A vector nozzle and an aeroengine

Abstract

The present disclosure relates to the technical field of aeroengines, and in particular, provides a vector nozzle and an aeroengine. The vector nozzle includes a conical barrel and a converging mechanism; it further includes a first control mechanism and a plurality of first adjustment components; a plurality of hinge points distributed along the circumference are formed at one end of the converging mechanism away from the conical barrel; the plurality of first adjustment components correspond to the hinge points one by one, and the plurality of first adjustment components are sequentially attached along the circumferential direction to form a cylindrical expansion section; the first control mechanism includes a first control ring and a first control component; one end of the first control component is connected to the conical barrel, and the other end is connected to the first control ring; the first control ring is slidably connected to the first adjustment component, and when the first control ring moves along the center line direction of the conical barrel, it can drive each first adjustment component to deflect and form a structure with an elliptical cross-section. It can achieve the transformation from circular to elliptical, which not only improves the stealth performance but also retains the characteristics of vector deflection, and can greatly improve the survival probability of fighter jets in the battlefield.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aero-engines, and in particular to a vector nozzle and an aero-engine. Background Art

[0002] The thrust vector nozzle is the core component for realizing thrust vector control, and vector deflection is achieved by controlling the deflection direction of the vector nozzle. In the battlefield environment, in order to increase the survival probability of the aircraft, improving the maneuverability and stealth performance of high-performance thrust vector engines is the main trend of future fighter development.

[0003] How to improve stealth performance while ensuring the omnidirectional vector deflection advantage of symmetrical vectors is one of the important issues that need to be urgently solved in this field. Summary of the invention

[0004] The present disclosure is proposed in view of the above problems. The present disclosure provides a vector nozzle and an aircraft engine.

[0005] According to one aspect of the present disclosure, a vector nozzle is provided, comprising a cone and a convergence mechanism disposed at the cone outlet; wherein the first control mechanism and a plurality of first adjustment components are also included;

[0006] The convergence mechanism is formed with a plurality of hinge points distributed along the circumference at one end away from the cone; the plurality of first adjustment components correspond to the hinge points one by one, and the plurality of first adjustment components are sequentially fitted together along the circumferential direction to form a cylindrical expansion section;

[0007] The first control mechanism includes a first control ring and a first control component; one end of the first control component is connected to the cone, and the other end is connected to the first control ring; the first control component can push the first control ring to move along the center line of the cone;

[0008] The first control ring is connected with the first adjustment component in a sliding cooperation manner. When the first control ring moves along the center line direction of the cone, it can drive each of the first adjustment components to deflect and form a structure with an elliptical cross section.

[0009] The vector nozzle as described above, wherein, optionally, the first adjustment component includes a first adjustment rod and first sealing sheets arranged on both sides of the first adjustment rod;

[0010] One end of the first adjusting rod is hinged to the convergence mechanism at the hinge point, and the first sealing sheets on two adjacent first adjusting rods are slidably attached;

[0011] The first adjusting rod is provided with a slide groove along the length direction, and the width of the bottom of the slide groove is greater than the width of the notch of the slide groove;

[0012] A sliding rod is provided on the first control ring, and a slider adapted to the sliding groove is provided at one end of the sliding rod away from the first control ring.

[0013] For the vector nozzle as described above, optionally, the sliding groove includes a first groove section and a second groove section;

[0014] The first groove section is arranged along the length direction of the first adjusting rod;

[0015] The second groove section is inclined in the radial direction of the first control ring along the length direction of the first adjusting rod; a smooth transition is provided between the first groove section and the second groove section;

[0016] Along the circumferential direction of the first control ring, the second groove sections on multiple first adjusting rods correspond to multiple inclination angles.

[0017] For the vector nozzle as described above, optionally, the inclination angles of the second groove sections on any two first adjusting rods symmetrically arranged with respect to the first plane are equal; wherein, the first plane is a plane parallel to the wing of the aircraft where the vector nozzle is located and passing through the center line of the first control ring;

[0018] Along the circumferential direction of the first control ring, from the first adjusting rod with the center line located on the first plane to the first adjusting rod with the center line located on the second plane, the inclination angles of the second groove sections on each first adjusting rod increase in sequence;

[0019] Wherein, the second plane is a plane perpendicular to the wing of the aircraft where the vector nozzle is located and passing through the center line of the first control ring.

