WO2019127936A1

WO2019127936A1 - Nozzle structure, jet device and engine

Info

Publication number: WO2019127936A1
Application number: PCT/CN2018/079768
Authority: WO
Inventors: 刘若鹏; 栾琳; 李娜
Original assignee: 深圳光启空间技术有限公司
Priority date: 2017-12-25
Filing date: 2018-03-21
Publication date: 2019-07-04
Also published as: CN207795422U

Abstract

Provided are a nozzle structure, a jet device and an engine. The nozzle structure (2) comprises: a nozzle body (10), the nozzle body (10) being provided with a liquid flow channel (11), with a first end of the liquid flow channel (11) being a liquid inlet port (12), and a second end of the liquid flow channel (11) being a liquid jet port (13); and a swirler (20), the swirler (20) being disposed in the liquid flow channel (11) and located at the liquid jet port (13). The nozzle body (10) is further provided with an air flow channel (14), with a first end of the air flow channel (14) being an air inlet port (15), and a second end of the air flow channel (14) being an air jet port (16). The air jet port (16) is spaced apart from the liquid jet port (13) so as to exert a shearing action on a tapered atomized liquid fuel jetted out of the liquid jet port (13). The jet device solves the problem of the performance of a liquid rocket engine being affected by incomplete combustion of the liquid fuel due to the poor atomization effect of jet devices in the prior art on the liquid fuel.

Description

Nozzle structure, injection device and engine

Technical field

The utility model relates to the technical field of rocket engines, in particular to a nozzle structure, an injection device and an engine.

Background technique

Liquid rocket engines are usually provided with an injection device for jetting and igniting two components (liquid fuel and gas oxidant), and the atomizing injection effect of the injection device on the liquid fuel determines the combustion efficiency of the liquid fuel, and also directly It is about the performance of liquid rocket engines.

technical problem

The injection device of the existing liquid rocket engine has a poor atomization effect on the liquid fuel, thereby causing insufficient combustion of the liquid fuel, thereby affecting the working performance of the liquid rocket engine, so that the liquid rocket engine cannot meet different injection conditions, Rocket propulsion performance.

Technical solution

The main object of the present invention is to provide a nozzle structure, an injection device and an engine to solve the problem that the atomization effect of the injection device in the prior art on the liquid fuel is poor, thereby causing insufficient combustion of the liquid fuel and affecting the liquid rocket. Problems with the performance of the engine.

In order to achieve the above object, according to an aspect of the present invention, a nozzle structure is provided, comprising: a nozzle body having a liquid flow passage, a first end of the liquid flow passage being a liquid inlet port, and a second liquid flow passage The end is a liquid injection port; the vortex device is arranged in the liquid flow channel and located at the liquid injection port; the nozzle body further has an air flow channel, the first end of the air flow channel is an air inlet port, and the second end of the air flow channel is a gas The injection port is disposed at a distance from the liquid injection port to shear the cone-shaped atomized liquid fuel ejected from the liquid injection port.

Further, the liquid flow path includes a liquid flow path section, a necking flow path section and a jet flow path section which are sequentially connected, wherein the cross-sectional area of the constricted flow path section gradually decreases in a direction away from the liquid flow path section, The cross-sectional area of the jet flow path section is smaller than the cross-sectional area of the liquid flow path section, and the swirler is disposed in the liquid flow path section, the necked flow path section forms a swirl chamber, and the jet flow path section has a liquid ejection port.

Further, the nozzle body has a cylindrical shape, and the cylindrical nozzle body includes a first barrel and a second barrel that are connected to each other, wherein the liquid flow passage penetrates the first barrel and the second barrel along the axial direction of the nozzle body The connection between the first cylinder and the second cylinder forms a stepped structure, and the air inlet port of the air flow passage is opened on the step surface of the step structure, and the air flow passage extends in the second cylinder body.

Further, the air flow channels are plural, and the plurality of air flow channels are disposed around the outer circumference of the liquid flow channel.

Further, a swirling groove is formed on the swirler, and a swirling passage is formed between the guiding groove and the inner wall surface of the nozzle body.

Further, the swirl channel extends in a spiral shape.

According to another aspect of the present invention, an injection device is provided, comprising: a casing having a liquid collecting chamber and a collecting chamber spaced apart from each other, wherein the housing is further provided with a liquid inlet hole and an air inlet hole, wherein the liquid inlet The hole communicates with the liquid collecting chamber, the air inlet hole communicates with the air collecting chamber; the nozzle structure, the nozzle structure is disposed in the outer casing, and the liquid inlet port of the nozzle structure communicates with the liquid collecting chamber, and the air inlet port of the nozzle structure is connected with the air collecting chamber The nozzle structure is the above nozzle structure.

