Thrust vectoring nozzle and aero-engine

Abstract

The invention relates to the technical field of aero-engines, in particular to a thrust vectoring nozzle and an aero-engine. The thrust vectoring nozzle comprises a conical cylinder and a convergence mechanism. The device further comprises a first control mechanism and a plurality of first adjusting assemblies. A plurality of hinge points distributed along the circumference are formed at one end, far away from the conical cylinder, of the convergence mechanism; the multiple first adjusting assemblies are in one-to-one correspondence with the hinge points, and the multiple first adjusting assemblies are sequentially attached in the circumferential direction to form a cylindrical expansion section; the first control mechanism comprises a first control ring and a first control assembly; one end of the first control assembly is connected with the conical cylinder, and the other end is connected with the first control ring; the first control ring is connected with the first adjusting assemblies in a sliding fit mode, the first control ring can drive the first adjusting assemblies to deflect when moving in the center line direction of the conical cylinder, and a structure with the oval cross section is formed. Round-to-ellipse conversion can be realized, the stealth performance is improved, the characteristic of vector deflection is reserved, and the survival probability of a fighter in a battlefield can be greatly improved.

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; 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; 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; 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.

[0006] 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; 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; 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; A sliding rod is provided on the first control ring, and a sliding block matched with the sliding groove is provided at one end of the sliding rod away from the first control ring.

[0007] The vector nozzle as described above, wherein, optionally, the chute includes a first chute section and a second chute section; The first slot section is arranged along the length direction of the first adjusting rod; The second groove section is inclined along the length direction of the first adjusting rod and in the radial direction of the first control ring; the first groove section and the second groove section have a smooth transition; Along the circumferential direction of the first control ring, the second groove sections on the plurality of first adjustment rods correspond to a plurality of inclination angles.

[0008] The vector nozzle as described above, wherein optionally, the inclination angles of the second slot sections on any two of the first adjustment rods 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; Along the circumferential direction of the first control ring, from the first adjusting rod whose center line is located on the first plane to the first adjusting rod whose center line is located on the second plane, the inclination angle of the second groove section on each of the first adjusting rods increases successively; The second plane is a plane perpendicular to the wing of the aircraft where the vector nozzle is located and passes through the center line of the first control ring.

[0009] The vector nozzle as described above, wherein, optionally, the first control assembly is multiple and evenly distributed along the circumferential direction of the cone; The first control assembly includes a first push rod, a first support rod, a second support rod and two first connecting rods; The first push rod is slidably connected to the cone, and the first push rod can move in a direction close to or away from the cone; The first support rod is fixed to one end of the first push rod; the second support rod is fixedly connected to the first control ring; The two ends of the first support rod are respectively articulated with the first end balls of the two first connecting rods, and the two ends of the second support rod are respectively articulated with the second end balls of the two first connecting rods to form a parallelogram structure.

[0010] The vector nozzle as described above, wherein, optionally, the number of the first control components is at least three; and the plurality of the first control components are evenly distributed around the center line direction of the cone.

[0011] The vector nozzle as described above, wherein, optionally, the convergence mechanism comprises a second control component, a second control ring and a plurality of second adjustment components; One end of the second adjustment component is hinged to the cone, and the other end is provided with the hinge point; a plurality of the second adjustment components are distributed along the circumference of the cone; The second control assembly includes a second push rod, a second connecting rod and a fixed rod; One end of the second push rod is slidably connected to the cone cylinder, and the sliding direction is parallel to the axis of the cone cylinder; One end of the fixing rod is connected to the second adjusting assembly; Two ends of the second connecting rod are respectively hinged to one end of the fixing rod away from the second adjusting assembly and the second control ring.

[0012] The vector nozzle as described above, wherein, optionally, the second adjustment assembly includes a second adjustment rod and second sealing sheets arranged on both sides of the second adjustment rod; One end of the second adjusting rod is hinged to the cone, and the hinge point is arranged at the end of the second adjusting rod away from the cone; one end of the fixing rod away from the second connecting rod is fixedly mounted on the second adjusting rod; The second sealing sheet on any one of the second adjusting rods is slidably fitted with a second sealing sheet on an adjacent second adjusting rod.