[0020] For the vector nozzle as described above, optionally, there are multiple first control components, which are evenly distributed along the circumferential direction of the conical cylinder;

[0021] The first control component includes a first push rod, a first support rod, a second support rod, and two first link rods;

[0022] The first push rod is slidably connected to the conical cylinder, and the first push rod can move in a direction close to or away from the conical cylinder;

[0023] One end of the first support rod is fixed to the first push rod; the second support rod is fixedly connected to the first control ring;

[0024] Two ends of the first support rod are respectively ball-jointed to the first ends of the two first link rods, and two ends of the second support rod are respectively ball-jointed to the second ends of the two first link rods to form a parallelogram structure.

[0025] The vector nozzle as described above, wherein, optionally, the number of the first control components is at least three; and a plurality of the first control components are evenly distributed in the direction of the central axis of the conical barrel.

[0026] The vector nozzle as described above, wherein, optionally, the converging mechanism includes a second control component, a second control ring and a plurality of second adjusting components;

[0027] One end of the second adjusting component is hinged to the conical barrel, and the other end is provided with the hinge point; a plurality of the second adjusting components are distributed along the circumferential direction of the conical barrel;

[0028] The second control component includes a second push rod, a second connecting rod and a fixing rod;

[0029] One end of the second push rod is slidably connected to the conical barrel, and the sliding direction is parallel to the axis of the conical barrel;

[0030] One end of the fixing rod is connected to the second adjusting component;

[0031] Two ends of the second connecting rod are respectively hinged to one end of the fixing rod away from the second adjusting component and the second control ring.

[0032] The vector nozzle as described above, wherein, optionally, the second adjusting component includes a second adjusting rod and second sealing sheets arranged on both sides of the second adjusting rod;

[0033] One end of the second adjusting rod is hinged to the conical barrel, and the hinge point is arranged at one end of the second adjusting rod away from the conical barrel; one end of the fixing rod away from the second connecting rod is fixedly installed on the second adjusting rod;

[0034] The second sealing sheet on any one of the second adjusting rods is in sliding fit with one of the second sealing sheets on an adjacent second adjusting rod.

[0035] The vector nozzle as described above, wherein, optionally, the number of the second control components is plural, and a plurality of the second control components are evenly distributed in the circumferential direction of the conical barrel.

[0036] According to another aspect of the present disclosure, an aeroengine is further provided, which includes the vector nozzle described in any one of the above.

[0037] As will be described in detail below, the vector nozzle and aeroengine according to the embodiments of the present disclosure form an expansion section at the rear of the convergence mechanism. The expansion section is surrounded by a plurality of first adjustment components. Through the first control mechanism, the first adjustment components can be enabled to achieve changes in the cross-sectional shape and changes in the direction of the vector nozzle. In particular, the vector nozzle proposed by the present disclosure can achieve a circular-to-elliptical transition, which not only improves the stealth performance but also retains the characteristics of vector deflection, and can greatly improve the survival probability of fighter jets on the battlefield.

[0038] 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

[0039] By describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings, the above and other objects, features, and advantages of the present disclosure will become more apparent. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0040] Figure 1 is a perspective view of the vector nozzle proposed by the present disclosure;

[0041] Figure 2 is a perspective view of a partial structure of the vector nozzle proposed by the present disclosure;

[0042] Figure 3 is a partial schematic view of the vector nozzle proposed by the present disclosure when the expansion section is in a cylindrical structure;

[0043] Figure 4 is a partial structural schematic view of the vector nozzle proposed by the present disclosure when the expansion section is in an expanded state;

[0044] Figure 5 is a partial structural schematic view of the vector nozzle proposed by the present disclosure when the expansion section deflects in one direction;

[0045] Figure 6 is a partial structural schematic view of the vector nozzle proposed by the present disclosure when the expansion section deflects in the other direction;

[0046] Figure 7 is a schematic view of the vector nozzle proposed by the present disclosure when the expansion section is in a straight cylindrical structure;

[0047] Figure 8 is Figure 7 the right view of;

[0048] Figure 9It is a schematic diagram when the cross-sectional shape of the vector nozzle proposed by the present disclosure is an elliptical structure;

[0049] Figure 10 is Figure 9 the right view of;

[0050] Figure 11 It is a schematic diagram of the change in the inclination angle of the second groove section proposed by the present disclosure.