Further, the nozzle structure is plural, and the plurality of nozzle structures are spaced apart around the axis of the outer casing.

Further, the spraying device further includes a hydraulic detecting portion and a gas pressure detecting portion, and the liquid pressure measuring hole and the gas pressure measuring hole are further disposed on the outer casing, and the hydraulic detecting portion is disposed at the liquid pressure measuring hole to detect the pressure in the liquid collecting chamber, The air pressure detecting portion is disposed at the gas pressure measuring hole to detect the pressure in the air collecting chamber.

According to another aspect of the present invention, there is provided an engine including an engine body and an injection device disposed on the engine body, the injection device being the above-described injection device.

Beneficial effect

By applying the technical solution of the utility model, the liquid fuel moves in the liquid flow channel and is atomized by the centrifugal force of the vortex device and is ejected by the liquid injection port, and the liquid fuel injected is in a cone shape. The gas oxidant moves in the gas flow passage and is ejected by the gas injection port. Since the gas injection port is spaced apart from the liquid injection port, the gas oxidant ejected from the gas injection port can be sprayed toward the liquid ejection port. The atomized liquid fuel produces a shearing effect, achieves the effect of secondary atomization, and the effect of double atomization of the liquid fuel ensures the mixing effect of the liquid fuel and the gas combustion improver, thereby improving the combustion efficiency of the liquid fuel, thereby Improves engine performance, allowing the engine to adapt to different injection conditions.

DRAWINGS

The accompanying drawings, which are incorporated in the claims of the claims In the drawing:

Figure 1 shows a schematic front view of an injection device in accordance with an alternative embodiment of the present invention;

Figure 2 shows a bottom view of the injection device of Figure 1;

Figure 3 is a schematic view showing the internal structure of the injection device of Figure 1;

4 shows a front schematic view of a nozzle structure in accordance with an alternative embodiment of the present invention;

Figure 5 is a top plan view showing the nozzle structure of Figure 4;

Figure 6 is a front elevational cross-sectional view taken along line A-A of Figure 5;

Fig. 7 is a front cross-sectional view showing the line B-B in Fig. 5.

Wherein, the above figures include the following reference numerals:

1, outer casing; 2, nozzle structure; 110, liquid collection chamber; 120, gas collection chamber; 130, liquid inlet hole; 140, air inlet hole; 150, liquid pressure measuring hole; 160, gas pressure measuring hole; Body; 11, liquid flow channel; 111, liquid flow channel segment; 112, necking flow channel segment; 113, jet flow channel segment; 12, liquid inlet port; 13, liquid injection port; 14, air flow channel; Gas port; 16, gas injection port; 17, first cylinder; 18, second cylinder; 19, step surface; 20, vortex; 21, diversion channel.

Embodiments of the invention

The technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. example. The following description of the at least one exemplary embodiment is merely illustrative, and is in no way intended to limit the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

In order to solve the problem that the atomization effect of the injection device on the liquid fuel in the prior art is poor, thereby causing insufficient combustion of the liquid fuel and affecting the working performance of the liquid rocket engine, the utility model provides a nozzle structure and injection. And an engine, wherein the engine includes an engine body and an injection device disposed on the engine body, the injection device being the above-described and below-described injection device, as shown in FIGS. 1 to 3, the injection device including the outer casing 1 and the nozzle structure 2, The outer casing 1 has a liquid collecting chamber 110 and a gas collecting chamber 120. The outer casing 1 is further provided with a liquid inlet hole 130 and an air inlet hole 140. The liquid inlet hole 130 communicates with the liquid collecting chamber 110, and the air inlet hole 140 The air collection chamber 120 is in communication, the nozzle structure 2 is disposed in the outer casing 1, and the liquid inlet port 12 of the nozzle structure 2 is in communication with the liquid collection chamber 110. The air inlet port 15 of the nozzle structure 2 is in communication with the air collection chamber 120. The nozzle structure 2 is The nozzle structure described above and below.

