Design method of elliptic throat offset type pneumatic thrust vectoring nozzle

A vector nozzle and design method technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve problems such as difficult to realize flexible control of aircraft, difficult to realize integrated design of aircraft, poor infrared stealth ability, etc.

Active Publication Date: 2021-09-10
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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  • Design method of elliptic throat offset type pneumatic thrust vectoring nozzle
  • Design method of elliptic throat offset type pneumatic thrust vectoring nozzle
  • Design method of elliptic throat offset type pneumatic thrust vectoring nozzle

Examples

Experimental program
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Effect test

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 elliptic throat offset type pneumatic thrust vectoring nozzle. An inner flow channel of the elliptic throat offset type pneumatic thrust vectoring nozzle comprises a nozzle inlet, an equal straight section, a first throat front convergence section, a first throat, a second throat front expansion section, a second throat front convergence section and a second throat which communicate in sequence. According to the design method, the flow field structure of the inner flow channel is changed by designing the shape of each section of flow section into an elliptic shape, then a good inner and outer flow mixing effect can be achieved under the conditions of providing an omnidirectional vector angle and ensuring efficient vector thrust performance, and the infrared stealth performance of the spray pipe is effectively improved, so that the urgent requirements of modern aircrafts on strong stealth performance and high maneuvering performance are met; and in addition, the unique flat appearance of the elliptic throat offset type pneumatic thrust vectoring nozzle is more suitable for the aircrafts with special appearances such as flying wing layout, the requirement for the pneumatic-stealth integrated layout of the aircrafts in the future can be met, and the application range is wide.

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 Applications(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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