A Throat Offset Pneumatic Vectoring Nozzle with Internal S-Bend

A vector nozzle and throat technology, applied in the field of advanced thrust vector nozzles, can solve the problems of complex structure, troublesome maintenance, poor reliability, etc., and achieve the effect of widening the working envelope, good applicability, and reducing the reflection cross-sectional area

Active Publication Date: 2021-09-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

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.

Method used

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  • A Throat Offset Pneumatic Vectoring Nozzle with Internal S-Bend
  • A Throat Offset Pneumatic Vectoring Nozzle with Internal S-Bend
  • A Throat Offset Pneumatic Vectoring Nozzle with Internal S-Bend

Examples

Experimental program
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Effect test

Embodiment

[0048] The calculation is carried out for the typical configuration of the throat offset aerodynamic vectoring nozzle with inner S-bend and its control method.

[0049] Figure 5 show is Figure 4 The performance curves of the thrust vector angle of the three nozzle configurations as a function of the working drop pressure ratio. where curve A corresponds to Figure 4 The central cone configuration of the solid line in the curve B corresponds to Figure 4 The dotted line in the central cone configuration, curve C corresponds to Figure 4 Nozzle configuration without central cone.

[0050] It can be seen that the central cone of the solid line and the central cone of the dotted line are quite different in the shape of the head, and its influence on the performance of the nozzle is also obvious. The thrust vector angle performance of the dotted center cone is the worst. After optimizing the profile of the nozzle head, the thrust vector angle performance has been significant...

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PUM

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Abstract

The invention discloses a throat offset aerodynamic vectoring nozzle with an inner S-curve. The inner passage includes a nozzle inlet, an equal straight section, a converging section at the front of the throat, a throat, and a second throat. The expansion section at the front of the second throat, the convergent section at the front of the second throat, and the second throat (nozzle outlet), and a spindle-shaped center Cone, by using a special-shaped central cone, the concave cavity of the traditional throat offset aerodynamic vectoring nozzle is changed into a symmetrical S-curved channel, which can shield the engine turbine blade cascade and the inner channel in the front of the nozzle, and Supplemented with a specially optimized nozzle rear body surface, the low detectability of the nozzle can be significantly improved under the premise of ensuring that the thrust vector performance does not drop significantly; further, by controlling the front and rear movement of the central cone, the nozzle outlet can be realized. The adjustment of the area expands the use envelope of the nozzle and improves the flow stability under low working pressure ratio.

Description

technical field [0001] The invention relates to a throat offset aerodynamic vectoring nozzle with an inner S-curve, and belongs to the technical field of advanced thrust vectoring nozzles of aero-engines with radar stealth in mind. Background technique [0002] With the development of science and technology and the improvement of actual needs, low detectability and high maneuverability have gradually become important assessment indicators and evaluation criteria for the next generation of military aircraft. [0003] To achieve high maneuverability, thrust vectoring aeroengines have become an indispensable component. 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. [0004] At present, the fluid thrust vectoring nozzle has gradually become the research focus and research focus of various co...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/78F02K1/06
CPCF02K1/06F02K1/78
Inventor 黄帅徐惊雷俞凯凯汪阳生蒋晶晶潘睿丰陈匡世宋光韬
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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