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A low-infrared characteristic nozzle

An infrared and nozzle technology, applied in the direction of jet propulsion devices, machines/engines, etc., can solve problems such as abnormal changes in bypass ratio, achieve the effects of reducing infrared radiation characteristics, reducing visible area, and significant expansion and contraction rate

Active Publication Date: 2021-11-30
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cross-sectional area of ​​the flow is adjusted by the change of the pressure of the bypass airflow, which effectively solves the problem of abnormal changes in the bypass ratio when the S-curved rectangular nozzle with low infrared radiation characteristics is used.

Method used

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  • A low-infrared characteristic nozzle
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  • A low-infrared characteristic nozzle

Examples

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Embodiment Construction

[0029] Embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0030] A low infrared feature nozzle of this embodiment includes connotation 1 and a connotation 2, a connotation 1 body, and an outlet located in the connotation 2, and the flow path between Handan 2 and Connotation 1 Tao, the flow path in the connotation 1 is the connotation flow path, the longitudinal surface of the main part of the connotation 1 and the main part of the Hualin 2 is circular, of which: Connotation 1 main body to the connotation 1 outlet through smooth round rectangle makes the connotation 1 exit There is a certain amount of rectangular outlet, and the outlet end of the connotation 1 is mounted with a telescopic structure 3. The connotation flow path fluid can push the telescopic structure 3, so that it extends, reducing the width of the overall flow, thereby increasing the flow The fluid pressure in the road has forces some of the...

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Abstract

The invention relates to a nozzle with low-infrared characteristics, which includes inner and outer culverts. The main body of the inner culvert and the outlet are located in the culvert of the outer culvert. The flow channel between the outer culvert and the inner culvert is the outer culvert. It is the connotation flow channel, and the longitudinal sections of the main parts of the connotation and exoconclusion are circular, wherein: the connotation main body and the connotation outlet pass through a smooth circle to make the connotation outlet a rectangular outlet with a certain width-to-height ratio, and the connotation outlet end A telescopic structure is installed, and the fluid in the outer culvert channel can push the telescopic structure to protrude, reducing the width of the outer culvert channel, thereby increasing the fluid pressure in the outer culvert channel, forcing part of the flow at the inlet of the outer culvert to flow into the inner part, Passively adjust the bypass ratio of intension and extension. The invention adjusts the cross-sectional area of ​​the flow through the change of the pressure of the bypass airflow, and effectively solves the problem of the abnormal change of the bypass ratio when the S-curved rectangular nozzle with low infrared radiation characteristics is used.

Description

Technical field [0001] The present invention relates to the field of aerospace engine structural design, in particular a ceramic-based turbine rotor structure, and more particularly to a low infrared feature nozzle. Background technique [0002] With the development of infrared characteristics, the infrared stealth demand in the aircraft is gradually increased. Infrared radiation on the 3-5um wave band of the aircraft is mainly derived from aerospace engine high temperature components, including 70% of the infrared radiation of high temperature components. For a turbine, a combustion chamber, and a central cone, a particular aerodynamic and thermal environment is difficult to adopt a cooling measures, so that the infrared radiation characteristics of high-temperature components are blocked by the S-bend nozzle. It is an efficient infrared suppression measures. like figure 1 As shown, after the S-bend nozzle, the tube cavity high temperature member (the left side of the inlet surf...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/82F02K1/06F02K1/15F02K1/78
CPCF02K1/06F02K1/15F02K1/78F02K1/825
Inventor 张勃王治国陈远翔吉洪湖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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