Two-dimensional thrust vectoring nozzle and aircraft
By designing the convergence section, expansion section and flexible auxiliary jet pipeline structure of the binary vector nozzle, the difficulties of mechanical and pneumatic adjustment in the prior art are solved, and efficient thrust vector control and stable engine operation are achieved.
Patent Information
- Application Number
- CN202510510952.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-22
- Publication Date
- 2025-07-08
AI Technical Summary
It is difficult to take into account both mechanical and pneumatic adjustment without affecting the joint operation of the aircraft engine, resulting in a decrease in thrust and an increase in fuel consumption.
A binary vector nozzle structure including a converging section, an expansion section, an adjustment assembly, a flexible auxiliary jet pipeline and a switch is designed. The throat cross-sectional area is controlled by the radial rotation of the adjustment assembly, and the first airflow is interfered with by the flexible auxiliary jet pipeline and the second airflow to achieve efficient thrust vector control.
Without affecting the performance of the engine, a large thrust vector angle and efficient thrust vector efficiency are achieved, reducing system complexity and cost, and improving the maintainability of the nozzle.
Smart Images
Figure CN120273829A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of aeroengine nozzles, and in particular, to a two-dimensional vector nozzle and an aircraft. Background Art
[0002] In the field of fighter jets, a two-dimensional vector nozzle can accurately adjust the cross-sectional area of the nozzle throat according to the requirements of different working conditions, and can effectively reduce the infrared radiation of the exhaust system. The core principle of the aerodynamic thrust vector technology is to actively control the main flow of the nozzle by using the secondary flow, so that the air flow deflects in the expected direction. On the one hand, it greatly reduces the weight of the nozzle, significantly reduces the complexity and manufacturing cost of the system; on the other hand, it also improves the maintainability of the nozzle and reduces the difficulty and cost of logistics support. In addition, this technology also has the characteristics of high sensitivity and fast response speed. Therefore, the two-dimensional vector nozzle configuration with both mechanical and aerodynamic adjustments has become a research hotspot. A new generation of fighter jets should have the performance of stealth, multi-condition working ability and aerodynamic vector, so the two-dimensional vector nozzle configuration with both mechanical and aerodynamic adjustments has become a research hotspot.
[0003] In the related art, the throat control of a two-dimensional vector nozzle requires adjusting multiple nozzle wall surfaces, and the mechanical adjustment is difficult. At the same time, the high-pressure secondary flow required for the two-dimensional vector nozzle with aerodynamic adjustment comes from the compression components of the aeroengine. The greater the air extraction volume, the more obvious the impact on the common working of the aeroengine. When 15% of the secondary flow is extracted from the fan outlet and a thrust vector angle of 16.50° is obtained, the engine thrust drops by about 19%, and the specific fuel consumption increases by about 18.7%. In order to reduce this impact and at the same time ensure the realization of an available thrust vector angle, it is necessary to improve the configuration and working mode of the vector nozzle with aerodynamic adjustment. However, the scheme for improving the aerodynamic vector is restricted by the mechanically adjustable wall surface, making the configuration design of the two-dimensional vector nozzle with both mechanical and aerodynamic adjustments complicated. It can be seen that it is difficult for the two-dimensional vector nozzle in the related art to balance mechanical adjustment and aerodynamic adjustment without affecting the common working of the aeroengine. Summary of the Invention
[0004] In view of the above problems, the present application is proposed. The present application provides a two-dimensional vector nozzle and an aircraft.
[0005] According to one aspect of the present application, a two-dimensional vector nozzle is provided, including:
[0006] The binary vector nozzle body, the adjustment component, the air flow injection component and the switch; the binary vector nozzle body includes a converging section and a diverging section rotatably connected to the converging section. The converging section and the diverging section have a fluid passage for the first air flow to pass through. The adjustment component is rotatably connected to the outer side wall of the converging section, and the adjustment direction of the adjustment component is the radial direction of the binary vector nozzle body; the air flow injection component includes a flexible auxiliary injection pipeline and a second air flow injection pipeline. One end of the flexible auxiliary injection pipeline is communicated with the fluid passage of the converging section, the other end of the flexible auxiliary injection pipeline is communicated with the fluid passage of the diverging section, the switch is connected to one end of the second air flow injection pipeline, and the other end of the second air flow injection pipeline is communicated with the fluid passage of the diverging section.
