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Self-adaptive cycle engine with double external ducts

An engine, self-adaptive technology, applied in the direction of machine/engine, jet propulsion, etc., can solve the problems of increased weight, complex structure design and mechanism adjustment, etc., to achieve the effect of maintaining airflow stability

Inactive Publication Date: 2019-09-20
AERO ENGINE ACAD OF CHINA
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

Although this solution can realize the self-adaptive circulation function, it brings about the problems of increased weight, complicated structural design and mechanism adjustment.

Method used

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  • Self-adaptive cycle engine with double external ducts
  • Self-adaptive cycle engine with double external ducts

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Embodiment Construction

[0022] The present disclosure will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific implementation manners described here are only used to explain relevant content, rather than to limit the present disclosure. It should also be noted that, for ease of description, only parts related to the present disclosure are shown in the drawings.

[0023] It should be noted that, in the case of no conflict, the implementation modes and the features in the implementation modes in the present disclosure can be combined with each other. The present disclosure will be described in detail below with reference to the drawings and embodiments.

[0024] The aircraft has different requirements on the performance of the engine under different flight conditions. The disclosure provides a dual-external self-adaptive cycle engine. By adjusting the variable fan system and the adjustable mechanism in the adaptive core machine, t...

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Abstract

The disclosure provides a self-adaptive cycle engine with double external ducts. The self-adaptive cycle engine comprises a fan, a low-pressure turbine, an external-duct jet pipe, a main jet pipe and a core engine, wherein the fan is driven by the low-pressure turbine and comprises a front-section fan and a rear-section fan; the front-section fan is provided with a first external duct, and the rear-section fan is provided with a second external duct and an internal duct; the external-duct jet pipe is arranged at an outlet of the first external duct and used for discharging airflow flowing through the first external duct; the main jet pipe is arranged at an outlet of the internal duct and used for discharging airflow flowing through the second external duct and the internal duct; the core engine comprises a high-pressure air compressor, a combustion chamber and a high-pressure turbine; the high-pressure air compressor is driven by the high-pressure turbine; and the combustion chamber is located between the high-pressure air compressor and the high-pressure turbine.

Description

technical field [0001] The present disclosure relates to the field of aero-engines, in particular to a double-external adaptive cycle engine. Background technique [0002] Many current and future aircraft need to install more efficient propulsion systems with the ability to perform different tasks in a variety of flight states and a wide range of power conditions. This requires the engine to have a large unit thrust in high-speed flight conditions, and to achieve low fuel consumption in low-speed flight conditions. Current conventional turbofan engines do not have this capability. In the low-speed flight state of the traditional turbofan engine, throttling is achieved by reducing the fan and core engine rotor speed, while reducing the engine flow and pressure ratio. This mode of operation limits the full optimization of the specific fuel consumption in the throttling state. The reduction of the engine flow increases the overflow resistance of the intake port and the body ...

Claims

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Application Information

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IPC IPC(8): F02K3/06F02K3/075
CPCF02K3/06F02K3/075
Inventor 牟园伟王奉明
Owner AERO ENGINE ACAD OF CHINA
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