A simplified aerodynamic thrust vectoring nozzle and its control method

Abstract

This invention discloses a simplified aerodynamic thrust vectoring nozzle and its control method, comprising a nozzle outer wall, a nozzle inlet and outlet located at opposite ends of the nozzle outer wall, a bypass secondary flow inlet, a bypass valve, a front convergent section, a nozzle throat, a bypass secondary flow outlet, and an adaptive bypass cavity located within the nozzle outer wall. The front convergent section is hinged to the nozzle outer wall via a front hinge, and the rear diverging section is hinged to the nozzle outer wall via a rear hinge. The space enclosed by the nozzle outer wall, the front convergent section, and the rear diverging section constitutes the adaptive bypass cavity. The upstream of the bypass secondary flow inlet connects to the nozzle outer wall and the front convergent section, and the downstream connects to the adaptive bypass cavity. The upstream of the bypass secondary flow outlet connects to the adaptive bypass cavity, and the downstream connects to the nozzle throat and the rear diverging section. This invention simplifies the adaptive bypass channel structure, reduces structural complexity and weight, and achieves simultaneous adjustment of thrust vector angle and flow capacity, resulting in superior aerodynamic performance.

Description

Technical Field

[0001] This invention belongs to the field of advanced aero-engine exhaust system design, and specifically relates to an aerodynamic thrust vectoring nozzle and its control method. Background Technology

[0002] Research on aerodynamic thrust vectoring nozzles is a hot research area in the field of aerospace propulsion technology. Compared with the complex adjustment mechanism of traditional mechanical vectoring nozzles, aerodynamic thrust vectoring nozzles have significant advantages. Among them, the throat-deflecting aerodynamic vectoring nozzle deflects the mainstream flow by asymmetrically injecting a secondary flow near the nozzle throat, thereby generating a stable thrust vector. With its fixed geometric configuration, simple mechanical structure, and excellent vectoring performance, it has become a research focus for many countries.

[0003] Current adaptive bypass aerodynamic thrust vector nozzles adjust the thrust vector angle of the nozzle by controlling the opening of the bypass valve. However, their bypass channels are mostly complex in structure, heavy in weight, have fixed geometry that cannot be adjusted, and have low reliability.

[0004] Therefore, this invention provides a simplified aerodynamic thrust vector nozzle and its control method. By condensing the typical flow characteristics of the adaptive bypass aerodynamic thrust vector nozzle, the bypass channel structure design is simplified, reducing structural complexity, weight, and cost, laying the foundation for subsequent applications. Summary of the Invention

[0005] In order to overcome the shortcomings of the existing technology, the purpose of this invention is to provide a simplified aerodynamic thrust vector nozzle and its control method, so as to reduce the weight caused by the complex bypass channel, realize the simultaneous adjustment of thrust vector angle and flow capacity, and have better aerodynamic performance.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A simplified aerodynamic thrust vectoring nozzle includes an outer wall surface of the nozzle, a nozzle inlet and a nozzle outlet located at opposite ends of the outer wall surface, a bypass secondary flow inlet, a bypass valve, a front convergent section, a nozzle throat, a bypass secondary flow outlet, and an adaptive bypass cavity located within the outer wall surface of the nozzle, wherein:

[0008] The front converging section is hinged to the outer wall of the nozzle via a front hinge, and the rear expanding section is hinged to the outer wall of the nozzle via a rear hinge; the space enclosed by the outer wall of the nozzle, the front converging section, and the rear expanding section constitutes the adaptive bypass cavity.

[0009] The nozzle throat is located at the junction of the front converging section and the rear diverging section;

[0010] The upstream of the bypass secondary flow inlet is connected to the outer wall of the nozzle and the front convergence section, and the downstream is connected to the adaptive bypass cavity.

[0011] The bypass secondary flow outlet is connected upstream to the adaptive bypass cavity and downstream to the nozzle throat and the rear expansion section.

[0012] The bypass valve is located at the inlet of the bypass secondary flow and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity.

[0013] Furthermore, the outer wall shape of the nozzle can be varied to change the shape of the adaptive bypass cavity.