[0051] Explanation of reference numerals:

[0052] 1 - Cone barrel, 2 - Converging mechanism, 3 - Diverging section;

[0053] 21 - Hinge point, 22 - Second control assembly, 23 - Second control ring, 24 - Second adjustment assembly;

[0054] 221 - Second push rod, 222 - Second connecting rod, 223 - Fixed rod;

[0055] 241 - Second adjustment rod, 242 - Second sealing sheet;

[0056] 31 - First control mechanism, 32 - First adjustment assembly;

[0057] 311 - First control ring, 312 - First control assembly;

[0058] 3111 - Slide rod, 3112 - Slide block;

[0059] 3121 - First push rod, 3122 - First support rod, 3123 - Second support rod, 3124 - First connecting rod;

[0060] 321 - First adjustment rod, 322 - First sealing sheet, 323 - Pressing sheet;

[0061] 3211 - Slide groove, 3212 - First groove section, 3213 - Second groove section. Detailed implementation manners

[0062] In order to make the objectives, technical solutions, and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure 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 disclosure, rather than all the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0063] Please refer to Figures 1 to 9, the present disclosure provides a vector nozzle, including a conical barrel 1 and a converging mechanism 2 disposed at the outlet of the conical barrel 1; wherein, it further includes a first control mechanism 31 and a plurality of first adjustment components 32; in specific implementation, the converging mechanism 2 is used to form a constricted shape from front to back, that is, to form a converging section. An expanding section 3 is formed behind the converging mechanism 2. The first control mechanism 31 is used to control the first adjustment components 32 so that the expanding section 3 formed by the plurality of first adjustment components 32 can deflect and be converted from a circular cross-section to an elliptical cross-section. In specific implementation, the conical barrel 1 is a steel conical barrel.

[0064] Please refer to Figure 1 and Figure 2 , specifically, a plurality of circumferentially distributed hinge points 21 are formed at one end of the converging mechanism 2 away from the conical barrel 1; in some embodiments, the hinge center lines of the plurality of hinge points 21 are distributed along the tangent direction of the circle where the plurality of hinge points 21 are located at this point. The plurality of first adjustment components 32 correspond to the hinge points 21 one by one, and the plurality of first adjustment components 32 are sequentially attached along the circumferential direction to form a cylindrical expanding section 3. The first adjustment component 32 can rotate around the hinge center line corresponding to each hinge point 21, so that the first adjustment component 32 can tilt in a direction close to or away from the center line of the conical barrel 1, so as to facilitate the formation of a deflected or cross-sectional shape-changing expanding section by the first adjustment component 32.

[0065] In order to conveniently control the first adjustment components 32, in some embodiments, please refer to Figure 1 , the first control mechanism 31 includes a first control ring 311 and a first control component 312; one end of the first control component 312 is connected to the conical barrel 1, and the other end is connected to the first control ring 311. The first control component 312 can push the first control ring 311 to move along the center line direction of the conical barrel 1. The first control ring 311 is slidably connected with the first adjustment components 32. When the first control ring 311 moves along the center line direction of the conical barrel 1, it can drive each first adjustment component 32 to deflect and form a structure with an elliptical cross-section. In specific implementation, by controlling the first control ring 311 to drive each first adjustment component 32 to deflect to different degrees, a shape with an elliptical cross-section is formed at the position of the first control ring 311. In this way, a complex deflection control mechanism can be simplified, and the reliability of the system is increased.

[0066] By transforming the vector nozzle from circular to elliptical, the shielding of some high-temperature components can be achieved, and the mixing of the external airflow and the high-temperature mainstream can be enhanced to a certain extent, reducing the temperature length of the mainstream core area, reducing the infrared radiation signal of the rearward jet, and achieving infrared stealth. At the same time, the elliptical outlet section can achieve shielding during the reflection of the radar signal, thereby weakening the reception rate of the radar signal and achieving radar stealth. Compared with the conventional circular-to-rectangular nozzle, the circular-to-elliptical nozzle has good structural performance and does not have the disadvantage of high stress at the corner of the circular-to-rectangular nozzle. The smooth structure also improves the aerodynamic performance of the nozzle.

[0067] In order to enable multiple first adjustment components 32 to enclose the divergent section and be able to adapt to deflections at different angles and changes in cross-sectional shapes, in some implementation manners, please refer to Figures 1 to 4 , the first adjustment component 32 includes a first adjustment rod 321 and first sealing sheets 322 disposed on both sides of the first adjustment rod 321. Two first sealing sheets 322 are respectively and fixedly disposed on both sides of each first adjustment rod 321. The first sealing sheets 322 are strip-shaped, and one edge in the length direction of the first sealing sheet 322 is fixedly connected to the first adjustment rod 321. The divergent section 3 is enclosed by the first sealing sheets 322. When the cross-sectional size of the divergent section 3 changes, the first sealing sheets 322 can automatically adapt to different cross-sectional dimensions, improving the sealing performance of the nozzle.