[0007] Compared with the prior art, the dual vector nozzle provided in the present application includes a dual vector nozzle body, an adjustment assembly, an air flow injection assembly, and a switch. The dual vector nozzle body includes a convergent section and a divergent section rotatably connected to the convergent section. The convergent section and the divergent section have a fluid passage for the first air flow to pass through. The adjustment assembly is rotatably connected to the outer side wall of the convergent section, and the adjustment direction of the adjustment assembly is the radial direction of the dual vector nozzle body. Therefore, when the adjustment assembly rotates along the radial direction, a force will be exerted on the convergent section. This force will cause the convergent section to rotate by a certain angle and drive the divergent section to rotate as well, so that the junction between the convergent section and the divergent section changes, thereby achieving the purpose of adjustable cross-sectional area of the throat at this junction. Moreover, the air flow injection assembly includes a flexible auxiliary injection pipeline and a second air flow injection pipeline. One end of the flexible auxiliary injection pipeline is connected to the fluid passage of the convergent section, and the other end of the flexible auxiliary injection pipeline is connected to the fluid passage of the divergent section. The switch is connected to one end of the second air flow injection pipeline, and the other end of the second air flow injection pipeline is connected to the fluid passage of the divergent section. Therefore, under the adjustment of the switch, a smaller flow rate of the second air flow is introduced into the fluid passage of the divergent section through the second air flow injection pipeline, strengthening the interference of the second air flow on the first air flow, increasing the deflection force of the first air flow, and causing it to deflect along the radial direction of the dual vector nozzle body, avoiding a greater impact on the performance of the aeroengine due to a large amount of extraction of the second air flow. The flexible auxiliary injection pipeline can inject the first air flow located in the convergent section into the fluid passage of the divergent section to enhance the interference effect of the second air flow on the first air flow, further increase the thrust vector angle, and improve the thrust vector efficiency. Using this structure and injection method can achieve vector control while reducing the impact on the common operation of the engine. At the same time, the flexible auxiliary injection pipeline can adapt to the rotation of the convergent section and the divergent section through its own contraction and stretching, thus perfectly solving the problem of difficult design of the high-efficiency aerodynamic vector structure brought by throat control and indirectly reducing the adverse impact on the common operation of the aeroengine, ensuring that the engine can work well under different working conditions. Based on this, the present application can achieve a larger range of pressure drop ratios by controlling the cross-sectional area of the throat and a smaller flow rate of the second air flow through the switch. Under the limitation of the above conditions, by adjusting the auxiliary injection angle and the pressure ratio between the second air flow and the first air flow, a larger thrust vector angle, higher thrust vector efficiency, and thrust coefficient can be achieved. It can be seen that the dual vector nozzle provided in the embodiment of the present application can take into account mechanical adjustment and aerodynamic adjustment without affecting the common operation of the aeroengine.
[0008] According to another aspect of the present application, an aircraft is provided, including the above dual vector nozzle.
[0009] Compared with the prior art, the beneficial effects of the aircraft provided in the present application are the same as those of the above dual vector nozzle, and will not be elaborated here.
[0010] It is to be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the claimed technology. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] By describing the embodiments of the present application in more detail in conjunction with the accompanying drawings, the above and other objects, features and advantages of the present application will become more apparent. The drawings are used to provide a further understanding of the embodiments of the present application and constitute a part of the specification, and are used together with the embodiments of the present application to explain the present application, and do not constitute a limitation to the present application. In the drawings, the same reference numerals generally represent the same components or steps.
[0012] Figure 1 A schematic structural diagram of a binary vector nozzle according to an embodiment of the present application is shown;
[0013] Figure 2 One of the schematic diagrams showing the deflection of the first air flow according to an embodiment of the present application is shown;
[0014] Figure 3 Another schematic diagram showing the deflection of the first air flow according to an embodiment of the present application is shown;
[0015] Figure 4 One of the cross-sectional views showing the binary convergent section and the divergent section according to an embodiment of the present application is shown;
[0016] Figure 5 Another cross-sectional view showing the binary convergent section and the divergent section according to an embodiment of the present application is shown.