It should be noted that the engine of the present application is preferably a rocket engine, and the injection device uses the nozzle structure 2 to inject liquid fuel and gas oxidant into the engine body, wherein the liquid fuel is stored in the sump 110 in a short term and is configured by the nozzle structure 2 The gas oxidizer is discharged in a short-term concentration and stored in the plenum 120 and ejected by the nozzle structure 2, and the gas oxidant is preferably oxygen.

As shown in FIG. 3 to FIG. 7, the nozzle structure includes a nozzle body 10 and a swirler 20, wherein the nozzle body 10 has a liquid flow path 11, and the first end of the liquid flow path 11 is a liquid inlet port 12, and the liquid flow channel 11 The second end is a liquid ejection port 13 , and the swirler 20 is disposed in the liquid flow channel 11 and located at the liquid ejection port 13 . The nozzle body 10 further has an air flow channel 14 , and the first end of the air flow channel 14 is an air inlet port 15 . The second end of the air flow passage 14 is a gas injection port 16, and the gas injection port 16 is spaced apart from the liquid injection port 13 to cause shearing of the cone-shaped atomized liquid fuel ejected from the liquid ejection port 13.

Thus, the liquid fuel moves in the liquid flow path 11 and is atomized by the centrifugal force of the vortex device 20 and is ejected by the liquid ejecting port 13, and the ejected liquid fuel has a conical mist shape, and the gas ignites. The agent moves within the gas flow passage 14 and is ejected by the gas injection port 16, and the gas injection port 16 is disposed at a distance from the liquid injection port 13, so that the gas oxidant ejected from the gas injection port 16 can be ejected to the liquid ejection port 13. The cone-shaped atomized liquid fuel produces a shearing effect, achieving the effect of secondary atomization, and the effect of double atomization of the liquid fuel ensures the mixing effect of the liquid fuel and the gas combustion improver, and improves the liquid fuel. The combustion efficiency, which improves the performance of the engine, allows the engine to adapt to different injection conditions.

As shown in FIG. 6, the liquid flow path 11 includes a liquid flow path section 111, a necking flow path section 112, and a jet flow path section 113 which are sequentially connected, wherein the cross-sectional area of the constricted flow path section 112 is away from the liquid flow. The direction of the track section 111 gradually decreases, the cross-sectional area of the jet flow path section 113 is smaller than the cross-sectional area of the liquid flow path section 111, and the swirler 20 is disposed in the liquid flow path section 111, and the constricted flow path section 112 forms a spiral. The flow chamber, the jet flow path section 113 has a liquid ejection port 13.

At the beginning of the injection of the liquid fuel by the nozzle structure 2, since the pressure in the liquid flow path 11 has not been established, the liquid fuel leaves the nozzle structure 2 in a column shape, and then, the liquid flow path 11 of the nozzle structure 2 generates a lower pressure to make the liquid fuel The generation of a certain axial velocity causes the liquid fuel to move downstream, and at the same time, due to the presence of the swirler 20 in the liquid flow path section 111, the liquid fuel is subjected to centrifugal force, so that the liquid fuel is ejected from the constricted flow path section 112. When there is a certain rotation speed, the rotation speed is converted into the radial speed and the tangential speed of the constricted flow path section 112 in a short time, so the liquid fuel rapidly increases in size in the radial direction, so that the liquid fuel is tapered. The shape gradually expands; however, this trend does not develop unrestrictedly because the surface tension of the liquid fuel increases as the tapered profile of the liquid fuel expands, and the surface of the liquid fuel in the shape of a cone The radius of curvature decreases, which together determine the injection pattern of the liquid fuel, so when the liquid fuel develops to a certain peak in the radial direction, it is subjected to its surface. The influence of the force begins to shrink, and at the same time, the degree of rotation of the liquid fuel begins to increase, but this reduced form does not develop unrestricted because the liquid fuel shrinks to near the necked flow path section 112. At the time of the axis, it expands again, and then expands, shrinks, re-expands, and then shrinks again and again. Therefore, at the beginning of the injection, the neck-shaped flow path section 112 will periodically move along the axis in a figure-eight shape. As the pressure in the liquid flow path 11 is further increased, the liquid fuel is still scattered radially in a hollow state, but the previous phenomenon no longer occurs. When the pressure is stable and reaches the set maximum value, the radial expansion of the liquid fuel also reaches the maximum at the same time. At this time, the atomized liquid film formed by the liquid fuel is the thinnest, and the interaction between the liquid fuel and the air is the strongest, and the fracture occurs. A stable misty cone field is presented.