[0068] One end of the first adjustment rod 321 is hinged to the converging mechanism 2 at the hinge point 21. Please refer to Figure 1 and Figure 2 , in specific implementation, the number of the first adjustment rods 321 is equal to the number of the hinge points 21 and they correspond one by one. The first sealing sheets 322 on two adjacent first adjustment rods 321 are in sliding fit. That is, between two adjacent first adjustment rods 321, there are two first sealing sheets 322. The two first sealing sheets 322 are respectively fixed on the two first adjustment rods 321, and the two first sealing sheets 322 are in sliding fit. That is, one of the first sealing sheets 322 abuts against the other first sealing sheet 322. When the relative position between the two first adjustment rods 321 changes, the two first sealing sheets 322 slide relative to each other, and the two first sealing sheets 322 remain in contact during the sliding process. In specific implementation, in order to ensure the sealing effect of the first sealing sheets 322, a pressing sheet 323 is further provided on the first adjustment rod 321. The pressing sheet 323 is used to press the two first sealing sheets 322 so that the two first sealing sheets 322 are pressed tightly.

[0069] To facilitate the control of the deflection angle of the first adjusting rod 321, that is, it is necessary to ensure that the first adjusting rod 321 can be deflected towards the center line of the conical cylinder 1 and also ensure that the first adjusting rod 321 can be deflected away from the center line of the conical cylinder 1. For this purpose, in some embodiments, the following improvements are also made. Please refer to Figure 11 , a sliding groove 3211 is provided along the length direction of the first adjusting rod 321, and the width of the bottom in the sliding groove 3211 is greater than the width of the notch of the sliding groove 3211. For example, the sliding groove 3211 can be a T-shaped groove or a dovetail groove. In some implementation manners, it can also be set in other ways as long as the slider can be prevented from falling off the sliding groove 3211 during the sliding process. A sliding rod 3111 is provided on the first control ring 311, and a slider 3112 adapted to the sliding groove 3211 is provided at one end of the sliding rod 3111 away from the first control ring 311. In some implementation manners, the slider 3112 can also be set as a ball head structure, and the sliding groove 3211 is set in a shape adapted to the ball head structure. In this way, when the slider 3112 slides in the sliding groove 3211, a component force acting radially inward or radially outward along the conical cylinder 1 can be applied to the first adjusting rod 321, so as to facilitate the precise control of the first adjusting rod 321. In specific implementation, the sliding rod 3111 is arranged on the inner wall of the first control ring 311, and the number of the sliding rods 3111 is equal to and corresponds to the number of the first control rings 311 one by one. The sliding rod 3111 is arranged radially along the first control ring 311.

[0070] To achieve the control of the variable cross-section, it is necessary to control the deflection of the first adjusting assembly 32 to different degrees to achieve the purpose of changing the cross-sectional shape. Please refer to Figure 11 , in some implementation manners, the sliding groove 3211 includes a first groove section 3212 and a second groove section 3213. The function of the first groove section 3212 is to achieve differential control of different first adjusting rods 321 when the slider 3112 slides therein, that is, when the first control ring 311 moves along the axis direction of the conical cylinder 1 without radial offset, the deflection angles of the first adjusting rods 321 at different positions are different. The first groove section 3212 is arranged along the length direction of the first adjusting rod 321. That is, if the first control ring 311 moves along the axis direction of the conical cylinder 1 without radial offset, the deflection angles of the plurality of first adjusting rods 321 are the same.

[0071] The second groove section 3213 is inclined in the radial direction of the first control ring 311 along the length direction of the first adjusting rod 321; a smooth transition is made between the first groove section 3212 and the second groove section 3213. In this way, the slider 3112 can smoothly transition between the first groove section 3212 and the second groove section 3213.

[0072] In the circumferential direction of the first control ring 311, the second groove segments 3213 on multiple first adjusting rods 321 correspond to multiple inclination angles. Specifically, the types of inclination angles are determined according to the actual situation. Taking the transformation from a circle to an ellipse as an example, when the number of first adjusting rods 321 is 24 and they are evenly distributed along the circumferential direction, there should be 7 kinds of inclination angles. Between the maximum inclination angle and the minimum inclination angle, the inclination angles of the second groove segments 3213 on the corresponding first adjusting rods 321 should increase or decrease in sequence.

[0073] In some implementation manners, in order to form a structure for transforming a circle into an ellipse, especially to form a flat opening structure on a vector nozzle, that is, the major axis of the corresponding ellipse is parallel to the plane where the aircraft wing is located, and the minor axis is perpendicular to the plane where the aircraft wing is located, so as to achieve the best infrared stealth and radar stealth effects. In some implementation manners, the inclination angles of the second groove segments 3213 on any two first adjusting rods 321 symmetrically arranged with respect to the first plane are equal; wherein, the first plane is a plane parallel to the wing of the aircraft where the vector nozzle is located and passing through the center line of the first control ring 311.