[0013] As described above, in the vector nozzle, optionally, there are multiple second control components, and the multiple second control components are evenly distributed around the circumference of the cone.

[0014] According to another aspect of the present disclosure, an aircraft engine is also proposed, which includes the vector nozzle described in any one of the above items.

[0015] As will be described in detail below, according to the vector nozzle and aircraft engine of the embodiment of the present disclosure, by setting a convergence mechanism, a first control mechanism and a first adjustment component, an expansion section is formed in the rear direction of the convergence mechanism, and the expansion section is surrounded by a plurality of first adjustment components. Through the first control mechanism, the first adjustment component can achieve a change in the cross-sectional shape and a change in the direction of the vector nozzle. In particular, the vector nozzle proposed in the present disclosure can achieve a circular ellipse, which not only improves the stealth performance, but also retains the characteristics of vector deflection, which can greatly improve the survival probability of the fighter in the battlefield.

[0016] 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 technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. 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 of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0018] Figure 1 is a stereoscopic diagram of the vector nozzle proposed in the present disclosure; Figure 2 is a three-dimensional diagram of the local structure of the vector nozzle proposed in the present disclosure; Figure 3 It is a partial schematic diagram of the expansion section of the vector nozzle proposed in the present disclosure when it is a cylindrical structure; Figure 4 It is a partial structural schematic diagram of the expansion section of the vector nozzle proposed in the present disclosure in an expansion state; Figure 5 It is a schematic diagram of the local structure of the expansion section of the vector nozzle proposed in the present disclosure when it is deflected in one direction; Figure 6 It is a schematic diagram of the local structure of the expansion section of the vector nozzle proposed in the present disclosure when it is deflected in another direction; Figure 7 is a schematic diagram of a case where the expansion section of the vector nozzle proposed in the present disclosure is a straight cylindrical structure; Figure 8 yes Figure 7 Right view of; Fig. 9 is a schematic diagram of a vector nozzle proposed in the present disclosure when the cross-sectional shape is an elliptical structure; Fig.10 yes Fig. 9 Right view of; Fig.11 It is a schematic diagram of the change in the inclination angle of the second slot section proposed in the present disclosure.

[0019] Description of reference numerals: 1- cone, 2- convergence mechanism, 3- expansion section; 21- hinge point, 22- second control component, 23- second control ring, 24- second adjustment component; 221 - second push rod, 222 - second connecting rod, 223 - fixed rod; 241 - second adjusting rod, 242 - second sealing sheet; 31-first control mechanism, 32-first adjustment component; 311-first control ring, 312-first control component; 3111-slide bar, 3112-slide block; 3121-first push rod, 3122-first support rod, 3123-second support rod, 3124-first connecting rod; 321-first adjusting rod, 322-first sealing sheet, 323-pressing sheet; 3211- slide chute, 3212- first chute section, 3213- second chute section. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described here.

[0021] Please refer to Figures 1 to 9 The present disclosure proposes a vector nozzle, including a cone 1 and a convergence mechanism 2 arranged at the outlet of the cone 1; wherein, it also includes a first control mechanism 31 and a plurality of first adjustment components 32; in a specific implementation, the convergence mechanism 2 is used to form a constriction shape from front to back, that is, to form a convergence section. An expansion section 3 is formed behind the convergence mechanism 2. The first control mechanism 31 is used to control the first adjustment component 32 so that the expansion section 3 formed by the plurality of first adjustment components 32 can be deflected and converted from a circular cross section to an elliptical cross section. In a specific implementation, the cone 1 is a steel cone.

[0022] Please refer to Figure 1 and Figure 2 Specifically, 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; 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 the 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 fitted along the circumferential direction to form a cylindrical expansion section 3. The first adjustment components 32 can rotate around the hinge center lines corresponding to the hinge points 21, so that the first adjustment components 32 can be tilted in a direction close to or away from the center line of the cone 1, so as to realize that the first adjustment components 32 form an expansion section with a deflection or a changed cross-sectional shape.