[0017] Reference Numerals:
[0018] 1 - Binary vector nozzle body; 101 - Convergent section; 1011 - Circular to square convergent section; 1012 - Binary convergent section; 10121 - First convergent wall panel; 10122 - Second convergent wall panel; 102 - Divergent section; 1021 - First divergent wall panel; 1022 - Second divergent wall panel; 2 - Adjusting assembly; 201 - Telescopic rod; 202 - Triangular rocker arm; 3 - Air flow injection assembly; 301 - Flexible auxiliary injection pipeline; 302 - Second air flow injection pipeline and 4 - Switch. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0019] In order to make the objectives, technical solutions and advantages of the present application more apparent, exemplary embodiments according to the present application will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. It should be understood that the present application is not limited by the exemplary embodiments described herein.
[0020] In the field of fighter jets, the two-dimensional vector nozzle can accurately adjust the cross-sectional area of the nozzle throat according to the requirements of different working conditions, and can effectively reduce the infrared radiation of the exhaust system. The core principle of the aerodynamic thrust vector technology is to actively control the first airflow of the nozzle by using the secondary flow, so that the airflow deflects in the expected direction. On the one hand, it greatly reduces the weight of the nozzle, significantly reduces the complexity and manufacturing cost of the system; on the other hand, it also improves the maintainability of the nozzle and reduces the difficulty and cost of logistics support. In addition, this technology also has the characteristics of high sensitivity and fast response speed. Therefore, the two-dimensional vector nozzle configuration with both mechanical and aerodynamic adjustments has become a research hotspot. The new generation of fighter jets should have the performance of stealth, multi-condition working ability and aerodynamic vector, so the two-dimensional vector nozzle configuration with both mechanical and aerodynamic adjustments has become a research hotspot.
[0021] In the related technology, the throat control of the two-dimensional vector nozzle requires regulating multiple nozzle wall surfaces, and the mechanical adjustment is difficult. At the same time, the high-pressure secondary flow required for the two-dimensional vector nozzle with aerodynamic adjustment comes from the compression components of the aero-engine. The greater the air extraction volume, the more obvious the impact on the common working of the aero-engine. When 15% of the secondary flow is extracted from the fan outlet and a thrust vector angle of 16.50° is obtained, the engine thrust drops by about 19%, and the specific fuel consumption increases by about 18.7%. In order to reduce this impact and at the same time ensure the realization of an available thrust vector angle, it is necessary to improve the configuration and working mode of the vector nozzle with aerodynamic adjustment. However, the scheme for improving the aerodynamic vector is restricted by the mechanically adjustable wall surface, making the configuration design of the two-dimensional vector nozzle with both mechanical and aerodynamic adjustments complicated. It can be seen that it is difficult for the two-dimensional vector nozzle in the related technology to balance mechanical adjustment and aerodynamic adjustment without affecting the common working of the aero-engine.
[0022] In view of the above problems, the present application provides a two-dimensional vector nozzle. Figure 1 The structural schematic diagram of the two-dimensional vector nozzle according to the embodiment of the present application is shown. As Figure 1As shown in the figure, the two-dimensional vector nozzle includes a two-dimensional vector nozzle body 1, an adjustment assembly 2, an air flow injection assembly 3, and a switch 4. The two-dimensional vector nozzle body 1 includes a convergent section 101 and a divergent section 102 rotatably connected to the convergent section 101. The convergent section 101 and the divergent section 102 have a fluid passage for the first air flow to pass through. The adjustment assembly 2 is rotatably connected to the outer wall of the convergent section 101, and the adjustment direction of the adjustment assembly 2 is the radial direction of the two-dimensional vector nozzle body 1. The air flow injection assembly 3 includes a flexible auxiliary injection pipeline 301 and a second air flow injection pipeline 302. One end of the flexible auxiliary injection pipeline 301 is communicated with the fluid passage of the convergent section 101, and the other end of the flexible auxiliary injection pipeline 301 is communicated with the fluid passage of the divergent section 102. The switch 4 is connected to one end of the second air flow injection pipeline 302, and the other end of the second air flow injection pipeline 302 is communicated with the fluid passage of the divergent section 102.