[0074] Please refer to Figure 11 , along the circumferential direction of the first control ring 311, from the first adjusting rod 321 whose center line is located on the first plane to the first adjusting rod 321 whose center line is located on the second plane, the inclination angles of the second groove segments 3213 on each first adjusting rod 321 increase in sequence, as shown in Figure 11 , the inclination angles of the second groove segments 3213 on the first adjusting rods 321 between 0 degrees and 90 degrees gradually increase. And the change of the inclination angle of the second groove segment 3213 is preferably a uniform change. Wherein, the second plane is a plane perpendicular to the wing of the aircraft where the vector nozzle is located and passing through the center line of the first control ring 311.

[0075] In some implementation manners, in order to facilitate the control of the movement of the first control ring 311, and further realize the control of the transformation of the vector nozzle from a circle to an ellipse and the deflection of the vector nozzle, there are multiple first control components 312, and they are evenly distributed along the circumferential direction of the conical cylinder 1. In some implementation manners, the number of the first control components 312 is at least three, and in some implementation manners, three are preferred.

[0076] Please refer to Figures 1 to 7 , in order to conveniently control the first control ring 311, the first control component 312 includes a first push rod 3121, a first support rod 3122, a second support rod 3123 and two first connecting rods 3124. Specifically, the first push rod 3121 is slidably connected to the conical cylinder 1, and the first push rod 3121 can move along the direction close to or away from the conical cylinder 1.

[0077] The first support rod 3122 is fixed to one end of the first push rod 3121; the second support rod 3123 is fixedly connected to the first control ring 311. In specific implementation, the lengths of the first support rod 3122 and the second support rod 3123 are equal. The two ends of the first support rod 3122 are respectively ball-jointed to the first ends of the two first connecting rods 3124, and the two ends of the second support rod 3123 are respectively ball-jointed to the second ends of the two first connecting rods 3124 to form a parallelogram structure.

[0078] The centerlines of all the first support rods 3122 are in the same plane, and the plane where the centerlines of the multiple first support rods 3122 are located is perpendicular to the centerline of the first control ring 311. The centerlines of all the second support rods 3123 are in the same plane, and the plane where the centerlines of the multiple second support rods 3123 are located is perpendicular to the centerline of the first control ring 311.

[0079] For each parallelogram structure, the centerline of the first support rod 3122 thereon is always parallel to the centerline of the second support rod 3123. During the movement of the first control assembly 312, it can be ensured that the planes where the multiple first support rods 3122 are located are always parallel to the planes where the multiple second support rods 3123 are located, that is, the first control ring 311 is kept in translation. When the pushing distances of the multiple first push rods 3121 are different, the first control ring 311 will deflect in the radial direction, so as to achieve the purpose of changing the direction of the vector nozzle.

[0080] Please refer to Figure 1 、 Figure 2 、 Figure 8 、 Figure 10 and Figure 11 In specific implementation, the number of the first control assemblies 312 is at least three; and the multiple first control assemblies 312 are evenly distributed around the centerline direction of the conical barrel 1. By arranging the multiple first control assemblies 312, the complexity of control can be reduced while ensuring the accurate control of the first control ring 311. By driving the first control ring 311 to achieve the deflection of the divergent section 3, the roundness and smoothness of the connection between the convergent section and the divergent section 3 can be better ensured, and the loss of the thrust of the jet engine can be reduced.

[0081] In specific implementation, the converging mechanism 2 includes a second control assembly 22, a second control ring 23 and a plurality of second adjusting assemblies 24. Through the converging mechanism 2, the radius of the circle where the hinge point 21 is located can be changed to adjust the radial dimension of the divergent section.

[0082] Specifically, one end of the second adjusting assembly 24 is hinged to the conical barrel 1, and the other end is provided with a hinge point 21; the multiple second adjusting assemblies 24 are evenly distributed along the circumferential direction of the conical barrel 1. In specific implementation, the number of the second adjusting assemblies 24 is equal to the number of the first adjusting assemblies 32.