[0014] Furthermore, the front converging section is rotatable about the front hinge, and the rear expanding section is rotatable about the rear hinge, thereby changing the nozzle throat height H. throat This allows for the adjustment of nozzle flow capacity.

[0015] Furthermore, the rotation angle α of the front converging section satisfies 20°≤α≤40°, where α is the angle between the front converging section and the outer wall of the nozzle; the rotation angle β of the rear expanding section satisfies 10°≤β≤20°, where β is the angle between the rear expanding section and the outer wall of the nozzle.

[0016] Furthermore, the upper and lower sides of the front convergent section can rotate symmetrically or asymmetrically. When the pressure ratio is 4, if only the upper and lower sides of the front convergent section rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°.

[0017] Furthermore, the upper and lower sides of the rear expansion section can rotate asymmetrically. When the pressure ratio is 4, if only the upper and lower sides of the rear expansion section rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

[0018] Furthermore, the nozzle throat height H throat With nozzle inlet height H in The relationship between them satisfies 0.28 ≤ H throat / H in ≤0.49.

[0019] Furthermore, the length L1 of the front converging section is related to the nozzle inlet height H. in The relationship between them satisfies 0.38 ≤ L1 / H in ≤0.46.

[0020] Furthermore, the length L2 of the rear expansion section is related to the nozzle inlet height H. in The relationship between them satisfies 0.84 ≤ L² / H in ≤0.92.

[0021] Furthermore, the height H of the bypass secondary flow channelbypass With nozzle inlet height H in The relationship between them satisfies 0.05 ≤ H bypass / H in ≤0.15.

[0022] Furthermore, the nozzle exit height H out With nozzle inlet height H in The relationship between them satisfies 0.65 ≤ H out / H in ≤1.15.

[0023] Furthermore, the structure of the aerodynamic thrust vectoring nozzle is suitable for Laval nozzles, dual-throat aerodynamic thrust vectoring nozzles, or axisymmetric fluid thrust vectoring nozzles.

[0024] A control method for the aerodynamic thrust vector nozzle includes the following steps: the front converging section can rotate around the front hinge, and the rear expanding section can rotate around the rear hinge. By combining the two, the throat area is adjusted to achieve the adjustment of the nozzle flow capacity.

[0025] Furthermore, in the non-vectoring state, the front converging section and the rear diverging section are rotated synchronously to adjust the nozzle throat height H. throat This allows for the adjustment of nozzle flow capacity.

[0026] Furthermore, in the vector state, the bypass valve works in conjunction with the front convergence section and the rear expansion section to simultaneously adjust the thrust vector and flow capacity.

[0027] Beneficial effects: The simplified aerodynamic thrust vectoring nozzle and its control method of the present invention have the following advantages compared with the prior art:

[0028] (1) In this invention, the cavity formed by the front convergent section and the rear expansion section and the outer wall of the nozzle is used as an adaptive bypass channel, which greatly simplifies the structure of the adaptive bypass channel and has the advantages of easy processing, light weight and good maintainability. The weight of a single adaptive bypass channel is expected to be reduced by more than 50%.

[0029] (2) In this invention, the flow capacity is adjusted by rotating the front converging section and the rear expanding section to adjust the nozzle throat area. Compared with the traditional fixed geometry structure, this invention is expected to achieve a flow adjustment range of 80% to 120%. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of a pneumatic thrust vectoring nozzle in one embodiment of the present invention;

[0031] Figure 2This is a dimensioned diagram of a pneumatic thrust vector nozzle and its control method in one embodiment of the present invention;

[0032] Figure 3 This is a schematic diagram of a design scheme for a bypass dual-throat nozzle in one embodiment of the present invention;

[0033] Figure 4 Mach number contour plot for a traditional bypass dual-throat nozzle under vector conditions;

[0034] Figure 5 This is a numerical simulation Mach number cloud diagram under vector conditions for a bypass dual-throat nozzle design scheme in one embodiment of the present invention.