[0023] In order to conveniently control the first adjustment component 32, in some embodiments, please refer to Figure 1The 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 cone 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 of the cone 1. The first control ring 311 is connected with the first adjustment component 32 in a sliding fit. When the first control ring 311 moves along the center line of the cone 1, it can drive each first adjustment component 32 to deflect and form a structure with an elliptical cross section. In a specific implementation, the first control ring 311 is controlled to drive each first adjustment component 32 to deflect to different degrees, and a shape with an elliptical cross section is formed at the position of the first control ring 311. In this way, the complex deflection control mechanism can be simplified and the reliability of the system is increased.

[0024] By transforming the vector nozzle from a circular shape to an elliptical shape, some high-temperature components can be shielded, and the mixing of the external airflow and the high-temperature mainstream can be enhanced to a certain extent, the temperature length of the core area of ​​the mainstream can be shortened, and the infrared radiation signal of the backward jet can be reduced to achieve infrared stealth. At the same time, the elliptical outlet cross-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 corners of the circular-to-rectangular nozzle. The smooth structure also improves the aerodynamic performance of the nozzle.

[0025] In order to realize that the plurality of first adjustment components 32 surround the expansion section and can adapt to the deflection of different angles and the change of the cross-sectional shape, in some implementations, please refer to Figures 1 to 4 The first adjustment assembly 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 fixedly disposed on both sides of each first adjustment rod 321. The first sealing sheets 322 are in the shape of long strips, and one edge of the first sealing sheet 322 in the length direction is fixedly connected to the first adjustment rod 321. The expansion section 3 is surrounded by the first sealing sheets 322. When the cross-sectional size of the expansion section 3 changes, the first sealing sheets 322 can automatically adapt to different cross-sectional sizes, thereby improving the sealing performance of the nozzle.

[0026] One end of the first adjusting rod 321 is hinged to the convergence mechanism 2 at a hinge point 21, see Figure 1 and Figure 2In a specific implementation, the number of the first adjustment rods 321 is equal to the number of the hinge points 21, and they correspond one to one. The first sealing sheets 322 on the two adjacent first adjustment rods 321 are slidably fitted, that is, there are two first sealing sheets 322 between the two adjacent first adjustment rods 321, and the two first sealing sheets 322 are respectively fixed on the two first adjustment rods 321, and the two first sealing sheets 322 are slidably fitted, that is, one of the first sealing sheets 322 is abutted 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 fitted during the sliding process. In a specific implementation, in order to ensure the sealing effect of the first sealing sheet 322, a pressing sheet 323 is also provided on the first adjustment rod 321, and 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.

[0027] In order to facilitate the control of the deflection angle of the first adjustment rod 321, that is, it is necessary to ensure that the first adjustment rod 321 can be controlled to deflect in a direction close to the center line of the cone 1, and to ensure that the first adjustment rod 321 can be controlled to deflect in a direction away from the center line of the cone 1. To this end, in some embodiments, the following improvements are made, please refer to Fig.11 , the first adjusting rod 321 is provided with a slide groove 3211 along the length direction, and the width of the bottom of the slide groove 3211 is greater than the width of the notch of the slide groove 3211. For example, the slide groove 3211 can be a T-shaped groove or a dovetail groove. In some implementations, it can also be set in other ways, as long as it can prevent the slider from falling off from the slide groove 3211 during the sliding process. The first control ring 311 is provided with a slide rod 3111, and the end of the slide rod 3111 away from the first control ring 311 is provided with a slide block 3112 adapted to the slide groove 3211. In some implementations, the slide block 3112 can also be set as a ball head structure, and the slide groove 3211 is set to a shape adapted to the ball head structure. In this way, the slide block 3112 can apply a component force radially inward along the cone 1 or radially outward along the cone 1 to the first adjusting rod 321 during the sliding process in the slide groove 3211, so as to accurately control the first adjusting rod 321. In a specific implementation, the sliding rods 3111 are 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 . The sliding rods 3111 are arranged along the radial direction of the first control ring 311 .