[0083] Please refer to Figures 1 to 7 , the second control component 22 includes a second push rod 221, a second connecting rod 222 and a fixed rod 223. The function of the second control component 22 is to control the contraction degree of the converging section. Specifically, the contraction degree of the converging section is achieved by controlling the position of the second control ring 23. When the contraction degree of the converging section is different, the radius of the circle where the corresponding hinge point 21 is located is different. By setting the second control component 22, it is convenient to realize the size of the front end of the expansion section, so as to realize the adjustment of the shape and size of the entire vector nozzle. Specifically, one end of the second push rod 221 is slidably connected to the conical cylinder 1, and the sliding direction is parallel to the axis of the conical cylinder 1; by controlling the sliding of the second push rod 221, the movement of the second control ring 23 can be controlled. In practical applications, the second control ring 23 can reciprocate along the axis direction of the conical cylinder 1. One end of the fixed rod 223 is connected to the second adjustment component 24; both ends of the second connecting rod 222 are respectively hinged to one end of the fixed rod 223 away from the second adjustment component 24 and the second control ring 23. In this way, the rotation of the second adjustment component 24 around the hinge center line with the conical cylinder 1 is realized through the movement of the second control ring 23.

[0084] In specific implementation, the number of the second control components 22 can be at least three. Taking three as an example, the three second control components 22 are evenly distributed along the circumferential direction of the conical cylinder 1. Specifically, the second control components 22 can be arranged at intervals with the first control component 312.

[0085] Please refer to Figure 2 , in specific implementation, in order to enclose the second adjustment component 24 into a sealed cylindrical structure, the second adjustment component 24 includes a second adjustment rod 241 and second sealing sheets 242 arranged on both sides of the second adjustment rod 241. Specifically, one end of the second adjustment rod 241 is hinged to the conical cylinder 1, and the hinge point 21 is arranged at the end of the second adjustment rod 241 away from the conical cylinder 1; the end of the fixed rod 223 away from the second connecting rod 222 is fixedly installed on the second adjustment rod 241. When the cross-sectional size of the converging section changes, the second sealing sheets 242 can automatically adapt to different cross-sectional sizes, improving the sealing performance of the nozzle.

[0086] One second sealing sheet 242 on any second adjustment rod 241 is slidably attached to one second sealing sheet 242 on the adjacent second adjustment rod 241. Specifically, one second sealing sheet 242 is arranged on each side of each second adjustment rod 241. The second sealing sheet 242 is strip-shaped, and one side edge of the second sealing sheet 242 is fixedly connected to the second adjustment rod 241. The two second sealing sheets 242 between adjacent two second adjustment rods 241 are attached to each other.

[0087] In specific implementation, in order to avoid possible interference during the adjustment process, a cross shaft connection is adopted at the hinge point 21. The first adjustment rod 321 and the second adjustment rod 241 are respectively rotationally connected to two shafts of the cross shaft. The rotation center line of the cross shaft and the second adjustment rod 241 forms an angle of 50 to 70 degrees with the center line of the second adjustment rod 241, and preferably 60 degrees.

[0088] Through the vector nozzle proposed by the present disclosure, by controlling the synchronous movement of a plurality of second push rods 221 along the axis direction of the cone barrel 1, the second control ring 23 can be driven to translate along the axis direction of the cone barrel 1. When the second control ring 23 moves, the second link 222 is driven to act, and further causes the second adjustment assembly 24 to deflect around its hinge point with the cone barrel 1, thereby changing the contraction degree of the convergent section. Specifically, when a plurality of second control rings 23 move away from the cone barrel 1, the contraction degree of the convergent section increases. The radius of the circle where the hinge point 21 is located becomes smaller. Please refer to Figure 3 When the contraction degree of the convergent section is changed by adjusting the second push rod 221, and the radius of the circle where the hinge point 21 is located is equal to the diameter of the circle where a plurality of sliders 3112 are located. If the sliders are all in the first groove section 3212, at this time, as Figure 3 and Figure 7 shown, the expansion section 3 is basically a cylindrical structure. If in Figure 3 and Figure 7 shown state, the second push rod 221 is adjusted to make the convergent section continue to contract, and the first control mechanism 31 remains unchanged. At this time, the first adjustment assembly 32 deflects, and the expansion section 3 forms a flared structure, as Figure 4 shown. If in Figure 3 and Figure 7 shown state, the second push rod 221 remains unchanged, and each first push rod 3121 is controlled according to different elongation lengths. Since the first support rod 3122, the second support rod 3123 and the two first link rods 3124 form a parallelogram structure with a spherical hinge at the vertex, the common action of a plurality of first control assemblies 312 can make the center line of the first control ring 311 always parallel to the center line of the cone barrel 1. When the lengths of a plurality of first push rods 3121 are different, the first control ring 311 deflects in a plane perpendicular to the center line of the cone barrel 1. At this time, if all the sliders 3112 are located in the first groove section 3212, the expansion section 3 is still cylindrical, but only the direction has changed, which can simplify the complex deflection control mechanism and increase the reliability of the system; if all the sliders 3112 are located in the second groove section 3213, the expansion section 3 is converted into an elliptical cross section.

