conveying system, one end of the mixer is provided with a pressurized liquid inlet guide pipe communicated with an inner cavity of the mixer, and the other end of the mixer is provided with a pressurized mixed gas outlet guide pipe communicated with the inner cavity of the mixer. The surface of the mixer is provided with a pressurized gas inlet communicated with an inner cavity of the mixer, the pressurized gas conveying system is communicated with the pressurized gas inlet, a turbulent flow structure is arranged at the position, close to the pressurized liquid inlet guide pipe, in the mixer, and a flow guide structure is arranged at the position, corresponding to the pressurized gas inlet, in the mixer. The flow guide structure is used for guiding gas entering through the pressurized gas inlet towards the direction where the turbulent flow structure is located. The self-generated supercharging device has the advantages that the structural design is simple and reasonable, the current self-generated supercharging flow and temperature can be matched in the variable-thrust process of an engine, and therefore the supercharging requirement of a carrier rocket propellant storage tank is met.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, and in particular to a boost flow and temperature matching device during a variable thrust process of a rocket engine. Background Art

[0002] As the mainstream carrier for humans to enter space, launch vehicles have the remarkable characteristics of 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 the propellant medium used in liquid phase. Common liquid propellants include nitrogen tetroxide, unsymmetrical dimethyl hydrazine, hydrogen peroxide, liquid oxygen, kerosene, liquid methane, liquid hydrogen, etc. During the operation of liquid launch vehicles, liquid propellant medium is continuously consumed, and the liquid level in the propellant tank of the launch vehicle continues to decrease. As the liquid volume in the tank decreases, the tank pressure will continue to decrease. However, the rocket engine requires a certain inlet pressure to ensure the normal operation of the engine. Therefore, the propellant tank pressurization system of the launch vehicle needs to be specially designed. Commonly used pressurization methods include inert gas pressure replenishment and rocket engine self-pressurization.

[0003] Self-generated supercharging of rocket engines refers to the process in which liquid propellant is heated to a gaseous state in the engine during the operation of the rocket engine, and then returned to the propellant tank, using its own propellant medium to produce a supercharging medium for the propellant tank, hence the name self-generated supercharging. Traditional liquid rocket engines in fixed-thrust working mode can match the supercharging flow and temperature at the rated operating point of the engine well through calibration tests and other means. Through design finalization, it can basically ensure that the flow and temperature at the design point meet the use requirements, and no additional device settings are required.

[0004] At present, 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 liquid rocket engines are typical nonlinear systems, during the thrust adjustment process, the flow rate and temperature of the propellant boost will inevitably deviate from the boost demand of the current thrust condition. The traditional solution is to ensure through design that in the thrust adjustment condition, its boost capacity is still guaranteed to be no less than the boost demand of the current thrust. This causes the propellant tank pressure to be too high during flight, resulting in many problems such as large dead weight and poor performance of the launch vehicle. In severe cases, it may also cause waste of propellant and damage the performance of the launch vehicle.

[0005] Based on this, it is necessary to develop a boost flow and temperature matching device for 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 boost flow and temperature matching device for a rocket engine during thrust variation, 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 boost flow and temperature matching device for a rocket engine during thrust variation, comprising a mixer and a pressurized gas delivery system, wherein one end of the mixer is provided with a pressurized liquid inlet conduit connected to its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit connected to its inner cavity, a surface of the mixer is provided with a pressurized gas inlet connected to its inner cavity, the pressurized gas delivery system is connected to the pressurized gas inlet, a portion of the mixer close to the pressurized liquid inlet conduit is provided with a flow disturbance structure, and a portion of the mixer corresponding to the pressurized gas inlet is provided with a flow guide structure, and the flow guide structure is used to guide the gas entering through the pressurized gas inlet toward the direction where the flow disturbance structure is located.

[0009] Based on the above technical solution, the present invention can also be improved as follows.

[0010] Furthermore, the blender is a cylindrical container.

[0011] Furthermore, 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 interconnected, and the pressurized gas delivery system is connected to the inner cavity of the pressurized gas collecting chamber.

[0012] Furthermore, the above-mentioned guide structure is a conical guide cylinder, the conical end of the guide structure faces the direction of the above-mentioned spoiler structure, the conical bottom of the guide structure is connected to the inner wall of the above-mentioned mixer, and the above-mentioned pressurized gas inlet is provided with multiple ones and distributed at intervals along the circumference of the above-mentioned mixer.

[0013] Furthermore, the above-mentioned guide structure includes a plurality of guide plates, and the above-mentioned pressurized gas inlet is provided with a plurality of guide plates, which are distributed at intervals along the circumference of the above-mentioned mixer. The plurality of guide plates are connected to the inner wall of the above-mentioned mixer at equal intervals along the circumference, and are distributed one by one on the inner side of each of the above-mentioned pressurized gas inlets. Each of the above-mentioned guide plates extends obliquely toward the direction where the above-mentioned spoiler structure is located and the middle of the inner cavity of the mixer.

