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Throat offset type pneumatic vector spraying pipe with parallelogram section

A parallelogram, vector nozzle technology, applied in the directions of machines/engines, jet propulsion devices, etc., to achieve the effect of reducing flight resistance and being widely used

Active Publication Date: 2019-05-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The inner and outer surfaces (including the rear body) of the active nozzles are both binary up-down symmetry or ternary axisymmetric. elliptical, etc.) will be used more and more, however there are very few non-axisymmetric nozzles with thrust vectoring capabilities

Method used

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  • Throat offset type pneumatic vector spraying pipe with parallelogram section
  • Throat offset type pneumatic vector spraying pipe with parallelogram section
  • Throat offset type pneumatic vector spraying pipe with parallelogram section

Examples

Experimental program
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Effect test

Embodiment

[0034] Calculations are performed for a typical configuration of a parallelogram cross section passive type throat offset aerodynamic vectoring nozzle.

[0035] Figure 7 Shown is the vector angle data of the parallelogram section nozzle with the inclination angle of α=45°, α=60°, α=67.5°, α=75° in the vector state in the range of falling pressure ratio (NPR) 2-10 . It can be seen that the smaller the α angle, the pitch vector angle tends to decrease. Therefore, the selection of α is advisable to be 60°-75°.

[0036] Figure 8 Shown is the vector angle data of the parallelogram cross-section nozzle with α=60° configuration in the vector state under different conditions of the average throat width-to-height ratio (W / H). It can be seen that within the range of aspect ratio 1.2-9.6, the pitch vector angle increases gradually with the increase of the first throat aspect ratio. The selection of the average width-to-height ratio of the first throat is preferably 2.4-4.8, and consi...

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Abstract

The invention discloses a throat offset type pneumatic vector spraying pipe with a parallelogram section. A spraying pipe inner runner comprises a spraying pipe inlet, an equal straight segment, a first-throat front convergent section, a first throat, a second-throat front expanding segment, a second-throat front convergent section and a second throat which communicate in sequence; an inclined side wall face begins to be arranged on a certain position in the inner runner, the circulation section from the inner runner to the second throat is in a parallelogram shape, through the shape design ofthe parallelogram circulation section, the good airflow mixing effect is obtained, the spraying pipe infrared hidden property is effectively improved, meanwhile, the large thrust vector angle is provided for an aircraft still, the inclined side wall face has the offset effect on the airflow, under the vector and non-vector state, the initial pitching and yaw vector angles exist, the requirement of pneumatic-hidden integrated layout of the future aircraft can be met, and the purpose is wide.

Description

technical field [0001] The invention relates to an aerodynamic vectoring nozzle with a parallelogram cross-section and an offset throat, belonging to the technical field of thrust vectoring aeroengine nozzles. Background technique [0002] With the development of science and technology and the improvement of actual demand, more and more thrust vectoring aeroengines will be used in future aircraft. The core of the thrust vectoring aeroengine to realize the thrust vectoring function is the thrust vectoring nozzle. The traditional mechanical thrust vectoring nozzle has complex structure, poor reliability and troublesome maintenance. Therefore, it is imminent to develop a thrust vectoring nozzle with simple structure, light weight and good maintainability. [0003] At present, the fluid thrust vectoring nozzle has gradually become the research focus and research hotspot of various countries due to its simple structure and light weight, and will be put into engineering applicat...

Claims

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Application Information

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IPC IPC(8): F02K1/00F02K1/82
Inventor 蒋晶晶徐惊雷黄帅汪阳生陈匡世汪丰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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