[0089] In Figure 3 、 Figure 7 and Figure 8In the state shown in the figure, while keeping the length of the second push rod 221 unchanged, if the lengths of all the first push rods 3121 are controlled to be equal, and all the sliders 3112 are located within the corresponding second groove segments 3213, at this time, the deflection angles of the first control components 312 at different positions are different, thereby realizing the conversion of the expansion section 3 into an elliptical cross-section, as Figure 9 and Figure 10 shown. The present disclosure realizes the combination of a vector nozzle and an elliptical nozzle, which not only ensures the flexibility of the nozzle, but also improves the stealth performance of the nozzle. The structure is also sufficiently streamlined, reducing the weight of the nozzle while ensuring reliability.

[0090] It should be noted that for the control of the convergent section and the expansion section 3, there is a certain coupling. Only by adjusting the movement length of the second push rod 221 can the diameters of the convergent section and the expansion section 3 be adjusted simultaneously, reducing the control difficulty. At the same time, the first control ring 311 can also independently control the size of the expansion section 3, and can make a more precise adjustment of the cross-sectional diameter of the expansion section 3.

[0091] The present disclosure proposes an aeroengine including the vector nozzle proposed by the present disclosure.

[0092] It should be noted that the circles and circular shapes referred to in the present disclosure are not absolute circles or circular shapes, but are approximately circular; the ellipses and elliptical shapes referred to in the present disclosure are not absolute ellipses or elliptical shapes, but are approximately elliptical. As long as the deviation of any point is not greater than the set value, it can be considered to conform to the circles or ellipses referred to in the present disclosure.

[0093] The basic principles of the present disclosure have been described above in combination with specific embodiments. However, it should be noted that the advantages, advantages, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, advantages, effects, etc. are essential for each embodiment of the present disclosure. In addition, the above-mentioned specific details are only for the purpose of illustration and easy understanding, rather than limitations. The above details do not limit the present disclosure to necessarily adopt the above specific details to implement.

[0094] The block diagrams of the devices, apparatuses, equipment, and systems involved in the present disclosure are only illustrative examples and do not intend to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open-ended words, meaning "including but not limited to", and can be used interchangeably with each other. The words "or" and "and" used here refer to the word "and / or", and can be used interchangeably with each other unless the context clearly indicates otherwise. The word "such as" used here refers to the phrase "such as but not limited to", and can be used interchangeably with each other.

[0095] In addition, as used herein, "or" as used in a list of items beginning with "at least one" indicates a disjunctive list such that, for example, a listing of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Further, the phrase "exemplary" does not mean that the examples described are preferred or better than other examples.

[0096] It should also be noted that in the systems and methods of the present disclosure, the various components or steps can be decomposed and / or recombined. Such decompositions and / or recombinations should be regarded as equivalent solutions of the present disclosure.

[0097] Various changes, substitutions, and alterations to the techniques described herein can be made without departing from the teachings of the technology defined by the appended claims. In addition, the scope of the claims of the present disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and acts described above. Processes, machines, manufactures, compositions of events, means, methods, or acts that are currently available or later to be developed that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Accordingly, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or acts within their scope.

[0098] The foregoing description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent 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 disclosure. Thus, the present disclosure is not intended to be limited to the aspects shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0099] The foregoing description has been presented for purposes of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although numerous example aspects and embodiments have been discussed above, those skilled in the art will recognize some of their variations, modifications, alterations, additions, and subcombinations.

