A multi-segment, large deflection angle, two-dimensional vector nozzle, method and application

Abstract

This invention discloses a multi-segment, large-angle two-dimensional vector nozzle, its method, and its application, belonging to the field of aero-engines. It includes a circular-to-square section, with a circular interface at the front end connected to the engine outlet, and an angle deflection mechanism arranged along the axial extension direction of the rear square outlet. The angle deflection mechanism includes circumferentially arranged side plates and follower components. Two side plates are symmetrically arranged on both sides of the rear square outlet, and two sets of follower components are coupled to the upper and lower sides of the rear square outlet, respectively, and located between the two side plates. The two side plates and the upper and lower follower components form the jet outlet. The follower components are composed of multiple angle adjustment plates sequentially hinged, allowing relative rotation between adjacent angle adjustment plates. By adjusting the rotation angle of each angle adjustment plate, the deflection angle of the jet outlet is adjusted, achieving a maximum deflection angle of 90°. This invention solves the problem that conventional two-dimensional vector nozzles cannot achieve large-angle vector deflection in the prior art.

Description

Technical Field

[0001] This invention belongs to the field of aero-engines, specifically relating to a multi-segment large deflection angle two-dimensional vector nozzle, its method, and its application. Background Technology

[0002] With the continuous advancement of modern aviation and military technology, the survival environment for fighter jets is becoming increasingly challenging. To gain an advantage and improve survivability in various air combat scenarios, higher demands are placed on aircraft performance. Thrust vectoring technology endows fighter jets with unprecedented maneuverability and agility, significantly enhancing their combat effectiveness and survivability. The vector nozzle is the core component of thrust vectoring technology, enabling aircraft to possess advantages such as high maneuverability, short takeoff distances, and even vertical takeoff and landing. Vector nozzles are mainly divided into two-dimensional vector nozzles and axisymmetric thrust vector nozzles. Two-dimensional vector nozzles have two key characteristics: First, they offer superior maneuverability. The vertically adjustable vector nozzle provides the ability to control pitch, improving aircraft maneuverability in the pitch dimension. Second, they reduce infrared signature. The rectangular nozzle allows for thorough mixing of the high-temperature exhaust stream with cool air, thereby reducing the aircraft's infrared signature.

[0003] The current two-dimensional vector nozzle has a single-plate structure at both the top and bottom. Due to the limitation of the flow area, its deflection capability is limited, and it can only achieve a deflection of about 20°, which cannot achieve true short-distance vertical take-off and landing. Summary of the Invention

[0004] The technical problem to be solved:

[0005] To overcome the shortcomings of existing technologies, this invention provides a multi-segment, large-angle two-dimensional vector nozzle and a method for adjusting thrust. By using follower components installed at the upper and lower edges of the circular-to-square exit, the large-angle adjustment of the two-dimensional vector nozzle is increased (up to 90°), thereby optimizing the short-distance vertical takeoff and landing process of aircraft. This invention solves the problem that conventional two-dimensional vector nozzles cannot achieve large-angle vector deflection in existing technologies.

[0006] The technical solution of this invention is: a multi-segment large deflection angle binary vector nozzle, comprising a circular-to-square section, wherein the front circular interface of the circular-to-square section is connected to the engine outlet, and the rear square outlet is provided with an angle deflection mechanism along the axial extension direction; the angle deflection mechanism includes side plates and follower components arranged circumferentially, the two side plates are symmetrically arranged on both sides of the rear square outlet, and two sets of follower components are respectively coupled to the upper and lower sides of the rear square outlet and located between the two side plates; the two side plates and the upper and lower follower components form a jet outlet;

[0007] The follower component is composed of multiple angle adjustment plates that are sequentially hinged together. Adjacent angle adjustment plates can rotate relative to each other. By adjusting the rotation angle of each angle adjustment plate, the deflection angle of the jet outlet can be adjusted, so that the maximum deflection angle of the jet outlet reaches 90°.

[0008] A further technical solution of the present invention is that the first adjusting plate, which is hinged to the square outlet at the rear end of the circular-to-square tube section, can be deflected by 15 to 20° relative to each other between adjacent angle adjusting plates.