[0028] In order to achieve the control of the variable cross-section, it is necessary to control the first adjustment component 32 to different degrees of deflection to achieve the purpose of changing the cross-sectional shape. Fig.11In some implementations, the slide 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 differentiated control of different first adjustment rods 321 when the slider 3112 slides therein, that is, when the first control ring 311 moves along the axial direction of the cone 1 without radial offset, the deflection angles of the first adjustment rods 321 at different positions are different. The first groove section 3212 is arranged along the length direction of the first adjustment rod 321. That is, if the first control ring 311 moves along the axial direction of the cone 1 without radial offset, the deflection angles of multiple first adjustment rods 321 are the same.

[0029] The second slot section 3213 is inclined along the length direction of the first adjusting rod 321 and in the radial direction of the first control ring 311 ; the first slot section 3212 and the second slot section 3213 are smoothly transitioned, so that the slider 3112 can smoothly transition between the first slot section 3212 and the second slot section 3213 .

[0030] 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 tilt angles. Specifically, the tilt angle types are determined according to the actual situation. Taking the case of a circular ellipse as an example, when the number of first adjustment rods 321 is 24 and they are evenly distributed along the circumferential direction, there should be 7 tilt angles. Between the maximum tilt angle and the minimum tilt angle, the tilt angles of the second slot sections 3213 on the corresponding first adjustment rods 321 should increase or decrease in sequence.

[0031] In some implementations, in order to form a circular ellipse structure, especially to form a flat mouth structure on the vector nozzle, that is, the major axis of the corresponding ellipse is parallel to the plane where the aircraft wing is located, and the corresponding 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 implementations, the inclination angles of the second slot sections 3213 on any two of the first adjustment rods 321 symmetrically arranged about 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 passes through the center line of the first control ring 311.

[0032] Please refer to Fig.11 , 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 angle of the second groove section 3213 on each first adjustment rod 321 becomes larger in sequence, such as Fig.11 In the embodiment, the inclination angle of the second slot section 3213 on the first adjustment rod 321 gradually increases from 0 degrees to 90 degrees. The change of the inclination angle of the second slot section 3213 is preferably uniform. The second plane is a plane perpendicular to the wing of the aircraft where the vector nozzle is located and passes through the center line of the first control ring 311.

[0033] In some implementations, in order to facilitate the control of the movement of the first control ring 311, and thus realize the control of the vector nozzle's circular rotation to ellipse and the vector nozzle's deflection, there are multiple first control components 312, and they are evenly distributed along the circumferential direction of the cone 1. In some implementations, the number of the first control components 312 is at least three, and in some implementations, three is preferred.

[0034] Please refer to Figures 1 to 7 In order to conveniently control the first control ring 311, the first control assembly 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 cone 1, and the first push rod 3121 can move in a direction close to or away from the cone 1.

[0035] 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 a 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.

[0036] The center lines of all first support rods 3122 are in the same plane, and the plane where the center lines of the first support rods 3122 are located is perpendicular to the center line of the first control ring 311. The center lines of all second support rods 3123 are in the same plane, and the plane where the center lines of the second support rods 3123 are located is perpendicular to the center line of the first control ring 311.

[0037] For each parallelogram structure, the center line of the first support rod 3122 is always parallel to the center line of the second support rod 3123. During the operation of the first control assembly 312, it can ensure that the surface where the multiple first support rods 3122 are located is always parallel to the surface 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 produce a deflection in the radial direction, thereby achieving the purpose of changing the direction of the vector nozzle.

[0038] Please refer to Figure 1 , Figure 2 , Figure 8 , Fig.10 and Fig.11In a specific implementation, the number of the first control components 312 is at least three; and the multiple first control components 312 are evenly distributed around the center line direction of the cone 1. By setting multiple first control components 312, the complexity of control can be reduced while ensuring accurate control of the first control ring 311. By driving the first control ring 311 to achieve the deflection of the expansion section 3, the roundness and smoothness of the connection between the convergence section and the expansion section 3 can be better guaranteed, and the loss of jet engine thrust can be reduced.