[0035] Figure 6 This is a numerical simulation Mach number cloud diagram under non-vector conditions for a bypass dual-throat nozzle design scheme in one embodiment of the present invention;

[0036] Figure 7 This is a numerical simulation Mach number cloud diagram of the enlarged throat area in a non-vector state for a bypass dual-throat nozzle design scheme in one embodiment of the present invention.

[0037] Figure 8 This is a numerical simulation Mach number cloud diagram of the asymmetric inward rotation of the upper and lower front convergent sections in a vector state for a bypass dual-throat nozzle design scheme in one embodiment of the present invention.

[0038] In the picture:

[0039] 1. Nozzle inlet, 2. Nozzle outer wall, 3. Front hinge, 4. Bypass secondary flow inlet, 5. Bypass valve, 6. Front convergent section, 7. Nozzle throat, 8. Bypass secondary flow outlet, 9. Adaptive bypass cavity, 10. Rear diverging section, 11. Rear hinge, 12. Nozzle outlet. Detailed Implementation

[0040] The present invention will be further explained below with reference to the accompanying drawings and embodiments.

[0041] like Figures 1 to 3 As shown, in one embodiment of the present invention, a simplified aerodynamic thrust vector nozzle includes a nozzle inlet 1, a nozzle outer wall 2, a front hinge 3, a bypass secondary flow inlet 4, a bypass valve 5, a front convergent section 6, a nozzle throat 7, a bypass secondary flow outlet 8, an adaptive bypass cavity 9, a rear expansion section 10, a rear hinge 11, and a nozzle outlet 12 connected in series.

[0042] The nozzle inlet 1 and nozzle outlet 12 are located at opposite ends of the outer wall 2 of the nozzle. The fluid flows from the nozzle inlet 1 to the nozzle outlet 12.

[0043] 4. Bypass secondary flow inlet, 5. Bypass valve, 6. Front convergent section, 7. Nozzle throat, 8. Bypass secondary flow outlet, and 9. Adaptive bypass cavity are located inside the outer wall surface 2 of the nozzle.

[0044] The front converging section 6 is hinged to the outer wall surface 2 of the nozzle via the front hinge 3, and the rear expanding section 10 is hinged to the outer wall surface 2 of the nozzle via the rear hinge 11.

[0045] The space enclosed by the nozzle outer wall 2, the front converging section 6, and the rear diverging section 10 constitutes the adaptive bypass cavity 9. The adaptive bypass cavity 9 is used to receive the airflow from the bypass secondary flow inlet 4, and after passing through the adaptive bypass cavity 9, it flows out from the bypass secondary flow outlet 8, causing disturbance to the mainstream.

[0046] The nozzle throat 7 is located at the junction of the front converging section 6 and the rear diverging section 10.

[0047] The bypass secondary flow inlet 4 is upstream connected to the nozzle outer wall 2 and the front convergence section 6, and downstream connected to the adaptive bypass cavity 9.

[0048] The bypass secondary flow outlet 8 is upstream connected to the adaptive bypass cavity 9, and downstream connected to the nozzle throat 7 and the rear expansion section 10.

[0049] The bypass valve 5 is located at the bypass secondary flow inlet 4 and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity 9.

[0050] The front converging section 6 is rotatable about the front hinge 3, and the rear expanding section 10 is rotatable about the rear hinge 11 to change the height H of the nozzle throat 7. throat This allows for the adjustment of nozzle flow capacity.

[0051] In one embodiment of the present invention, the shape of the nozzle outer wall 2 is variable, thereby changing the shape of the adaptive bypass cavity.

[0052] In one embodiment of the present invention, the rotation angle α of the front converging section 6 satisfies 20°≤α≤40°, where α is the angle between the front converging section 6 and the outer wall surface 2 of the nozzle; the rotation angle β of the rear expanding section 10 satisfies 10°≤β≤20°, where β is the angle between the rear expanding section 10 and the outer wall surface 2 of the nozzle, such as... Figure 2 As shown.

[0053] In one embodiment of the present invention, the nozzle throat 7 is at a height H throat Height H of nozzle inlet in The relationship between them satisfies 0.28 ≤ H throat / H in ≤0.49.