[0009] A further technical solution of the present invention is: the angle adjustment plate is a rectangular flat plate, the long side of which is a hinged side, and the short side is its width; the width of the side plate is greater than or equal to the sum of the widths of the angle adjustment plates of the follower assembly, and the height is 4 to 5 times the width of the angle adjustment plate; so that the side plate can cover any deflection position of the upper and lower follower assemblies.

[0010] A further technical solution of the present invention is that the distance between the two side plates is equal to the length of the angle adjustment plate, so as to ensure the airtightness of the jet outlet.

[0011] A further technical solution of the present invention is that the follower component includes at least three sequentially hinged angle adjustment plates, and the hinge joints are sealed.

[0012] A further technical solution of the present invention is as follows: each of the upper and lower follower components includes three angle adjustment plates, namely an upper first angle adjustment plate, an upper second angle adjustment plate, an upper third angle adjustment plate, a lower first angle adjustment plate, a lower second angle adjustment plate, and a lower third angle adjustment plate; two first angle adjustment plates are respectively sealed and hinged to the upper and lower edges of the outlet of the circular-to-square section, two second angle adjustment plates are respectively sealed and hinged to the first angle adjustment plates, and two third angle adjustment plates are respectively sealed and hinged to the second angle adjustment plates; the width of the side plate is equal to three times the width of the angle adjustment plate.

[0013] A further technical solution of the present invention is: the two side plates are respectively fixed to both sides of the outlet of the round-to-square section by welding, and the center of the long side of the side plate is aligned with the center of the two sides of the round-to-square section by welding; the round-to-square section and the side plates have the same thickness.

[0014] A further technical solution of the present invention is: the rotation angle of each angle adjustment plate in the follow-up component corresponds to the nozzle deflection angle, the rotation angle of each angle adjustment plate is determined by the nozzle deflection angle, and follow-up control is applied.

[0015] A method for adjusting thrust using a multi-segment, large-angle two-dimensional vector nozzle is as follows:

[0016] When the nozzle is in its normal state, all the angle adjustment plates of the upper and lower follower components are in a horizontal position, and the nozzle is horizontal with no vector.

[0017] When the nozzle is in the downward vector state, the angle adjustment plates of the upper and lower follower components rotate downward in sequence, and the rotation angle is controlled by the set nozzle deflection angle; at this time, the jet direction is downward, and the nozzle obtains an upward thrust.

[0018] When the nozzle is in the upward vector state, the angle adjustment plates of the upper and lower follower components rotate upward in sequence, and the rotation angle is controlled by the set nozzle deflection angle; at this time, the jet direction is upward, and the nozzle obtains downward thrust.

[0019] An application of a multi-segment, large-angle two-dimensional vector nozzle, wherein the two-dimensional vector nozzle is used for thrust vector control of an aircraft, generating an additional torque perpendicular to the aircraft axis in the pitch direction.

[0020] Beneficial effects

[0021] The beneficial effects of this invention are as follows: the two-dimensional vector nozzle of this invention can fully mix the high-temperature exhaust flow with the cold air through the rectangular nozzle, thereby reducing the infrared signature of the aircraft; it applies thrust vector control to the aircraft, generating an additional torque perpendicular to the aircraft axis in the pitch direction, giving the engine higher vector performance, thereby improving the aircraft's maneuverability and survivability, and optimizing the short-distance vertical takeoff and landing process of the aircraft.

[0022] This invention expands the nozzle deflection angle range by using a follower component arranged along the axial extension direction, achieving a maximum deflection of 90°. The follower component is composed of multiple angle adjustment plates sequentially hinged together, and the rotation angle of each angle adjustment plate can be adjusted independently, enabling rapid adjustment of the entire nozzle deflection angle. By corresponding the nozzle deflection angle with the vector thrust, the required vector thrust of the aircraft can be precisely controlled by adjusting the rotation angle of the angle adjustment plate.

[0023] In this invention, the angle adjustment plates within the upper and lower follower components are connected by sealed hinges, thus providing excellent sealing performance. This improves the engine's vector thrust performance, thereby greatly enhancing the aircraft's maneuverability, combat capability, and survivability, and solving the problem of excessively small deflection angles in existing two-dimensional vector nozzles. The key challenge of this invention lies in using the hinged adjustment plates and side plates to form a sealed nozzle flow channel, which significantly reduces nozzle leakage losses while simultaneously improving the nozzle's vector thrust performance.