[0014] Furthermore, the flow disturbance structure comprises a partition plate arranged on the inner wall of the blender, and a flow hole is provided in the middle of the partition plate.

[0015] Furthermore, the partition is annular.

[0016] Furthermore, the partition includes a plurality of sector-shaped plate surfaces, and the plurality of sector-shaped plate surfaces are distributed on the inner wall of the mixer at equal intervals along the circumferential direction.

[0017] Furthermore, the pressurized gas delivery system comprises a delivery conduit, one end of which is connected to the pressurized gas inlet, and the other end of which is connected to a gas source.

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

[0019] The beneficial effects of the present invention are: the structural design is simple and reasonable, and it can help the engine to match the current self-generated boost flow and temperature during the variable thrust process, thereby meeting the boost demand of the launch vehicle propellant tank. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0021] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0022] 1. mixer; 2. delivery conduit; 11. pressurized liquid inlet conduit; 12. pressurized mixed gas outlet conduit; 13. flow disturbance structure; 14. flow guide structure; 15. pressurized gas collecting chamber; 21. pressurized flow regulator. DETAILED DESCRIPTION

[0023] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0024] Example: Figure 1 As shown, the boost flow and temperature matching device for the variable thrust process of a rocket engine of this embodiment includes a mixer 1 and a pressurized gas delivery system. The mixer 1 is provided with a pressurized liquid inlet conduit 11 connected to its inner cavity at one end, and a pressurized mixed gas outlet conduit 12 connected to its inner cavity at the other end. A pressurized gas inlet connected to its inner cavity is provided on the surface of the mixer 1. The pressurized gas delivery system is connected to the pressurized gas inlet. A spoiler structure 13 is provided at a portion of the mixer 1 near the pressurized liquid inlet conduit 11. A guide structure 14 is provided at a portion of the mixer 1 corresponding to the pressurized gas inlet. The guide structure 14 is used to guide the gas entering through the pressurized gas inlet toward the direction where the spoiler structure 13 is located.

[0025] In the boost flow and temperature matching device for the variable thrust process of the rocket engine of the present 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 the regenerative cooling, heat exchange and heating of the engine thrust chamber (such as the thrust chamber cooling outlet collector). Inside the mixer 1, the boost liquid flows normally from the upstream to the downstream (that is, it flows from one end of the mixer 1 to the other end). After being disturbed by the flow spoiler structure 13, a local vortex is formed in the area between the flow spoiler structure 13 and the guide structure 14. At the same time, the boost gas at this location is sprayed in from the boost gas inlet. Under the action of the guide structure 14, the flow direction of the gas after injection forms an inclination angle (the inclination angle is an obtuse angle) with the normal flow direction of the boost liquid, similar to the boost gas sprayed in the reverse direction, and forms a mutual impact with the boost liquid, thereby enhancing the gas-liquid mixing effect. This setting of the supercharged blender 1 can greatly improve the blending efficiency of the supercharged liquid and gas. When the blending flow rate is constant, the size of the blender can be greatly reduced, which is conducive to the compact layout of the structure. This setting of the supercharged blender can ensure that the blender has good blending efficiency within a large range of changes when the supercharged liquid and gas flow rates are constantly changing during the engine thrust change process, and achieve a basically uniform blending effect at the blender outlet. The design of this structure is conducive to strengthening the mixing of gas and liquid, shortening the length of the mixing zone, and significantly improving the compactness of the structure.

[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 are 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 faces the direction of the above-mentioned spoiler structure 13, the conical bottom of the guide structure 14 is connected to the inner wall of the above-mentioned mixer 1, and the above-mentioned pressurized gas inlet is provided with multiple ones, and is distributed at intervals along the circumference of the above-mentioned mixer 2.

[0031] In the above scheme 1), the flow guide structure 14 is an integral conical cylinder component, which is sealed on the inner wall of the blender 1, and the angle between its conical surface and the center line forms an obtuse angle. In combination with the multiple pressurized gas inlets uniformly distributed at intervals on the inner wall of the blender 1, the supercharger gas can be evenly sprayed into all directions of the inner wall of the blender 1, which is beneficial to subsequent uniform blending.

[0032] 2) The above-mentioned guide structure 14 includes a plurality of guide plates, and the above-mentioned pressurized gas inlet is provided with a plurality of them, and they are distributed at intervals along the circumference of the above-mentioned mixer 2. The plurality of guide plates are connected to the inner wall of the above-mentioned mixer 1 at equal intervals along the circumference, and are distributed one by one on the inner side of each of the above-mentioned pressurized gas inlets. Each of the above-mentioned guide plates extends obliquely toward the direction where the above-mentioned spoiler structure 13 is located and the middle part of the inner cavity of the mixer 2.

[0033] In the above-mentioned scheme 2), the guide structure 14 adopts multiple separately designed guide plates, which can be distributed corresponding to each pressurized gas inlet, and an obtuse angle is formed between the guide 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 disturbed, thereby achieving effective mixing.