[0054] In one embodiment of the present invention, the length L1 of the front converging section 6 is equal to the height H of the nozzle inlet 1. in The relationship between them satisfies 0.38 ≤ L1 / Hin ≤0.46.

[0055] In one embodiment of the present invention, the length L2 of the rear expansion section 10 is equal to the height H of the nozzle inlet 1. in The relationship between them satisfies 0.84 ≤ L² / H in ≤0.92.

[0056] In one embodiment of the present invention, the bypass secondary flow channel 8 has a height H. bypass Height H of nozzle inlet in The relationship between them satisfies 0.05 ≤ H bypass / H in ≤0.15;

[0057] In one embodiment of the present invention, the nozzle outlet 12 is at a height H out Height H of nozzle inlet in The relationship between them satisfies 0.65 ≤ H out / H in ≤1.15.

[0058] In one embodiment of the present invention, a control method for a pneumatic thrust vector nozzle includes the following steps: the front converging section 6 can rotate around the front hinge 3, and the rear expanding section 10 can rotate around the rear hinge 11. By combining the two, the throat area is adjusted to achieve the adjustment of the nozzle flow capacity.

[0059] In one embodiment of the present invention, in a non-vector state, the front converging section 6 and the rear expanding section 10 are rotated synchronously to adjust the height H of the nozzle throat 7. throat This allows for the adjustment of nozzle flow capacity.

[0060] In one embodiment of the present invention, in the vector state, the bypass valve 5 works in conjunction with the front convergence section 6 and the rear expansion section 10 to simultaneously adjust the thrust vector and flow capacity.

[0061] The simplified aerodynamic thrust vectoring nozzle of this invention uses the space formed by the nozzle's outer wall, the front convergent section, and the rear diverging section as an adaptive bypass, replacing the original complex bypass duct structure. Compared to the replaced bypass duct structure, the solution of using the three inherent internal flow channels of the nozzle as adaptive bypasses reduces the number of parts, decreases the nozzle's weight, and reduces its complexity.

[0062] Compared to the original fixed-wall solution, this invention solves the problem of unadjustable flow rate. The front converging section 6 can rotate around the front hinge 3 located in front of it, and the rear expanding section 10 can rotate around the rear hinge 11 located behind it. Together, they adjust the throat area, thereby regulating the nozzle flow capacity. Preferably, the upper and lower sides of the front converging section 6 and the rear expanding section 10 can rotate symmetrically or asymmetrically, achieving simultaneous adjustment of flow capacity and thrust vector. In one embodiment of this invention, the upper and lower sides of the front converging section 6 can rotate symmetrically or asymmetrically. When the pressure ratio is 4, if only the upper and lower sides of the front converging section 6 rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°. The upper and lower sides of the rear expanding section 10 can rotate asymmetrically. When the pressure ratio is 4, if only the upper and lower sides of the rear expanding section 10 rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

[0063] When the bypass valve of the nozzle opens, the secondary flow merges with the main flow at the nozzle throat through the bypass channel. Generally, although the geometric throat area remains unchanged, the injection of the secondary flow reduces the effective aerodynamic throat area, thus reducing the nozzle's flow capacity. This invention adjusts the throat geometry by actuating the front convergent section and the rear diverging section, compensating for the flow capacity loss caused by the opening vector. It also meets the flow regulation requirements of aircraft during afterburner operation.

[0064] The structure of the aerodynamic thrust vectoring nozzle of the present invention is applicable to Laval nozzles, dual-throat aerodynamic thrust vectoring nozzles, or axisymmetric fluid thrust vectoring nozzles.

[0065] The present invention can be better understood from the following embodiments.

[0066] Example 1:

[0067] Design scheme for bypass dual-throat nozzle.

