A Throat Offset Pneumatic Vectoring Nozzle with a Serrated Solid Tab at the Outlet

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 type aerodynamic vectoring nozzle with a sawtooth-shaped solid protrusion at the outlet, which belongs to the technical field of thrust vectoring aeroengine nozzles. Background technique [0002] With the development of science and technology and the changes in the air combat situation, modern aircraft have an increasing demand for high maneuverability, low detectability and integrated design. On the one hand, the use of thrust vectoring nozzles will become the inevitable choice for future aircraft to improve maneuverability; on the other hand, the use of non-axisymmetric nozzles has become a consensus for aircraft that emphasize low detectability and integrated design. Therefore, non-axisymmetric nozzles with thrust vectoring function are of great value to future aircraft. [0003] The fluid thrust vectoring nozzle has become a research hotspot in various countries due to its simple structure and light weight. Among...

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 in the concave cavity, it is necessary to take into account the enhanced mixing of the mainstream and the outflow caused by the flow direction vortex generated by the airflow passing through the serrated solid protrusions and the intensified mixing effect in the concave cavity. Efficient rotation of vortex with full three-dimensional motion effect

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