[0039] In a specific implementation, the convergence mechanism 2 includes a second control component 22, a second control ring 23 and a plurality of second adjustment components 24. Through the convergence mechanism 2, the radius of the circle where the hinge point 21 is located can be changed to adjust the radial size of the expansion section.

[0040] Specifically, one end of the second adjustment assembly 24 is hinged to the cone 1, and the other end is provided with a hinge point 21; a plurality of second adjustment assemblies 24 are evenly distributed along the circumference of the cone 1. In specific implementation, the number of the second adjustment assemblies 24 is equal to the number of the first adjustment assemblies 32.

[0041] Please refer to Figures 1 to 7 , the second control assembly 22 includes a second push rod 221, a second connecting rod 222 and a fixed rod 223. The function of the second control assembly 22 is to control the contraction degree of the convergent section. Specifically, the contraction degree of the convergent section is achieved by controlling the position of the second control ring 23. When the contraction degree of the convergent section is different, the radius of the circle where the corresponding hinge point 21 is located is different. By setting the second control assembly 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 cone 1, and the sliding direction is parallel to the axis of the cone 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 cone 1. One end of the fixed rod 223 is connected to the second adjustment assembly 24; the two ends of the second connecting rod 222 are respectively hinged to the end of the fixed rod 223 away from the second adjustment assembly 24 and the second control ring 23. In this way, the second adjustment assembly 24 is rotated around the hinge center line with the cone 1 by the movement of the second control ring 23 .

[0042] In a specific implementation, the number of the second control components 22 may be at least three. For example, the three second control components 22 are evenly distributed along the circumference of the cone 1. Specifically, the second control component 22 may be spaced apart from the first control component 312.

[0043] Please refer to Figure 2In the specific implementation, in order to enclose the second adjustment assembly 24 into a sealed cylindrical structure, the second adjustment assembly 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 cone 1, and the hinge point 21 is arranged at the end of the second adjustment rod 241 away from the cone 1; the end of the fixing 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 convergent section changes, the second sealing sheet 242 can automatically adapt to different cross-sectional sizes, thereby improving the sealing performance of the nozzle.

[0044] The second sealing sheet 242 on any second adjustment rod 241 is slidably fitted with a second sealing sheet 242 on an adjacent second adjustment rod 241. Specifically, a second sealing sheet 242 is provided on both sides of each second adjustment rod 241, and the second sealing sheet 242 is in a strip shape, 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 two adjacent second adjustment rods 241 fit each other.

[0045] In the specific implementation, in order to avoid possible interference during the adjustment process, a cross-axis connection is adopted at the hinge point 21, and the first adjustment rod 321 and the second adjustment rod 241 are respectively rotatably connected to the two axes of the cross-axis, and the angle between the rotation center line of the cross-axis and the second adjustment rod 241 and the center line of the second adjustment rod 241 is 50 to 70 degrees, among which 60 degrees is preferred.