[0024] Preferably, the relative deflection angle of the first adjustment plate hinged to the square outlet at the rear end of the circular-to-square section between adjacent angle adjustment plates is set to 15-20°, and the number of angle adjustment plates in each set of follower components is limited to at least 3 in order to make the maximum deflection angle of the jet outlet reach 90°.

[0025] Preferably, the width of the side plate is set to be greater than or equal to the sum of the widths of the angle adjustment plates of the follower component, and the height is 4 to 5 times the width of the angle adjustment plate, so that the side plate can cover any deflection position of the upper and lower follower components; at the same time, the distance between the two side plates is limited to be equal to the length of the angle adjustment plate, ensuring the integrity and airtightness of the entire nozzle flow channel and preventing air leakage. Attached Figure Description

[0026] Figure 1 This is an overall axis view of the nozzle;

[0027] Figure 2 This is a top view of the entire nozzle;

[0028] Figure 3 This is a bottom view of the entire nozzle;

[0029] Figure 4 This is an axis view of a circular-to-square section;

[0030] Figure 5 This is the left view of the circular-to-square section;

[0031] Figure 6 The nozzle deflects downwards;

[0032] Figure 7 The nozzle deflects upwards;

[0033] Figure 8 This is a numerical simulation of the temperature distribution (in K) when the nozzle deflects downwards.

[0034] Figure 9 This is a numerical simulation density distribution diagram of the nozzle deflecting downwards (unit: kg / m³). 3 );

[0035] Explanation of reference numerals in the attached drawings: 1. Round to square tube section; 2. Side plate; 3. Side plate; 4. Upper first angle adjustment piece; 5. Upper second angle adjustment piece; 6. Upper third angle adjustment piece; 7. Lower first angle adjustment piece; 8. Lower second angle adjustment piece; 9. Lower third angle adjustment piece. Detailed Implementation

[0036] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the invention, and should not be construed as limiting the invention.

[0037] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0038] Reference Figures 1-3 As shown, an embodiment of the present invention provides a multi-segment large deflection angle binary vector nozzle, comprising a circular-to-square section 1, side plates 2 and 3, an upper first angle adjusting plate 4, an upper second angle adjusting plate 5, an upper third angle adjusting plate 6, a lower first angle adjusting plate 7, a lower second angle adjusting plate 8, and a lower third angle adjusting plate 9. The circular inlet of the circular-to-square section 1 is connected to the engine outlet via high-temperature resistant bolts. The square outlet of the circular-to-square section 1 is welded to the long sides of side plates 2 and 3 on both sides, respectively. The upper side of the rectangular outlet of the circular-to-square section 1 is hinged to the long side of the upper first angle adjusting plate 4, the upper second angle adjusting plate 5 is hinged to the other long side of the upper first angle adjusting plate 4, and the upper third angle adjusting plate 6 is hinged to the other long side of the upper second angle adjusting plate 5. The lower side of the rectangular outlet of the circular-to-square section 1 is hinged to the long side of the lower first angle adjusting plate 7, the lower second angle adjusting plate 8 is hinged to the other long side of the lower first angle adjusting plate 7, and the lower third angle adjusting plate 9 is hinged to the other long side of the lower second angle adjusting plate 8. The inner walls of the circular-to-square section 1, the six adjusting plates, and the two side plates form a sealed airflow channel. The high-temperature engine gas entering through the circular-to-square section 1 is ejected through this sealed channel.

[0039] Preferably, both side plates are rectangular plates, with one long side welded to both sides of the round-to-square exit, and the distance between the two side plates is the side length of the square exit segment of the round-to-square segment.

[0040] Preferably, the horizontal side of the two side plates is the short side and the vertical side is the long side, wherein the length of the short side is equal to 3 times the width of the adjustment piece and the length of the long side is 4 to 5 times the width of the adjustment piece.