[0068] In this embodiment, the structure of the bypass dual-throat nozzle is as follows: it includes a nozzle outer wall surface 2, a nozzle inlet 1 and a nozzle outlet 12 located at both ends of the nozzle outer wall surface 2, a bypass secondary flow inlet 4, a bypass valve 5, a front convergent section 6, a nozzle throat 7, a bypass secondary flow outlet 8, and an adaptive bypass cavity 9 located within the nozzle outer wall surface 2. The front convergent section 6 is hinged to the nozzle outer wall surface 2 via a front hinge 3, and the rear expanding section 10 is hinged to the nozzle outer wall surface 2 via a rear hinge 11. The space enclosed by the front convergent section 6 and the rear diverging section 10 constitutes the adaptive bypass cavity 9; the nozzle throat 7 is located at the junction of the front convergent section 6 and the rear diverging section 10; the bypass secondary flow inlet 4 is connected upstream to the nozzle outer wall 2 and the front convergent section 6, and downstream to the adaptive bypass cavity 9; the bypass secondary flow outlet 8 is connected upstream to the adaptive bypass cavity 9, and downstream to the nozzle throat 7 and the rear diverging section 10; the bypass valve 5 is located at the bypass secondary flow inlet 4 and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity 9.

[0069] The front converging section 6 can rotate around the front hinge 3, and the rear diverging section 10 can rotate around the rear hinge 11 to change the height H of the nozzle throat 7. throat This allows for the adjustment of nozzle flow capacity.

[0070] Figure 3 The diagram shown is a structural schematic of the design scheme of the bypass dual-throat nozzle of the present invention. Figure 4 Mach number cloud map for a traditional bypass dual-throat nozzle under vector state; Figure 5 This is a numerical simulation Mach number contour plot of the design scheme of the bypass dual-throat nozzle of the present invention under vector conditions. Through the design of the present invention, with a design pressure ratio of 4, according to simulation calculations, the thrust vector angle of the configuration of the present invention is about 50% larger than that of the conventional configuration, demonstrating the technical advantages of the present invention.

[0071] Figure 6 The numerical simulation Mach number cloud diagram of the design scheme of the bypass dual-throat nozzle of the present invention under non-vector state is shown. Figure 7 This is a numerical simulation of the Mach number contour plots of the front converging sections and rear expanding sections on both sides of the upper and lower sides, showing their symmetrical inward rotation under non-vector conditions, for the bypass dual-throat nozzle design scheme of this invention. Through the design of this invention, the geometric throat area can be enlarged by changing the internal flow channel profile. When the design pressure ratio is 4, according to simulation calculations, the flow coefficient of the configuration of this invention is approximately 4% larger than that of the traditional configuration, demonstrating the technical advantages of this invention.

[0072] Figure 8This paper presents numerical simulation Mach number contour plots of the asymmetric inward rotation of the upper and lower front convergent sections under vector conditions, representing the design scheme of the bypass dual-throat nozzle according to the present invention. Through the design of the present invention, with a design pressure ratio of 4, simulation results show that, with the same opening degree of the bypass valves on both the upper and lower sides, a thrust vector angle of approximately 10° can be achieved by changing the inner flow channel profile through the rotation of the front convergent section, demonstrating the technical advantages of the present invention.

[0073] Example 2

[0074] Application examples of the adaptive bypass cavity of the present invention in Laval nozzles

[0075] Based on the traditional Laval nozzle, the adaptive bypass cavity design of this invention is adopted.

[0076] Example 3

[0077] Application examples of the adaptive bypass cavity of the present invention in axisymmetric fluid thrust vectoring nozzles

[0078] Based on the traditional axisymmetric fluid thrust vector nozzle, the adaptive bypass cavity design of this invention is adopted.