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

[0035] ① The flow disturbance structure 13 comprises a partition plate arranged on the inner wall of the blender 1, and a flow hole is provided in the middle of the partition plate.

[0036] More specifically, the partition is annular.

[0037] ② The partition plate comprises a plurality of sector-shaped plate surfaces, and the plurality of sector-shaped plate surfaces are distributed on the inner wall of the mixer 1 at equal intervals along the circumferential direction.

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

[0039] In this embodiment, the pressurized gas delivery system comprises a delivery conduit 2, one end of the delivery conduit 2 is connected to the pressurized gas inlet, and the other end is connected to a gas source.

[0040] In this embodiment, a boost flow regulator 21 is provided on the above-mentioned delivery conduit 2, which can avoid the problem that the boost liquid may be a cryogenic propellant (liquid oxygen, liquid methane, etc.). The boost flow regulator 21 can use a conventional flow valve on the pipeline, and the purpose is to accurately control the total boost flow, the flow of the boost liquid, and the flow of the gas. Among them, the flow of the boost liquid needs to be limited by a throttling element at the engine outlet, and as the engine changes thrust, the boost liquid flow changes with the pressure and temperature changes at the inlet of the throttling element. The flow of the boost gas also needs to be limited, and the flow control can also be completed directly through the boost flow regulator 21. During the rocket engine thrust change process, the boost flow regulator 21 adjusts the boost gas flow to ensure that the temperature of the boost mixed gas does not change too much during the rocket engine thrust change process. The mixed boost mixed gas eventually flows into the rocket tank through the boost mixed gas outlet conduit 12 to pressurize the liquid propellant in the rocket tank. In addition, during the rocket engine thrust change process, the flow ratio of the pressurized liquid and the pressurized gas will change due to the mismatch between the pressure and temperature of the outlet position of the pressurized liquid and the pressurized gas during the engine thrust change process, and the temperature of the pressurized gas may also change. At different engine thrust change characteristic points, the boost flow regulator 21 works at different opening positions to adjust the flow of the pressurized gas, ensuring that the final flow of the pressurized mixed gas changes according to the thrust change ratio and the temperature remains basically unchanged.

[0041] It should be noted that in this embodiment, the requirements for the boost flow regulator 21 are significantly reduced. During use, the boost flow regulator 21 is not completely closed, and there is no requirement for leakage rate control of the inlet and outlet of the boost flow regulator.

[0042] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0043] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0044] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, 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 specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

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

[0047] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A boost flow and temperature matching device for a rocket engine during thrust variation, characterized in that: The invention comprises a blender (1) and a pressurized gas delivery system, wherein one end of the blender (1) is provided with a pressurized liquid inlet conduit (11) connected to its inner cavity, and the other end is provided with a pressurized mixed gas outlet conduit (12) connected to its inner cavity, a surface of the blender (1) is provided with a pressurized gas inlet connected to its inner cavity, and the pressurized gas delivery system is connected to the pressurized gas inlet, a portion of the blender (1) close to the pressurized liquid inlet conduit (11) is provided with a flow disturbance structure (13), and a portion of the blender (1) corresponding to the pressurized gas inlet is provided with a flow guide structure (14), and the flow guide structure (14) is used to guide the gas entering through the pressurized gas inlet toward the direction where the flow disturbance structure (13) is located.

2. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 1, characterized in that: The blender (1) is a cylindrical container.

3. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 2, characterized in that: 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).

4. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 2, characterized in that: The flow guide structure (14) is a conical guide cylinder, the conical end of the flow guide structure (14) faces the direction of the flow disturbance structure (13), the conical bottom of the flow guide structure (14) is connected to the inner wall of the mixer (1), and a plurality of pressurized gas inlets are provided and are distributed at intervals along the circumference of the mixer (1).

5. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 2, characterized in that: The guide structure (14) includes a plurality of guide plates, a plurality of which are provided at the pressurized gas inlet and are distributed at intervals along the circumference of the mixer (1). The plurality of guide plates are connected to the inner wall of the mixer (1) at equal intervals along the circumference and are distributed one by one on the inner side of each of the pressurized gas inlets. Each of the guide plates extends obliquely toward the location of the spoiler structure (13) and the middle of the inner cavity of the mixer (1).

6. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 2, characterized in that: The flow disturbance structure (13) comprises a partition plate arranged on the inner wall of the mixer (1), and a flow hole is provided in the middle of the partition plate.

7. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 6, characterized in that: The partition is annular.

8. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 6, characterized in that: The partition plate comprises a plurality of sector-shaped plate surfaces, and the plurality of sector-shaped plate surfaces are distributed at equal intervals along the circumferential direction on the inner wall of the mixer (1).

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

10. The device for matching boost flow and temperature during thrust change of a rocket engine according to claim 9, characterized in that: The delivery conduit (2) is provided with a boost flow regulator (21).

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