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Throat offset type pneumatic thrust vectoring nozzle with orifice jet

A small hole jet and vector nozzle technology, applied in the direction of machines/engines, jet propulsion devices, etc., to achieve the effect of reducing pressure difference resistance

Active Publication Date: 2021-06-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the double-throat structure of the throat-offset aerodynamic vectoring nozzle, there is a unique concave cavity between the first and second throats, and there is a large convergence angle from the highest point of the concave cavity to the exit, so that the aircraft rear body to the exit section It inevitably converges, and this convergence angle is significantly larger than that of the ordinary Laval nozzle, resulting in a large rear body resistance, so the drag reduction problem of the throat offset aerodynamic vectoring nozzle needs to be solved urgently

Method used

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  • Throat offset type pneumatic thrust vectoring nozzle with orifice jet
  • Throat offset type pneumatic thrust vectoring nozzle with orifice jet
  • Throat offset type pneumatic thrust vectoring nozzle with orifice jet

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Experimental program
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Effect test

Embodiment 1

[0037] see figure 1 and figure 2 , this embodiment provides a throat-offset aerodynamic vectoring nozzle of a small-hole jet, including a nozzle body, and the nozzle body includes a nozzle inlet 1, etc. Straight section 2, a converging section 3 at the front of the throat, a throat 4, an expansion section 5 at the front of the second throat, a convergence section 6 at the front of the second throat, and a second throat 7;

[0038] The first throat 4, the expansion section 5 at the front of the second throat, the converging section 6 at the front of the second throat, and the second throat 7 together form the cavity 10, and a jet is provided on the upper part and the lower part of the front convergence section 6 of the second throat Small hole 9, the central axis of the jet small hole 9 is parallel to the central section of the nozzle body, the jet small hole 9 communicates with the cavity 10 and the external recirculation area, and also communicates with the cavity 10 and th...

Embodiment 2

[0048] see Image 6 , Figure 7 , Figure 8 as well as Figure 9 , this embodiment provides a throat-offset type aerodynamic vectoring nozzle of a small-hole jet. The difference between the pneumatic vectoring nozzle provided in this embodiment and the pneumatic vectoring nozzle provided in Embodiment 1 includes: the front converging section of the throat The upper and lower parts of The small hole arrangement scheme can further reduce the area of ​​the low pressure area, increase the average pressure in the low pressure area, and compensate the pressure in the low pressure area more uniformly. The total area A of the orifice at the exit of the small hole 9 2 , still need to meet: 0.1A th2 ≤A 2 ≤0.15A th2 , and the number of jet holes 9 in the upper part is the same as the number of jet holes 9 in the lower part.

[0049] More specifically, in this embodiment, the orifice area of ​​the outlet of each small jet hole 9 is the same.

[0050] Figure 7 is expressed as a ...

Embodiment 3

[0053] see Figure 10 , this embodiment provides a throat-offset type pneumatic vectoring nozzle of small-hole jet. The difference between the pneumatic vectoring nozzle provided in this embodiment and the pneumatic vectoring nozzle in Embodiment 1 is that in this embodiment, it needs to The installation angle θ is limited. The installation angle θ is the angle between the central axis of the jet hole 9 and the central section of the nozzle body. The installation angle θ satisfies: 0≤θ≤30°. The purpose is to change the installation of the jet hole 9 Angle, forming small hole jets with different angles, further improving the flow field structure of the low pressure return area outside the nozzle, and further reducing the resistance.

[0054] To sum up, in the present invention, by setting the small jet holes 9 to connect the cavity of the nozzle with the external recirculation area, the pressure difference between the inner and outer recirculation areas of the concave cavity is...

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Abstract

The invention discloses a throat offset type pneumatic thrust vectoring nozzle with orifice jet. At least one jet orifice is arranged in each of the upper portion and the lower portion of a front convergence section of a second throat, and the jet orifices are communicated with a concave cavity and an external recirculating zone and are symmetrical along the central section of a nozzle body. The concave cavity and the external recirculating zone are communicated through the jet orifices, self-adaptive orifice jet is formed through the pressure difference between the inner recirculating zone and the outer recirculating zone of the concave cavity, the orifice jet can effectively compensate the pressure of the low-pressure recirculating zone and reduce the pressure difference resistance of the outer wall face of the nozzle, the orifices can generate certain thrust, and the thrust coefficient of the nozzle is improved.

Description

technical field [0001] The invention relates to the technical field of aero-engine thrust vectoring nozzles, in particular to a throat-offset aerodynamic vectoring nozzle of a small-hole jet. Background technique [0002] The next-generation fighter requires the aircraft to have 4S capabilities, that is, super stealth, supersonic cruise, super maneuver and super information superiority; therefore, the requirements for the aircraft exhaust system are also greatly improved, that is, the use of thrust vectoring that is highly integrated with the rear fuselage. The gas system has become an inevitable choice. [0003] Flight-engine integration is the key technology and development trend of future fighter jets, and its core is aircraft-engine aerodynamic integration, structural integration and control integration. As far as aerodynamic integration is concerned, there is a complex expansion wave / shock wave system in the rear body of a high-speed flying aircraft, which will cause t...

Claims

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Application Information

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IPC IPC(8): F02K1/28
CPCF02K1/28
Inventor 潘睿丰徐惊雷黄帅陈匡世张玉琪成前曹明磊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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