[0023] During specific implementation, the first air flow generated by the engine enters the convergent section 101 of the two-dimensional vector nozzle. In the convergent section 101, the cross-sectional area of the passage gradually decreases. According to the continuity principle and Bernoulli's equation of fluid mechanics, the velocity of the air flow will gradually increase, and the pressure and temperature will decrease accordingly, enabling the air flow to be preliminarily accelerated and preparing for subsequent injection and vector control processes. When the adjustment assembly 2 rotates along the radial direction, a force will be applied to the convergent section 101. Since the adjustment assembly 2 is rotatably connected to the outer wall of the convergent section 101, this force will cause the convergent section 101 to rotate by a certain angle and drive the divergent section 102 to rotate as well, resulting in a change in the throat (the junction of the convergent section 101 and the divergent section 102), thereby achieving the purpose of adjustable cross-sectional area of the throat. Specifically, in the case of requiring high thrust, appropriately reducing the cross-sectional area of the throat can increase the flow velocity of the air flow in the throat, and then achieve more efficient expansion and acceleration in the divergent section 102, increasing the thrust generated by the nozzle. In some cases where it is necessary to reduce the thrust or adjust the air flow rate, the cross-sectional area of the throat can be increased to reduce the air flow velocity and flow rate.
[0024] During this process, under the adjustment of the switch 4, a second air flow with a smaller flow rate is introduced into the fluid channel communication of the expansion section 102 through the second air flow injection pipeline 302, strengthening the interference of the second air flow on the first air flow, increasing the deflection force of the first air flow, causing it to deflect along the radial direction of the dual-vector nozzle body 1, and avoiding a large impact on the performance of the aeroengine due to a large amount of extraction of the second air flow. The flexible auxiliary injection pipeline 301 can inject the first air flow located in the convergent section 101 into the fluid channel communication of the expansion section 102 to enhance the interference effect of the second air flow on the first air flow, further increasing the thrust vector angle and improving the thrust vector efficiency. With this structure and injection method, vector control can be achieved while reducing the impact on the co-working of the engine. At the same time, the flexible auxiliary injection pipeline 301 can adapt to the rotation of the convergent section 101 and the expansion section 102 through its own contraction and stretching, thus perfectly solving the problem of difficult design of the high-efficiency aerodynamic vector structure brought by throat control and indirectly reducing the adverse impact on the co-working of the aeroengine, ensuring that the engine can work well under different working conditions. Based on this, the present application can achieve a large range of pressure drop ratios by controlling the cross-sectional area of the throat, and achieve a smaller flow rate of the second air flow through the switch 4. Under the limitation of the above conditions, by adjusting the auxiliary injection angle and the pressure ratio between the second air flow and the first air flow, a large thrust vector angle, a high thrust vector efficiency, and a thrust coefficient can be achieved. It can be seen that the dual-vector nozzle provided by the embodiment of the present application can take into account mechanical adjustment and aerodynamic adjustment without affecting the co-working of the aeroengine.
[0025] It can be understood that the first air flow in the embodiment of the present application is the high-temperature and high-pressure gas generated by the engine, and the second air flow is the high-pressure cold air. Its gas supply equipment can be adjusted according to actual situations and is not limited herein. In addition, the way of rotational connection in the embodiment of the present application includes single hinge connection, double hinge connection, or ball head connection, which can be adjusted according to actual situations and is not limited herein.
[0026] Exemplarily, such as Figure 1As shown in the figure, the ratio of the cross-sectional area of the throat (the junction of the convergent section 101 and the divergent section 102) in the embodiment of the present application to the cross-sectional area of the second air flow injection pipeline 302 is 1: (0.04 - 0.15). First of all, the flow rate of the second air flow can be accurately controlled, ensuring that the second air flow can just right interfere with the first air flow, making it deflect along the radial direction of the dual vector nozzle body 1, and at the same time will not cause excessive damage to the overall flow characteristics of the first air flow, maintaining the orderliness of the air flow inside the engine, which is beneficial to the coordinated operation of various components of the engine. When the flow rate of the second air flow is too large, it will seriously disrupt the originally stable flow state of the first air flow, resulting in disordered air flow inside the engine and affecting the normal operation of components such as the compressor, combustion chamber and turbine; when the flow rate of the second air flow is too small, the first air flow cannot be effectively deflected.
[0027] Secondly, the second air flow is injected in a relatively concentrated manner, and the efficiency of its momentum transfer to the first air flow is relatively high. The relatively small cross-sectional area of the injection pipeline makes the injection speed and momentum direction of the second air flow relatively concentrated, enabling more effective momentum exchange with the first air flow, improving the interference efficiency of the secondary flow on the first air flow, and being able to play a more efficient role in realizing the deflection of the first air flow, which is beneficial to achieving a larger thrust vector angle and a higher thrust vector efficiency under the limitation of a smaller secondary flow rate.