As shown in FIG. 4 to FIG. 7 , the nozzle body 10 has a cylindrical shape, and the cylindrical nozzle body 10 includes a first cylindrical body 17 and a second cylindrical body 18 connected thereto, wherein the liquid flow channel 11 is along the nozzle body 10 . The first cylindrical body 17 and the second cylindrical body 18 are axially penetrated, and the joint between the first cylindrical body 17 and the second cylindrical body 18 forms a stepped structure, and the air inlet port 15 of the air flow passage 14 is opened on the step surface 19 of the stepped structure. The air flow passage 14 extends within the second cylinder 18. In this way, it is convenient to manufacture the nozzle body 10, and it is advantageous for the gas oxidant to enter the gas flow passage 14 through the inlet port 15 and be ejected by the gas injection port 16 to effectively impact and shear the cone-shaped atomized liquid. Fuel to enhance the atomization effect on liquid fuel.

Optionally, the airflow passage 14 extends in a curve or includes a plurality of linear flow passage segments that are in communication.

As shown in FIGS. 5 to 7, in order to further enhance the secondary atomization effect on the tapered atomized liquid fuel, the air flow passages 14 are plural, and the plurality of air flow passages 14 are spaced around the outer circumference of the liquid flow passage 11. Settings. Thus, it is ensured that the plurality of gas injection ports 16 of the plurality of gas flow passages 14 are disposed around the outer circumference of the liquid ejection port 13.

Alternatively, the air flow passages 14 are four, and the four air flow passages 14 are equally spaced around the outer circumference of the liquid flow passage 11.

As shown in FIGS. 6 and 7, the swirler 20 is provided with a flow guiding groove 21, and a swirling passage is formed between the flow guiding groove 21 and the inner wall surface of the nozzle body 10.

Optionally, the swirl channel extends helically. This ensures that the swirler 20 acts as a swirling effect on the liquid fuel.

It should be noted that, in the embodiment of the present application, in order to improve the working performance of the engine and increase the power output of the engine, the nozzle structure 2 is plural, and the plurality of nozzle structures 2 are spaced apart around the axis of the casing 1.

Preferably, the nozzle structure 2 is three, and the three nozzle structures 2 are equally spaced around the axis of the outer casing 1.

As shown in FIG. 3, the injection device further includes a hydraulic pressure detecting portion and a gas pressure detecting portion. The outer casing 1 is further provided with a liquid pressure measuring hole 150 and a gas pressure measuring hole 160. The hydraulic pressure detecting portion is disposed at the liquid pressure measuring hole 150 to detect The pressure in the liquid collection chamber 110 is provided at the gas pressure measuring hole 160 to detect the pressure in the gas collection chamber 120.

It is to be noted that the terminology used herein is for the purpose of describing particular embodiments, and is not intended to limit the exemplary embodiments. As used herein, the singular " " " " " " There are features, steps, operations, devices, components, and/or combinations thereof.

The relative arrangement of the components and steps, numerical expressions, and numerical values set forth in these embodiments are not intended to limit the scope of the invention. In the meantime, it should be understood that the dimensions of the various parts shown in the drawings are not drawn in the actual scale relationship for the convenience of the description. Techniques, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the techniques, methods, and devices should be considered as part of the specification. In all of the examples shown and discussed herein, any specific values are to be construed as illustrative only and not as a limitation. Accordingly, other examples of the exemplary embodiments may have different values. It should be noted that similar reference numerals and letters indicate similar items in the following figures, and therefore, once an item is defined in one figure, it is not required to be further discussed in the subsequent figures.

In the description of the present invention, it is to be understood that the orientation words such as "front, back, up, down, left, right", "horizontal, vertical, vertical, horizontal" and "top, bottom", etc. are indicated. Azimuth or positional relationship is generally based on the orientation or positional relationship shown in the drawings, and is merely for the convenience of the description of the present invention and the simplified description, which are not intended to indicate or imply the indicated device. Or the components must have a specific orientation or be constructed and operated in a specific orientation, and thus are not to be construed as limiting the scope of the invention; the orientations "inside and outside" refer to the inside and outside of the contours of the components themselves.

For convenience of description, spatially relative terms such as "above", "above", "on top", "above", etc., may be used herein to describe as in the drawings. The spatial positional relationship of one device or feature to other devices or features. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation of the device described. For example, if the device in the figures is inverted, the device described as "above other devices or configurations" or "above other devices or configurations" will be positioned "below other devices or configurations" or "at Under other devices or configurations." Thus, the exemplary term "above" can include both "over" and "under". The device can also be positioned in other different ways (rotated 90 degrees or at other orientations) and the corresponding description of the space used herein is interpreted accordingly.