[0046] Through the vector nozzle proposed in the present disclosure, by controlling the synchronous movement of multiple second push rods 221 along the axial direction of the cone tube 1, the second control ring 23 can be driven to translate along the axial direction of the cone tube 1. When the second control ring 23 moves, the second connecting rod 222 is driven to move, and the second adjustment component 24 is further deflected around the hinge between it and the cone tube 1, thereby changing the contraction degree of the convergence section. Specifically, when the multiple second control rings 23 move away from the cone tube 1, the contraction degree of the convergence 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 convergence 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 the multiple sliders 3112 are located, if the sliders are all in the first slot section 3212, at this time, Figure 3 and Figure 7 As shown, the expansion section 3 is basically a cylindrical structure. Figure 3 and Figure 7 Based on the state shown, the second push rod 221 is adjusted to make the convergence section continue to contract, and the first control mechanism 31 is kept unchanged. At this time, the first adjustment component 32 is deflected, and the expansion section 3 forms a flaring structure, such as Figure 4 If Figure 3 and Figure 7 On the basis of the state shown, the second push rod 221 is kept unchanged, and each first push rod 3121 is controlled according to different elongation. Since the first support rod 3122, the second support rod 3123 and the two first connecting rods 3124 form a parallelogram structure with a ball hinge at the vertex, the joint action of multiple first control components 312 can make the center line of the first control ring 311 always parallel to the center line of the cone 1. When the lengths of multiple first push rods 3121 are different, the first control ring 311 is offset on the plane perpendicular to the center line of the cone 1. At this time, if all the sliders 3112 are located in the first slot section 3212, the expansion section 3 is still cylindrical, but the direction is deflected, 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 slot section 3213, the expansion section 3 is converted into an elliptical cross section.

[0047] exist Figure 3 , Figure 7 and Figure 8 In the state shown in , the length of the second push rod 221 is kept unchanged. If the lengths of all the first push rods 3121 are controlled to be equal, and all the sliders 3112 are located in the corresponding second slot sections 3213, at this time, the deflection angles of the first control components 312 located at different positions are different, so that the expansion section 3 is converted into an elliptical cross section, as shown in FIG. Fig. 9 and Fig.10 The present invention realizes the combination of the vector nozzle and the 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, which reduces the weight of the nozzle while ensuring reliability.

[0048] It should be pointed out that there is a certain coupling in the control of the convergence section and the expansion section 3. It is only necessary to adjust the movement length of the second push rod 221 to simultaneously adjust the diameters of the convergence section and the expansion section 3, thereby 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 a more precise adjustment can be made to the cross-sectional diameter of the expansion section 3.

[0049] The present disclosure proposes an aircraft engine, comprising the vector nozzle proposed in the present disclosure.

[0050] It should be noted that the circle and circular shape referred to in the present disclosure are not absolute circles or circular shapes, but approximate circles; the ellipse and ellipse referred to in the present disclosure are not absolute ellipses or ellipses, but approximate ellipses. As long as the deviation of any point is not greater than the set value, it can be considered to meet the circle or ellipse referred to in the present disclosure.

[0051] The basic principles of the present disclosure are described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, strengths, effects, etc. are required by each embodiment of the present disclosure. In addition, the specific details disclosed above are only for the purpose of illustration and ease of understanding, and are not limitations. The above details do not limit the present disclosure to the necessity of adopting the above specific details to be implemented.

[0052] The block diagrams of the devices, apparatuses, equipment, and systems involved in this disclosure are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including," "comprising," "having," and the like are open words, referring to "including but not limited to," and can be used interchangeably therewith. The words "or" and "and" used herein refer to the words "and / or," and can be used interchangeably therewith, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to," and can be used interchangeably therewith.

[0053] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list 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). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0054] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0055] Various changes, substitutions, and modifications of the techniques described herein may be made without departing from the teachings defined by the appended claims. Furthermore, 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 actions described above. Currently existing or later to be developed processes, machines, manufactures, compositions of events, means, methods, or actions that perform substantially the same functions or achieve substantially the same results as the corresponding aspects described herein may be utilized. Thus, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or actions within their scope.

[0056] The above 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 may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

[0057] The above description has been given for the purpose 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 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 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 assembly (32) in a sliding manner, and the first control ring (311) can drive each of the first adjustment assemblies (32) to deflect when moving along the center line direction of the cone (1), thereby forming a structure with an elliptical cross-section.

2. The vector nozzle according to claim 1, characterized in that: 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).

3. The vector nozzle according to claim 2, characterized in that: 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.

4. The vector nozzle according to claim 3, 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).

5. 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.

6. The vector nozzle according to claim 5, 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).

7. 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).

8. The vector nozzle according to claim 7, 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).

9. The vector nozzle according to claim 7, 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).

10. An aircraft engine, characterized in that: Including the vector nozzle described in any one of claims 1-9.

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