[0041] Preferably, all six adjusting plates are rectangular adjusting plates of the same size, wherein the hinged sides are all long sides, and the adjacent adjusting plates, as well as the first adjusting plate and the round-to-square outlet, can be deflected relative to each other by 15 to 20 degrees.

[0042] An angle deflection mechanism is composed of side plate 2, side plate 3, upper first angle adjusting plate 4, upper second angle adjusting plate 5, upper third angle adjusting plate 6, lower first angle adjusting plate 7, lower second angle adjusting plate 8, and lower third angle adjusting plate 9. Upper first angle adjusting plate 4, upper second angle adjusting plate 5, and upper third angle adjusting plate 6 constitute an upper follower assembly, and lower first angle adjusting plate 7, lower second angle adjusting plate 8, and lower third angle adjusting plate 9 constitute a lower follower assembly. The angle deflection mechanism also includes a driving component, which controls the rotation angle of the angle adjusting plate through a connecting member to ensure stability in either horizontal or deflected states.

[0043] The two-dimensional vector nozzle of this invention, through its rectangular nozzle, enables thorough mixing of the high-temperature exhaust stream with cold air, thereby reducing the aircraft's infrared signature and improving its infrared and radar stealth capabilities. By adjusting the upper and lower three adjustment vanes for deflection, the nozzle can achieve a large-angle deflection thrust, enhancing the aircraft's maneuverability and survivability, thus solving the problem of excessively small deflection angles in existing two-dimensional vector nozzles.

[0044] Specifically, such as Figure 4 and Figure 5 As shown, the circular-to-square section 1 can be fixed to the engine via three bolt interfaces. The profile of the circular-to-square section 1 gradually transitions from a circular inlet to a square outlet, with the diameter of the circular inlet matching the engine dimensions. The outlet cross-section of the circular-to-square section 1 is square, with a width-to-height ratio of 1:1.

[0045] like Figure 2 and Figure 3 As shown, all six adjusting plates are rectangular. Two first-angle adjusting plates are respectively sealed and hinged to the upper and lower edges of the round-to-square outlet. Two second-angle adjusting plates are respectively sealed and hinged to the first-angle adjusting plates. Two third-angle adjusting plates are respectively sealed and hinged to the second-angle adjusting plates.

[0046] This embodiment describes a method for adjusting thrust using a multi-segment, large-angle two-dimensional vector nozzle, as detailed below:

[0047] When the nozzle is in its normal state, the three upper adjustment plates and the three lower adjustment plates are all in a horizontal position, and the nozzle is horizontal with no vector.

[0048] like Figure 6 As shown, when the nozzle is in the downward vector state, the upper first angle adjustment plate 4 deflects downward relative to the outlet of the circular-square section 1, and the second angle adjustment plate 5 and the third angle adjustment plate 6 deflect downward in sequence; at the same time, the lower first angle adjustment plate 7 deflects downward relative to the outlet of the circular-square section 1, and the second angle adjustment plate 8 and the third angle adjustment plate 9 deflect downward in sequence. The jet direction is downward, and the nozzle obtains an upward thrust at this time.

[0049] like Figure 7 As shown, when the nozzle is in the upward vector state, the upper first angle adjustment plate 4 deflects upward relative to the outlet of the circular-square section 1, and the second angle adjustment plate 5 and the third angle adjustment plate 6 deflect upward in sequence; at the same time, the lower first angle adjustment plate 7 deflects upward relative to the outlet of the circular-square section 1, and the second angle adjustment plate 8 and the third angle adjustment plate 9 deflect upward in sequence. The jet direction is upward, and the nozzle obtains downward thrust at this time.

[0050] When the nozzle deflects downwards, a numerical simulation is performed, setting the total inlet temperature of the nozzle to 800K, the pressure ratio to 3, and the ambient pressure to 101325Pa. The temperature distribution is as follows: Figure 8 Density distribution as Figure 9 The numerical simulation thrust results are shown in the table below:

[0051]

[0052] As can be seen from the table above, the thrust vector angle has reached 60 degrees, far exceeding that of conventional two-dimensional vector nozzles. Therefore, this configuration of two-dimensional vector nozzles can achieve a large range of deflection angles.