Claims

1. A vector nozzle, comprising a cone (1) and a convergence mechanism (2) arranged at the outlet of the cone (1); characterized in that: It also includes a first control mechanism (31) and a plurality of first adjustment components (32); The end of the convergence mechanism (2) away from the cone (1) is formed with a plurality of hinge points (21) distributed along the circumference; the plurality of first adjustment components (32) correspond to the hinge points (21) one by one, and the plurality of first adjustment components (32) are sequentially fitted together along the circumferential direction to form a cylindrical expansion section (3); The first control mechanism (31) comprises a first control ring (311) and a first control component (312); one end of the first control component (312) is connected to the cone (1), and the other end is connected to the first control ring (311); the first control component (312) is capable of pushing the first control ring (311) to move in the direction of the center line of the cone (1); The first control ring (311) is connected to the first adjustment component (32) in a sliding manner, and the first control ring (311) can drive each of the first adjustment components (32) to deflect when moving along the center line direction of the cone (1), thereby forming a structure with an elliptical cross-section; The first adjustment component (32) comprises a first adjustment rod (321) and first sealing sheets (322) arranged on both sides of the first adjustment rod (321); One end of the first adjustment rod (321) is hinged to the convergence mechanism (2) at the hinge point (21), and the first sealing sheets (322) on two adjacent first adjustment rods (321) are slidably fitted; The first adjusting rod (321) is provided with a sliding groove (3211) along the length direction, and the width of the bottom of the sliding groove (3211) is greater than the width of the notch of the sliding groove (3211); A sliding rod (3111) is provided on the first control ring (311), and a sliding block (3112) adapted to the sliding groove (3211) is provided at one end of the sliding rod (3111) away from the first control ring (311); The slide groove (3211) comprises a first groove section (3212) and a second groove section (3213); The first groove section (3212) is arranged along the length direction of the first adjustment rod (321); The second groove section (3213) is inclined along the length direction of the first adjustment rod (321) and in the radial direction of the first control ring (311); and there is a smooth transition between the first groove section (3212) and the second groove section (3213); Along the circumferential direction of the first control ring (311), the second slot sections (3213) on the plurality of first adjustment rods (321) correspond to a plurality of inclination angles.

2. The vector nozzle according to claim 1, characterized in that: The inclination angles of the second slot sections (3213) on any two of the first adjustment rods (321) symmetrically arranged about a first plane are equal; wherein the first plane is a plane parallel to the wing of the aircraft on which the vector nozzle is located and passes through the center line of the first control ring (311); Along the circumferential direction of the first control ring (311), from the first adjustment rod (321) whose center line is located on the first plane to the first adjustment rod (321) whose center line is located on the second plane, the inclination angles of the second groove sections (3213) on each of the first adjustment rods (321) gradually increase; The second plane is a plane perpendicular to the wing of the aircraft on which the vector nozzle is located and passes through the center line of the first control ring (311).

3. The vector nozzle according to claim 1, characterized in that: There are a plurality of first control components (312), which are evenly distributed along the circumferential direction of the cone (1); The first control assembly (312) comprises a first push rod (3121), a first support rod (3122), a second support rod (3123) and two first connecting rods (3124); The first push rod (3121) is slidably connected to the cone cylinder (1), and the first push rod (3121) is capable of moving in a direction approaching or moving away from the cone cylinder (1); The first support rod (3122) is fixed to one end of the first push rod (3121); the second support rod (3123) is fixedly connected to the first control ring (311); The two ends of the first support rod (3122) are respectively hinged to the first end balls of the two first connecting rods (3124), and the two ends of the second support rod (3123) are respectively hinged to the second end balls of the two first connecting rods (3124), so as to form a parallelogram structure.

4. The vector nozzle according to claim 3, characterized in that: The number of the first control components (312) is at least three; and the plurality of first control components (312) are evenly distributed around the center line direction of the cone (1).

5. The vector nozzle according to claim 1, characterized in that: The convergence mechanism (2) comprises a second control component (22), a second control ring (23) and a plurality of second adjustment components (24); One end of the second adjustment component (24) is hinged to the cone (1), and the other end is provided with the hinge point (21); a plurality of the second adjustment components (24) are distributed along the circumference of the cone (1); The second control assembly (22) comprises a second push rod (221), a second connecting rod (222) and a fixing rod (223); One end of the second push rod (221) is slidably connected to the cone cylinder (1), and the sliding direction is parallel to the axis of the cone cylinder (1); One end of the fixing rod (223) is connected to the second adjustment assembly (24); Both ends of the second connecting rod (222) are respectively hinged to one end of the fixing rod (223) away from the second adjustment assembly (24) and the second control ring (23).

6. The vector nozzle according to claim 5, characterized in that: The second adjustment component (24) comprises a second adjustment rod (241) and second sealing sheets (242) arranged on both sides of the second adjustment rod (241); One end of the second adjustment rod (241) is hinged to the cone cylinder (1), and the hinge point (21) is arranged at the end of the second adjustment rod (241) away from the cone cylinder (1); one end of the fixing rod (223) away from the second connecting rod (222) is fixedly mounted on the second adjustment rod (241); The second sealing sheet (242) on any one of the second adjusting rods (241) is slidably fitted with a second sealing sheet (242) on an adjacent second adjusting rod (241).

7. The vector nozzle according to claim 5, characterized in that: There are multiple second control components (22), and the multiple second control components (22) are evenly distributed around the circumference of the cone (1).

8. An aircraft engine, characterized in that: Including the vector nozzle described in any one of claims 1-7.

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