Throat offset type pneumatic vectoring exhaust nozzle with saw-tooth-shaped solid tabs at outlet

A vector nozzle and zigzag technology, which is applied in the field of thrust vectoring aero-engine nozzles, can solve problems such as low detectability, and achieve the effects of simple design, reduced flight resistance and large thrust vector angle.

Active Publication Date: 2019-08-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] At present, in order to achieve low detectability, aircraft often use nozzles with asymmetric exit sections, but it is still rare to combine aerodynamic vector nozzles with beaver tails or serrated prongs. Flow along the pressure gradient, the nearly zero pressure gradient flow of the outflow and the low-pressure area generated by the vortex

Method used

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  • Throat offset type pneumatic vectoring exhaust nozzle with saw-tooth-shaped solid tabs at outlet
  • Throat offset type pneumatic vectoring exhaust nozzle with saw-tooth-shaped solid tabs at outlet
  • Throat offset type pneumatic vectoring exhaust nozzle with saw-tooth-shaped solid tabs at outlet

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0038] Example one

[0039] Such as Figure 1-4 Shown is a throat offset pneumatic vectoring nozzle with a sawtooth-shaped solid protrusion at the outlet. It includes a nozzle body. The inner flow path includes nozzle inlet 1, equal straight section 2, and a front convergent throat. Section 3, first throat 4, second throat front expansion section 5, second throat front convergent section 6, and second throat 7, compared to the traditional throat offset pneumatic vectoring nozzle with the same size rectangular outlet In the reference configuration nozzle described later, under the premise that the projected area of ​​the nozzle outlet remains unchanged, the upper and lower wall surfaces downstream of the front convergent section 6 of the second throat are provided with inwardly inclined serrated solid protrusions 8 .

[0040] In this embodiment, the serrated solid protrusion 8 is a single isosceles triangle, and the length of the base of the isosceles triangle is consistent with t...

Example Embodiment

[0043] Example two

[0044] Image 6 Shows the three-dimensional geometric configuration of the present invention with baffles on both sides of the outlet. Compared with the original configuration, this configuration can pass through the baffles on both sides to reduce the flow of airflow to both sides, causing losses, and further improve the nozzle Pneumatic performance.

[0045] Side baffles can be installed symmetrically on both sides of the side wall surface downstream of the front convergent section of the second throat of the nozzle. Under the condition that the detectability is basically unchanged, the thrust performance of the nozzle is further greatly improved, and the vector of the nozzle is slightly increased. performance. The shortest side baffle is kept flush with the top of the solid protrusion, that is, the length of the side baffle is not shorter than the projection of the isosceles triangle of the solid protrusion on the horizontal plane. However, the side baffle...

Example Embodiment

[0047] Example three

[0048] Figure 7 It shows a configuration of the present invention with multiple serrated solid protrusions. The figure shows a double serrated solid protrusion. The number of protrusions can be further increased to improve the aerodynamic performance of the nozzle. At this time, the isosceles triangle sawtooth solid protrusions are still coplanar with the front convergent section of the second throat of the nozzle, and the plane of the median line of the isosceles triangle is consistent with the baseline throat offset pneumatic vector nozzle. If there is only one serrated tab, the length of the base of the isosceles triangle is consistent with the width of the nozzle width wall; if there are multiple serrated tabs, the sum of the length of the base of the isosceles triangle and the width of the nozzle width wall remain the same Consistent.

[0049] In the case of the same exit projection area, the aerodynamic performance of the nozzle with multi-serrated so...

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Abstract

The invention discloses a throat offset type pneumatic vectoring exhaust nozzle with saw-tooth-shaped solid tabs at an outlet. The throat offset type pneumatic vectoring exhaust nozzle comprises an exhaust nozzle body, wherein a flow channel in the exhaust nozzle sequentially comprises an exhaust nozzle inlet, an isometric section, a first throat front part convergent section, a first throat, a second throat front part expanding section, a second throat front part convergent section and a second throat; and the saw-tooth-shaped solid tabs are arranged on upper and lower wall surfaces at the downstream of the second throat front part convergent section and a projection area of the outlet of the exhaust nozzle is not changed. According to the throat offset type pneumatic vectoring exhaust nozzle disclosed by the invention, the saw-tooth-shaped solid tabs which are inclined toward are arranged at upper and lower sides of the outlet; and an infrared stealth function of the exhaust nozzle is improved under the condition that the projection area of the outlet is equal to an original projection area. Compared with a standard throat offset type pneumatic vectoring exhaust nozzle with a rectangular outlet section, the exhaust nozzle provided by the invention can be used for effectively reducing the speed of a flow spraying central line and reducing the length of a core region and noisesthrough reinforcing flow spraying and blending of the outlet; and meanwhile, the exhausting temperature is reduced and the infrared stealth function is improved.

Description

technical field [0001] The invention relates to a throat offset aerodynamic vectoring nozzle with saw-tooth-shaped solid protrusions at the outlet, and belongs to the technical field of thrust vectoring aircraft engine nozzles. Background technique [0002] With the development of science and technology and changes in the air combat situation, modern aircraft have higher and higher requirements for high maneuverability, low detectability and integrated design. On the one hand, the use of thrust vectoring nozzles will become an inevitable choice for future aircraft to improve maneuverability; on the other hand, the use of non-axisymmetric nozzles has become the consensus of aircraft that emphasize low detectability and integrated design. Therefore, a non-axisymmetric nozzle with thrust vectoring function is of great value for future aircraft. [0003] Fluid thrust vectoring nozzle has become a research hotspot in various countries due to its advantages of simple structure an...

Claims

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Application Information

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IPC IPC(8): F02K1/46
CPCF02K1/46
Inventor 潘睿丰徐惊雷黄帅蒋晶晶汪阳生陈匡世
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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