[0028] Exemplarily, as Figure 1 shown, the injection angle of the second air flow injection pipeline 302 in the embodiment of the present application is 40° - 150°. At this time, by adjusting the injection angle of the second air flow injection pipeline 302, the impact angle and strength of the second air flow on the first air flow can be accurately controlled, so as to flexibly adjust the deflection degree of the first air flow to meet the thrust vector control requirements of the aeroengine under different flight states and mission requirements.
[0029] When the injection angle is greater than or equal to 40° and less than 90°, the second air flow impacts the first air flow at a relatively small angle, and the interference on the first air flow is relatively gentle. In this case, the second air flow mainly acts on the edge area of the first air flow, causing a certain degree of deflection of the first air flow. When the injection angle gradually approaches 90° from 40°, the impact strength of the second air flow on the first air flow gradually increases, and the deflection degree of the first air flow also increases accordingly.
[0030] When the injection angle is 90°, the second air flow is injected perpendicular to the direction of the first air flow. At this time, the momentum transfer efficiency of the second air flow to the first air flow is the highest. The second air flow can act on the first air flow with the greatest impact force, making the first air flow receive the greatest acting force in the vertical direction, thereby generating a relatively significant deflection.
[0031] When the injection angle is greater than 90° and less than or equal to 150°, the second air flow begins to impact the first air flow from the other side, and at this time, the interference of the second air flow on the first air flow is deeper. As the angle increases, the acting direction of the second air flow on the first air flow gradually becomes opposite to the original direction of the first air flow, enabling the first air flow to deflect to a greater extent.
[0032] Figure 2 Fig. shows one of the schematic diagrams of the deflection of the first air flow in the embodiment of the present application. Figure 3 Fig. shows another schematic diagram of the deflection of the first air flow in the embodiment of the present application. It should be understood that in order to more clearly show the gas flow direction in the expansion section, the gas flow directions in the switch and the flow channels in the converging section are omitted here. Exemplarily, as Figures 1 to 3 shown, the ratio of the cross-sectional area of the flexible auxiliary injection pipeline 301 to the cross-sectional area of the second air flow injection pipeline 302 in the embodiment of the present application is (0.6 - 1.6):1. Correspondingly, the ratio of the momentum of the gas flowing out of the flexible auxiliary injection pipeline 301 to the momentum of the gas flowing out of the second air flow injection pipeline 302 is (0.6 - 1.6):1, which is beneficial to controlling the impact degree of the second air flow and the auxiliary jet on the first air flow, and further changing the control of the deflection degree of the first air flow.
[0033] When the ratio of the cross-sectional area of the flexible auxiliary injection pipeline 301 to the cross-sectional area of the second air flow injection pipeline 302 is 0.6:1, the momentum of the auxiliary jet is only 0.6 times that of the second air flow, and the second air flow dominates when impacting the first air flow. The second air flow impacts the first air flow with a larger momentum, causing the first air flow to start deflecting to a certain extent in the acting direction of the second air flow.
[0034] When the ratio of the cross-sectional area of the flexible auxiliary injection pipeline 301 to the cross-sectional area of the second air flow injection pipeline 302 is 1:1, the momenta of the auxiliary jet and the second air flow are equal, and their impact on the first air flow is more balanced. At this time, the two air flows can work together more effectively, impacting the first air flow from different directions or positions, and the resultant force generated is more stable and has a wider acting range. This collaborative impact enables the first air flow to be uniformly acted upon in a larger area, thereby more significantly changing the direction of the first air flow, further increasing the deflection angle of the first air flow, and making the deflection process smoother.
[0035] When the ratio of the cross-sectional area of the flexible auxiliary jet pipeline 301 to the cross-sectional area of the second air flow jet pipeline 302 is 1.6:1, the momentum of the auxiliary jet is 1.6 times that of the second air flow. The auxiliary jet plays an absolute dominant role in the impact on the first air flow. The auxiliary jet exerts a strong force on the first air flow with a large momentum, enabling the first air flow to deflect significantly, and the deflection angle is significantly larger than the case when the second air flow is dominant. At this time, the second air flow mainly plays an auxiliary role, helping the auxiliary jet to further adjust the deflection direction of the first air flow, so that the first air flow can change direction more quickly and significantly to meet the requirements of some special working conditions that require large-angle air flow deflection.
