A Design Method of Elliptical Throat Offset Pneumatic Vectoring Nozzle

A technology of vector nozzle and design method, applied in machine/engine, jet propulsion device and other directions, can solve the problems that the shape of the circular outlet is not suitable for the flat body, it is difficult to realize the integrated design of the aircraft, and it is difficult to realize the flexible control of the aircraft, etc. Achieve strong air combat advantages, improve infrared stealth performance, and enhance maneuverability and flexibility.

Active Publication Date: 2022-04-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Binary outlet nozzles such as rectangular outlet nozzles have excellent infrared stealth capabilities, but they can only provide vector angles in the pitch direction, making it difficult to achieve flexible control of aircraft; while axisymmetric nozzles can provide omnidirectional vector angles, but their infrared stealth The ability is poor, and the shape of its circular outlet is not suitable for the flat fuselage, so it is difficult to realize the integrated design of the aircraft

Method used

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  • A Design Method of Elliptical Throat Offset Pneumatic Vectoring Nozzle
  • A Design Method of Elliptical Throat Offset Pneumatic Vectoring Nozzle
  • A Design Method of Elliptical Throat Offset Pneumatic Vectoring Nozzle

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Embodiment 1

[0061] Adaptive passive oval throat offset aerodynamic vectoring nozzle for typical configurations.

[0062] Figure 7 Shown is NPR=6, T in the non-vector state 0 * = 300K, b / a=1 and b / a=0.6, the two kinds of dual throat vector nozzle (Dual Throat Nozzle, referred to as DTN) nozzle outlet jet flow along the cross-section flow direction vorticity contour, in which the outlet flow field along the The development direction of the jet flow is a Y-Z plane slice with a set of dimensionless distances X / L=0, 0.5, 1, 1.5, 2.5, and the dimensionless distance X / L represents the ratio of the distance X between the slice and the outlet of the nozzle and the total length L of the nozzle. The figure shows the flow direction vorticity nephogram of the nozzle exit jet slice along the section. The jet exchanges momentum and heat with the ambient gas under the interaction of flow direction vortex and reverse vortex, and the vortex scale gradually decays along the flow direction. Comparing the...

Embodiment 2

[0065] Adaptive passive oval throat offset aerodynamic vectoring nozzle for typical configurations.

[0066] Figure 9 Shown is the elliptical nozzle with short-to-longer-diameter ratios of b / a=1.0, b / a=0.8, b / a=0.6, b / a=0.4 in the non-vector state in the range of falling pressure ratio (NPR) 2-10 Thrust coefficient change curve in . It can be seen that the smaller b / a is, the higher the thrust coefficient is.

[0067] Figure 10 Shown are the elliptical nozzles with short-to-longer-diameter ratios of b / a=1.0, b / a=0.8, b / a=0.6, b / a=0.4 falling in different positions of the bypass channel in the vector state Thrust coefficient variation curve for pressure ratio (NPR) variation. In the figure, long indicates that the bypass channel is arranged in the direction of the long axis of a throat, and short indicates that the bypass channel is arranged in the direction of the short axis of a throat. It can be seen from the figure that, contrary to the results of the non-vector state,...

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Abstract

The invention discloses a design method of an elliptical throat offset type aerodynamic vectoring nozzle. The inner flow path of the elliptical throat offset type aerodynamic vectoring nozzle includes nozzle inlets, equal straight sections, Convergent section at the front of the first throat, first throat, expansion section at the front of the second throat, convergent section at the front of the second throat, and second throat; by designing the shape of the flow section of each section as an ellipse, the flow of the inner runner is changed. Field structure, so it can provide omnidirectional vector angle and ensure high-efficiency vector thrust performance, and has a good mixing effect of internal and external flow, effectively improving the infrared stealth performance of the nozzle, thus solving the problem of strong stealth performance of modern aircraft and high maneuverability; in addition, the unique flat shape of the elliptical throat offset aerodynamic vector nozzle is more suitable for some aircraft with special shapes such as flying wing layout, and can also meet the aerodynamic-stealth integrated layout of future aircraft requirements, a wide range of uses.

Description

technical field [0001] The invention relates to the technical field of thrust vectoring nozzles, and mainly relates to a design method of an elliptical throat offset aerodynamic vectoring nozzle. Background technique [0002] With the development of science and technology and the urgent needs of practical applications, more and more thrust vectoring aeroengines will be used in future aircraft. Traditional mechanical vectoring nozzles are complex in structure, heavy in weight, poor in stealth performance, and difficult to maintain. Therefore, it is necessary to develop a thrust vectoring nozzle with simple structure, light weight and good stealth performance. [0003] At present, the fluid thrust vectoring nozzle has gradually become the research focus and research focus of various countries due to its simple structure and light weight, and will enter engineering applications in the near future. Among them, the throat offset pneumatic vectoring nozzle is a new type of fluid...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/28F02K1/78
CPCF02K1/28F02K1/78
Inventor 成前徐惊雷黄帅潘睿丰张玉琪曹明磊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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