[0079] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A simplified aerodynamic thrust vectoring nozzle, characterized in that: Includes the nozzle outer wall (2), the nozzle inlet (1) and nozzle outlet (12) located at both ends of the nozzle outer wall (2), and the bypass secondary flow inlet (4), bypass valve (5), front convergent section (6), nozzle throat (7), bypass secondary flow outlet (8), adaptive bypass cavity (9), and rear expansion section (10) located within the nozzle outer wall (2), wherein: The front converging section (6) is hinged to the nozzle outer wall (2) via the front hinge (3), and the rear expanding section (10) is hinged to the nozzle outer wall (2) via the rear hinge (11); the space enclosed by the nozzle outer wall (2), the front converging section (6), and the rear expanding section (10) constitutes the adaptive bypass cavity (9). The nozzle throat (7) is located at the junction of the front converging section (6) and the rear expanding section (10); The bypass secondary flow inlet (4) is connected upstream to the nozzle outer wall (2) and the front convergence section (6), and downstream to the adaptive bypass cavity (9). The bypass secondary flow outlet (8) is connected upstream to the adaptive bypass cavity (9) and downstream to the nozzle throat (7) and the rear expansion section (10). The bypass valve (5) is located at the bypass secondary flow inlet (4) and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity (9).

2. A simplified aerodynamic thrust vectoring nozzle according to claim 1, characterized in that: The outer wall surface (2) of the nozzle has a variable shape to change the shape of the adaptive bypass cavity.

3. A simplified aerodynamic thrust vectoring nozzle according to claim 1, characterized in that: The front converging section (6) is rotatable about the front hinge (3), and the rear expanding section (10) is rotatable about the rear hinge (11) to change the height H of the nozzle throat (7). throat This allows for the adjustment of nozzle flow capacity.

4. A simplified aerodynamic thrust vectoring nozzle according to claim 3, characterized in that: The rotation angle α of the front converging section (6) satisfies 20°≤α≤40°, where α is the angle between the front converging section (6) and the outer wall surface (2) of the nozzle; the rotation angle β of the rear expanding section (10) satisfies 10°≤β≤20°, where β is the angle between the rear expanding section (10) and the outer wall surface (2) of the nozzle.

5. A simplified aerodynamic thrust vectoring nozzle according to claim 3 or 4, characterized in that: The upper and lower sides of the front convergent section (6) can rotate symmetrically or asymmetrically. When the pressure ratio is 4, when only the upper and lower sides of the front convergent section (6) rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°. The upper and lower sides of the rear expansion section (10) can rotate asymmetrically. When the pressure ratio is 4, when only the upper and lower sides of the rear expansion section (10) rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

6. A simplified aerodynamic thrust vectoring nozzle according to claim 1, characterized in that: The nozzle throat (7) is at a height H throat Height H of nozzle inlet (1) in The relationship between them satisfies 0.28 ≤ H throat / H in ≤0.49; The length L1 of the front converging section (6) and the height H of the nozzle inlet (1) in The relationship between them satisfies 0.38 ≤ L1 / H in ≤0.46; The length L2 of the rear expansion section (10) and the height H of the nozzle inlet (1) in The relationship between them satisfies 0.84 ≤ L² / H in ≤0.92; The bypass secondary flow outlet (8) has a height H. bypass Height H of nozzle inlet (1) in The relationship between them satisfies 0.05 ≤ H bypass / H in ≤0.15; The nozzle outlet (12) is at a height H out Height H of nozzle inlet (1) in The relationship between them satisfies 0.65 ≤ H out / H in ≤1.

15.

7. A simplified aerodynamic thrust vectoring nozzle according to claim 1, characterized in that: The structure of the aerodynamic thrust vector nozzle is suitable for Laval nozzles, dual-throat aerodynamic thrust vector nozzles, or axisymmetric fluid thrust vector nozzles.

8. A control method for a pneumatic thrust vectoring nozzle as described in claim 1, characterized in that: Includes the following steps: The front converging section (6) can rotate around the front hinge (3), and the rear expanding section (10) can rotate around the rear hinge (11). By combining the two, the throat area can be adjusted to achieve the adjustment of the nozzle flow capacity.

9. The control method according to claim 8, characterized in that: In the non-vector state, the front converging section (6) and the rear expanding section (10) are rotated synchronously to adjust the height H of the nozzle throat (7). throat This allows for the adjustment of nozzle flow capacity.

10. The control method according to claim 8, characterized in that: In the vector state, the bypass valve (5) works together with the front convergence section (6) and the rear expansion section (10) to simultaneously adjust the thrust vector and flow capacity.

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