[0036] In addition, the embodiment of the present application also limits the convergence ratio of the second air flow jet pipeline 302 to (1.26 - 4.33):1. Within this range, the outlet air flow velocity of the second air flow jet pipeline 302 increases with the increase of the convergence ratio, which is beneficial to realizing the precise control of the deflection direction of the first air flow. Preferably, the convergence ratio of the second air flow jet pipeline 302 is (3 - 4.33):1, and the effect of the second air flow on the first air flow is more significant, and the direction of the thrust vector can be adjusted more precisely.
[0037] Exemplarily, as Figures 1 to 3 shown, the distance between the other end of the second air flow jet pipeline 302 and the other end of the flexible auxiliary jet pipeline 301 in the embodiment of the present application is 2 to 8 times the maximum dimension of the second air flow jet pipeline 302 in the direction perpendicular to the flow direction in the flow direction of the first air flow. Within this range, the distance between the auxiliary jet and the second air flow can affect the length of the main separation zone of the first air flow and the pressure distribution on the pipeline wall surface between the auxiliary jet and the second air flow. By controlling the distance between the two, the length of the main separation zone of the first air flow and the pressure distribution on the pipeline wall surface can be changed.
[0038] When the distance is 2 times, the auxiliary jet and the second air flow are more likely to interfere and mix with each other. When they act on the first air flow together, the first air flow will be strongly disturbed, and the boundary layer is more likely to separate, which may lead to a relatively short length of the main separation zone of the first air flow. At the same time, in the wall surface area near the jet position, due to the combined impact of the auxiliary jet and the second air flow, the momentum of the two air flows is transferred to the pipeline wall surface in a relatively small space, resulting in an increase in the pressure on the pipeline wall surface, while in the area far from the jet position, the pressure may be relatively low, forming a large pressure gradient.
[0039] When the distance is 8 times, the combined disturbance effect of the auxiliary jet and the second air flow on the first air flow is relatively weakened, the separation process of the first air flow boundary layer is relatively lagged, and the length of the main separation zone will become longer. At the same time, on the entire wall surface, the pressure distribution may show a trend of gradually decaying from the jet position to the distance.
[0040] When the spacing is between 2 times and 8 times, the length of the main separation zone of the first air flow shows a continuous change trend from short to long. At the same time, as the spacing increases, the wall pressure distribution gradually transitions from a state of violent fluctuation and non-uniformity to a relatively uniform and stable state.
[0041] Figure 4 One of the cross-sectional views of the binary convergent section and the divergent section of the embodiment of the present application is shown. Figure 5 Another cross-sectional view of the binary convergent section and the divergent section of the embodiment of the present application is shown.
[0042] In an alternative manner, as Figures 1 to 5 shown, the convergent section 101 in the embodiment of the present application includes a circular-to-square convergent section 1011 and a binary convergent section 1012 connected to the circular-to-square convergent section 1011. Among them, the binary convergent section 1012 includes a first convergent wall plate 10121 symmetrically distributed along a first direction and a second convergent wall plate 10122 symmetrically distributed along a second direction. The first direction is perpendicular to the second direction. One end of the first convergent wall plate 10121 is rotatably connected to the circular-to-square convergent section 1011, and the other end of the first convergent wall plate 10121 is rotatably connected to the divergent section 102. One end of the second convergent wall plate 10122 is fixedly connected to the circular-to-square convergent section 1011, and the other end of the second convergent wall plate 10122 is fixedly connected to the divergent section 102. The outer side wall of the first convergent wall plate 10121 is rotatably connected to the adjustment assembly 2, and one end of the flexible auxiliary injection pipeline 301 is communicated with the fluid channel in the first convergent wall plate 10121.
[0043] During specific implementation, the first airflow generated by the engine first enters the circular-to-square converging section 1011. At this time, the airflow has a circular cross-section. The circular-to-square converging section 1011 begins to initially constrain and guide the first airflow, gradually transitioning the circular airflow into a square airflow. In the dual converging section 1012, the cross-sectional area of the channel gradually decreases, the velocity of the first airflow will gradually increase, and the pressure and temperature will correspondingly decrease, preliminarily accelerating the airflow and preparing for subsequent processes such as injection and vector control. When the adjustment component 2 rotates along the radial direction, a force will be exerted on the converging section. Since the adjustment component 2 is rotatably connected to the outer sidewall of the first converging wall plate 10121, this force will cause the first converging wall plate 10121 to rotate by a certain angle, and drive the diverging section 102 to also rotate, changing the throat, thereby achieving the purpose of adjustable cross-sectional area of the throat. During this process, under the adjustment of the switch 4, a second airflow with a smaller flow rate is introduced into the fluid channel communication of the diverging section 102 from the second airflow injection pipeline 302, strengthening the interference of the second airflow on the first airflow, increasing the deflection force of the first airflow, and causing it to deflect along the radial direction of the dual vector nozzle body 1, avoiding a greater impact on the performance of the aeroengine due to a large amount of extraction of the second airflow. The flexible auxiliary injection pipeline 301 can inject the first airflow from the fluid channel within the first converging wall plate 10121 into the fluid channel communication of the diverging section 102 to enhance the interference effect of the second airflow on the first airflow, further increasing the thrust vector angle and improving the thrust vector efficiency.
