A Throat Offset Pneumatic Vectoring Nozzle with Small Hole 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 differential resistance

Active Publication Date: 2022-01-04
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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  • A Throat Offset Pneumatic Vectoring Nozzle with Small Hole Jet
  • A Throat Offset Pneumatic Vectoring Nozzle with Small Hole Jet
  • A Throat Offset Pneumatic Vectoring Nozzle with Small Hole Jet

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Experimental program
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Effect test

Embodiment 1

[0037] see figure 1 with figure 2 , the present embodiment provides a small-hole jet throat offset aerodynamic vectoring nozzle, including a nozzle body, the nozzle body includes sequentially penetrated and symmetrical along the central section of the nozzle body: nozzle inlet 1, etc. Straight section 2, first throat convergent section 3, first throat 4, second throat expansion section 5, second throat convergent section 6, and 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 a concave cavity 10, and a jet is provided at the upper and lower parts of the converging section 6 at the front of the second throat. A 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 concave cavity 10 and the external backflow area, and also commu...

Embodiment 2

[0048] see Image 6 , Figure 7 , Figure 8 as well as Figure 9 , this embodiment provides a small-hole jet throat offset aerodynamic vectoring nozzle, the difference between the aerodynamic vectoring nozzle provided in this embodiment and the aerodynamic vectoring nozzle provided in Embodiment 1 includes: the converging section at the front of the throat The upper and lower parts of 6 are provided with two small jet holes 9. Specifically, when the number of small jet holes 9 set on the upper or lower part of the converging section 6 at the front of the throat is greater than one, that is, multiple jet holes 9 are used. The small hole layout scheme can further reduce the area of ​​the low-pressure area, increase the average pressure of the low-pressure area, and compensate the pressure of the low-pressure area more uniformly. The total orifice area A of the outlet 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 th...

Embodiment 3

[0053] see Figure 10 , the present embodiment provides a small-hole jet throat offset type pneumatic vectoring nozzle, 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 is required The installation angle θ is restricted, and the installation angle θ is the angle between the central axis of the jet hole 9 and the center section of the nozzle body. The installation angle θ satisfies: 0≤θ≤30°. angle, forming small hole jets with different angles, further improving the flow field structure in the low-pressure recirculation area outside the nozzle, and further reducing resistance.

[0054] In summary, the present invention connects the concave cavity of the nozzle with the external backflow area by setting the small jet hole 9, and utilizes the pressure difference between the internal and external backflow areas of the concave cavity to form an adaptive small hole jet,...

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Abstract

The invention discloses a small-hole jet throat offset type pneumatic vector nozzle. At least one small jet hole is arranged on the upper part and the lower part of the front converging section of the second throat, and the small jet hole communicates with the concave cavity and the external return flow. area, and the jet hole is symmetrical along the central section of the nozzle body. The invention connects the concave cavity and the external recirculation area through the small jet hole, utilizes the pressure difference in the internal and external recirculation area of ​​the concave cavity to form an adaptive small hole jet, and the small hole jet can effectively compensate the pressure of the low pressure recirculation area and reduce the pressure difference on the outer wall of the nozzle Resistance, and the small hole can generate a certain thrust, which improves the thrust coefficient of the nozzle.

Description

technical field [0001] The invention relates to the technical field of thrust vectoring nozzles of aero-engines, in particular to a small hole jet throat offset aerodynamic vectoring nozzle. Background technique [0002] The next generation of fighter jets requires the aircraft to have 4S capabilities, that is, super-stealth, supersonic cruise, super-maneuverability, and super-information superiority; therefore, the requirements for the exhaust system of the aircraft are also greatly increased, that is, the thrust vectoring row that is highly integrated with the rear fuselage Gas system becomes 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 an aircraft flying at high speed, wh...

Claims

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Application Information

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Patent Type & AuthorityPatents(China)
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
OwnerNANJING UNIV OF AERONAUTICS & ASTRONAUTICS