In addition, it should be noted that the use of the words "first", "second", etc. to limit the components is only to facilitate the distinction between the corresponding components, if not stated otherwise, the above words have no special meaning, so can not understand To limit the scope of protection of the present invention.

It should be noted that the terms "first", "second" and the like in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or order. It is to be understood that the data so used may be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in a sequence other than those illustrated or described herein.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention. For those skilled in the art, various modifications and changes can be made in the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and scope of the present invention are intended to be included within the scope of the present invention.

Claims

A nozzle structure, comprising:

a nozzle body (10) having a liquid flow passage (11), the first end of the liquid flow passage (11) being an inlet port (12), and the liquid flow passage (11) The second end is a liquid injection port (13);

a swirler (20), the swirler (20) being disposed in the liquid flow passage (11) and located at the liquid injection port (13);

The nozzle body (10) further has an air flow passage (14), the first end of the air flow passage (14) is an intake port (15), and the second end of the air flow passage (14) is a gas injection port ( 16), the gas injection port (16) is spaced apart from the liquid injection port (13) to shear the cone-shaped atomized liquid fuel ejected by the liquid ejection port (13) .
The nozzle structure according to claim 1, wherein said liquid flow path (11) comprises a liquid flow path section (111), a neck flow path section (112), and a jet flow path section (113) that are sequentially connected. Wherein the cross-sectional area of the necked flow path section (112) gradually decreases in a direction away from the liquid flow path section (111), the cross-sectional area of the injection flow path section (113) being smaller than a cross-sectional area of the liquid flow path section (111), and the swirler (20) is disposed in the liquid flow path section (111), and the constricted flow path section (112) forms a swirling chamber. The jet flow path section (113) has the liquid ejecting port (13).
The nozzle structure according to claim 1, wherein the nozzle body (10) has a cylindrical shape, and the nozzle body (10) having a cylindrical shape includes a first barrel (17) and a second connected to each other. a cylinder (18), wherein the liquid flow passage (11) penetrates the first cylinder (17) and the second cylinder (18) in an axial direction of the nozzle body (10), A joint structure of the first cylinder (17) and the second cylinder (18) forms a stepped structure, and an air inlet port (15) of the air flow passage (14) is opened on the step surface of the step structure (19) Above, the air flow passage (14) extends within the second cylinder (18).
The nozzle structure according to claim 3, wherein the air flow passages (14) are plural, and the plurality of air flow passages (14) are spaced around the outer circumference of the liquid flow passage (11).
The nozzle structure according to claim 1, wherein the swirler (20) is provided with a flow guiding groove (21), and the inner guiding surface of the guiding body (21) and the nozzle body (10) A swirl channel is formed between them.
The nozzle structure according to claim 5, wherein the swirl passage extends in a spiral shape.
A spraying device, comprising:

a casing (1) having a plurality of liquid collecting chambers (110) and a collecting chamber (120), and the casing (1) is further provided with a liquid inlet hole (130) and an air inlet hole (1) 140), wherein the liquid inlet hole (130) is in communication with the liquid collection chamber (110), and the air inlet hole (140) is in communication with the gas collection chamber (120);

a nozzle structure (2), the nozzle structure (2) is disposed in the outer casing (1), and a liquid inlet port (12) of the nozzle structure (2) is in communication with the liquid collection chamber (110). The intake port (15) of the nozzle structure (2) is in communication with the plenum chamber (120), and the nozzle structure (2) is the nozzle structure according to any one of claims 1 to 6.
The spraying device according to claim 7, characterized in that the nozzle structure (2) is plural, and a plurality of the nozzle structures (2) are spaced apart around the axis of the outer casing (1).
The spraying device according to claim 7, wherein the spraying device further comprises a hydraulic pressure detecting portion and a gas pressure detecting portion, and the casing (1) is further provided with a liquid pressure measuring hole (150) and a gas pressure measuring hole. (160), the hydraulic pressure detecting portion is disposed at the liquid pressure measuring hole (150) to detect a pressure in the liquid collecting chamber (110), and the air pressure detecting portion is disposed at the gas pressure measuring hole ( 160) to detect the pressure within the plenum (120).
An engine comprising an engine body and an injection device disposed on the engine body, wherein the injection device is the injection device according to any one of claims 7 to 9.