[0044] It can be understood that the end of the circular-to-square converging section 1011 away from the dual converging section 1012 in the embodiment of the present application is connected to the engine to play a role in supporting the converging section and other components.
[0045] Exemplarily, as Figures 1 to 5 shown, the ratio of the axial length of the circular-to-square converging section 1011 to the axial length of the dual converging section 1012 in the embodiment of the present application is (0.5 - 1.5):1. Within this range, the change range of the cross-sectional area of the throat can be controlled. When the ratio of the axial length of the circular-to-square converging section 1011 to the axial length of the dual converging section 1012 is 0.5:1, the throat will converge to a relatively small cross-sectional area. When the ratio of the axial length of the circular-to-square converging section 1011 to the axial length of the dual converging section 1012 is 1.5:1, the throat can maintain a relatively large cross-sectional area.
[0046] In an alternative manner, as Figures 1 to 5As shown in the figure, the expansion section 102 in the embodiment of the present application includes a first expansion wall panel 1021 symmetrically distributed along the first direction and a second expansion wall panel 1022 symmetrically distributed along the second direction. The first expansion wall panel 1021 is rotatably connected to the first converging wall panel 10121, and the second expansion wall panel 1022 is fixedly connected to the second converging wall panel 10122. Therefore, under the action of the adjustment assembly 2, the rotating first converging wall panel 10121 can drive the first expansion wall panel 1021 to rotate, so that the first airflow deflects in the first direction (i.e., deflects up and down). The other end of the flexible auxiliary injection pipeline 301 is communicated with the fluid channel in the first expansion wall panel 1021 to enhance the interference effect of the second airflow on the first airflow, further increase the thrust vector angle, and improve the thrust vector efficiency. At the same time, the flexible auxiliary injection pipeline 301 can adapt to the rotation of the first converging wall panel 10121 and the first expansion wall panel 1021 through its own contraction and stretching, thus perfectly solving the problem of difficult design of the high-efficiency pneumatic vector structure brought by throat control, and indirectly reducing the adverse impact on the common working of the aeroengine, ensuring that the engine can work well under different working conditions.
[0047] In an alternative manner, as Figures 1 to 4 shown, the ratio of the axial length of the expansion section in the embodiment of the present application to the axial length of the binary converging section 1012 is (0.5 - 2):1. At this time, the cross-sectional area of the throat and the maximum cross-sectional area of the expansion section (i.e., the cross-sectional area at the outlet of the expansion section) can be controlled.
[0048] As Figures 1 to 3 shown, the adjustment assembly 2 in the embodiment of the present application includes an actuating cylinder. The actuating end of the actuating cylinder includes a telescopic rod 201 and a triangular rocker arm 202. The telescopic rod 201 is rotatably connected to the outer side wall of the first converging wall panel 10121 through the triangular rocker arm 202. To more clearly show the connection relationship of the adjustment assembly 2, the actuating cylinder is omitted here. In practical applications, the fixed end of the actuating cylinder is rotatably connected to the aircraft skin, and the actuating end of the actuating cylinder controls the rotation positions of the first converging wall panel 10121 and the first expansion wall panel 1021 through telescoping, thereby changing the throat area and realizing the adjustable cross-sectional area of the throat. Specifically, the actuating cylinder controls the horizontal movement (i.e., telescoping back and forth) of the telescopic rod 201, so that the telescopic rod 201 drives the triangular rocker arm 202 to rotate, and then controls the rotation positions of the first converging wall panel 10121 and the first expansion wall panel 1021.
[0049] The present application also provides an aircraft, including the above binary vector nozzle, so as to have the performance of stealth, multi-condition working ability and pneumatic vector.
