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A binary nozzle structure for ejecting cold air from the engine compartment

A technology of engine compartment and binary nozzle, which is applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problem of excessive infrared radiation of nozzles, achieve the effects of ensuring stealth characteristics, improving infrared stealth performance, and reducing infrared radiation characteristics

Active Publication Date: 2022-06-07
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of this application is to provide a binary nozzle structure for ejecting cold air from the engine compartment, so as to solve the problem of more infrared radiation of the nozzle in the prior art

Method used

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  • A binary nozzle structure for ejecting cold air from the engine compartment
  • A binary nozzle structure for ejecting cold air from the engine compartment
  • A binary nozzle structure for ejecting cold air from the engine compartment

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Experimental program
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specific Embodiment approach

[0026] As a specific implementation manner, a binary nozzle structure for ejecting cold air from an engine compartment includes a circular turning section 1 , a converging section 2 and an expanding section 3 .

[0027] The inlet end of the rounded square section 1 is a circular structure, the outlet end is linearly reduced along the circular structure, and gradually becomes a square structure, and the size of the inlet is larger than that of the outlet end, and the convergent section 2 is linear from the inlet end to the outlet end. It gradually shrinks to form a throat, and the expansion end increases linearly from the inlet end to the outlet end to form a jet pipe. The outlet of the rounded section 1 communicates with the inlet of the converging section 2 , and the outlet of the converging section 2 communicates with the inlet of the expanding section 3 .

[0028] When the static pressure of the airflow expanding to the nozzle outlet is exactly equal to the external atmosph...

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Abstract

This application relates to the field of aero-engines. It is a binary nozzle structure for ejecting cold air from the engine compartment, including a circular turning square section, a converging section and an expanding section connected in sequence. There is a cooling channel, the outside of the convergent section and the expansion section is provided with an outer cover, and the two sides of the convergence section and the expansion section protrude up and down respectively to form a side wall structure, and the upper and lower sides of the side wall structure are provided with The first ventilation hole, the fourth cooling passage communicated with the first ventilation hole is opened in the side wall structure, and the inlet end of the fourth cooling passage communicates with the cooling passage in the circular section, the cooling in the engine compartment The device can enter into the first vent hole. It has the technical effect of improving the cooling performance of the nozzle and reducing infrared radiation.

Description

technical field [0001] The application belongs to the field of aero-engines, and particularly relates to a binary nozzle structure for ejecting cold air from an engine compartment. Background technique [0002] Stealth capability has become an essential key technology for advanced fighter jets, and the binary nozzle is conducive to the integrated design of the rear fuselage of the aircraft, its profile is conducive to the modification design, and its tail jet is conducive to blending with the external airflow. The advantages of reducing jet infrared radiation and other advantages have been widely studied and applied in countries around the world. Aiming at improving the stealth performance of the binary nozzle, integrating the stealth design concept into the design of the binary nozzle, and designing the structural scheme of the high-stealth binary nozzle is the core idea of ​​the design of the binary nozzle structure scheme. At present, the domestic research on binary vect...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/82
CPCF02K1/822F02K1/825
Inventor 曹茂国马宏宇杜寅威尚守堂叶留增刘帅许羚石岩李季王瑞祥
Owner AECC SHENYANG ENGINE RES INST
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