[0053] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A multi-segment, large deflection angle, two-dimensional vector nozzle, characterized in that: The system includes a circular-to-square section, the front circular interface of which is connected to the engine outlet, and the rear square outlet with an angle deflection mechanism along its axial extension direction. The angle deflection mechanism includes side plates and follower components arranged circumferentially. The two side plates are symmetrically arranged on both sides of the rear square outlet, and the two sets of follower components are coupled to the upper and lower sides of the rear square outlet and located between the two side plates. The jet outlet is formed by the two side plates and the upper and lower follower components. The follower component is composed of multiple angle adjustment plates that are sequentially hinged together. Adjacent angle adjustment plates can rotate relative to each other. By adjusting the rotation angle of each angle adjustment plate, the deflection angle of the jet outlet can be adjusted, so that the maximum deflection angle of the jet outlet reaches 90°.

2. The multi-segment large deflection angle binary vector nozzle according to claim 1, characterized in that: The first adjustment plate, which is hinged to the square outlet at the rear end of the circular-to-square section, can be deflected by 15 to 20 degrees relative to each other between adjacent angle adjustment plates.

3. The multi-segment large deflection angle binary vector nozzle according to claim 2, characterized in that: The angle adjustment plate is a rectangular flat plate with its long side being the hinge side and its short side being its width; the width of the side plate is greater than or equal to the sum of the widths of the angle adjustment plates of the follower assembly, and its height is 4 to 5 times the width of the angle adjustment plate; so that the side plate can cover any deflection position of the upper and lower follower assemblies.

4. The multi-segment large deflection angle binary vector nozzle according to claim 3, characterized in that: The distance between the two side plates is equal to the length of the angle adjustment plate, which is used to ensure the airtightness of the jet outlet.

5. The multi-segment large deflection angle binary vector nozzle according to claim 4, characterized in that: The follow-up component includes at least three sequentially hinged angle adjustment plates, and the hinge joints are sealed.

6. The multi-segment large deflection angle binary vector nozzle according to claim 5, characterized in that: Each of the upper and lower follower components includes three angle adjustment plates: an upper first angle adjustment plate, an upper second angle adjustment plate, an upper third angle adjustment plate, a lower first angle adjustment plate, a lower second angle adjustment plate, and a lower third angle adjustment plate. Two first angle adjustment plates are respectively sealed and hinged to the upper and lower edges of the outlet of the circular-to-square section, two second angle adjustment plates are respectively sealed and hinged to the first angle adjustment plates, and two third angle adjustment plates are respectively sealed and hinged to the second angle adjustment plates. The width of the side plate is equal to three times the width of the angle adjustment plate.

7. The multi-segment large deflection angle binary vector nozzle according to claim 1, characterized in that: The two side plates are respectively welded to both sides of the outlet of the round-to-square section, and the center of the long side of the side plate is aligned with the center of the two sides of the round-to-square section; the round-to-square section and the side plates have the same thickness.

8. The multi-segment large deflection angle binary vector nozzle according to claim 1, characterized in that: The rotation angle of each angle adjustment plate in the follow-up component corresponds to the nozzle deflection angle. The rotation angle of each angle adjustment plate is determined by the nozzle deflection angle, and follow-up control is applied.

9. A method for adjusting thrust of a multi-segment large deflection angle two-dimensional vector nozzle according to any one of claims 1-8, characterized in that: When the nozzle is in its normal state, all the angle adjustment plates of the upper and lower follower components are in a horizontal position, and the nozzle is horizontal with no vector. When the nozzle is in the downward vector state, the angle adjustment plates of the upper and lower follower components rotate downward in sequence, and the rotation angle is controlled by the set nozzle deflection angle; at this time, the jet direction is downward, and the nozzle obtains an upward thrust. When the nozzle is in the upward vector state, the angle adjustment plates of the upper and lower follower components rotate upward in sequence, and the rotation angle is controlled by the set nozzle deflection angle; at this time, the jet direction is upward, and the nozzle obtains downward thrust.

10. An application of the multi-segment large deflection angle binary vector nozzle according to any one of claims 1-8, characterized in that: The binary vector nozzle is used for thrust vector control of the aircraft, generating an additional torque perpendicular to the aircraft axis in the pitch direction.

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