[0050] As described above, this is only the specific implementation manner of the present application. Obviously, various modifications and combinations can be made without departing from the spirit and scope of the present application. Accordingly, this specification and the accompanying drawings are merely exemplary descriptions of the present application defined by the appended claims, and are considered to cover any and all modifications, variations, combinations, or equivalents within the scope of the present application. Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the intention of the present application includes these changes and modifications. Any person skilled in the art within the technical scope disclosed in the present application can easily think of changes or substitutions, which should all be covered by the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the said claims.
[0051] It should also be noted that in the apparatus and method of the present application, each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations shall be regarded as equivalent solutions of the present application.
[0052] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present application. Various modifications to these aspects are very obvious to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of the present application. Therefore, the present application is not intended to be limited to the aspects shown herein, but rather to the broadest scope consistent with the principles and novel features disclosed herein.
[0053] The above description has been given for purposes of illustration and description. In addition, this description is not intended to limit the embodiments of the present application to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions, and sub - combinations thereof.
Claims
1. A binary vector nozzle, characterized in that, Comprising: A binary vector nozzle body, an adjustment component, an air flow injection component, and a switch; the binary vector nozzle body includes a converging section and a diverging section rotatably connected to the converging section, the converging section and the diverging section have a fluid passage for the first air flow to pass through, the adjustment component is rotatably connected to the outer side wall of the converging section, and the adjustment direction of the adjustment component is the radial direction of the binary vector nozzle body; the air flow injection component includes a flexible auxiliary injection pipeline and a second air flow injection pipeline, one end of the flexible auxiliary injection pipeline is communicated with the fluid passage of the converging section, the other end of the flexible auxiliary injection pipeline is communicated with the fluid passage of the diverging section, the switch is connected to one end of the second air flow injection pipeline, and the other end of the second air flow injection pipeline is communicated with the fluid passage of the diverging section.
2. The binary vector nozzle according to claim 1, characterized in that, The ratio of the cross-sectional area at the junction of the converging section and the diverging section to the cross-sectional area of the second air flow injection pipeline is 1:(0.04 - 0.15).
3. The binary vector nozzle according to claim 2, wherein, The injection angle of the second air flow injection pipeline is 40° - 150°.
4. The binary vector nozzle according to claim 3, wherein The ratio of the cross-sectional area of the flexible auxiliary injection pipeline to the cross-sectional area of the second air flow injection pipeline is (0.6 - 1.6):
1.
5. The binary vector nozzle according to claim 3, characterized in that, The distance between the other end of the second air flow injection pipeline and the other end of the flexible auxiliary injection pipeline is 2 to 8 times the maximum dimension of the second air flow injection pipeline in the direction perpendicular to the flow direction in the flow direction of the first air flow.
6. The dual vector nozzle according to any one of claims 1 to 5, characterized in that, The converging section includes a circular-to-square converging section and a binary converging section; the binary converging section includes a first converging wall plate symmetrically distributed along a first direction and a second converging wall plate symmetrically distributed along a second direction, the first direction is perpendicular to the second direction, one end of the first converging wall plate is rotatably connected to the circular-to-square converging section, the other end of the first converging wall plate is rotatably connected to the diverging section, one end of the second converging wall plate is fixedly connected to the circular-to-square converging section, the other end of the second converging wall plate is fixedly connected to the diverging section, the outer side wall of the first converging wall plate is rotatably connected to the adjustment component, and one end of the flexible auxiliary injection pipeline is communicated with the fluid passage inside the first converging wall plate.
7. The binary vector nozzle according to claim 6, characterized in that, The ratio of the axial length of the circular-to-square converging section to the axial length of the binary converging section is (0.5 - 1.5):
1.
8. The binary vector nozzle according to claim 6, characterized in that, The diverging section includes a first diverging wall plate symmetrically distributed along a first direction and a second diverging wall plate symmetrically distributed along a second direction, the first diverging wall plate is rotatably connected to the first converging wall plate, the second diverging wall plate is fixedly connected to the second converging wall plate, and the other end of the flexible auxiliary injection pipeline is communicated with the fluid passage inside the first diverging wall plate.
9. The binary vector nozzle according to claim 6, characterized in that The ratio of the axial length of the diverging section to the axial length of the binary converging section is (0.5 - 2):
1.
10. An aircraft, characterized in that, Comprising: The binary vector nozzle according to any one of claims 1 to 9.