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A geared turbofan engine with a reversely installed core engine

A turbofan engine and gear transmission technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problems of high and low pressure rotor system matching and noise control difficulties, and achieve improved fan efficiency, simple structure, and reduced coupling vibration level Effect

Inactive Publication Date: 2018-10-26
中航空天发动机研究院有限公司
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AI Technical Summary

Problems solved by technology

For example, the fan of the engine must have sufficient resistance to intake distortion to cope with the low speed boundary layer airflow, and the high bypass ratio requires the engine to have a smaller and more efficient core engine, and the huge fan size is not proportional to the small core engine , making the high and low pressure rotor system matching and noise control more difficult

Method used

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  • A geared turbofan engine with a reversely installed core engine
  • A geared turbofan engine with a reversely installed core engine
  • A geared turbofan engine with a reversely installed core engine

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Embodiment Construction

[0026] See attached picture, image 3 It is a schematic diagram of the layout of the propulsion system on the airframe. The high bypass ratio turbofan engine is arranged behind the wide and flat fuselage, and the air intake is arranged in the way of being buried in the fuselage or close to the surface of the fuselage. The engine can use the high-aspect-ratio wing to reduce drag, and the low-speed boundary layer airflow flowing through the body surface can help the engine improve propulsion efficiency and also help reduce the noise level of the whole machine.

[0027] Figure 4 It is a schematic diagram of the internal structure layout of the engine and the intake and exhaust scheme. The air enters the engine through the fan 1, and after being pressurized by the fan, most of the airflow generates thrust and forms the mainstream, and a small part of the airflow passes through the outer duct 3 to the back of the core engine 4, and then enters from the opposite direction. The b...

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Abstract

The invention relates to an integrated design scheme of an aircraft engine, in particular to a gear drive turbofan engine with a reversely-mounted core machine. According to an existing aircraft layout, power is provided through the turbofan engine adopting a BLI technology, and by means of the layout, the higher requirements on the engine are required; and according to the high duct ratio, it is required that the engine is provided with the core machine which is smaller and more efficient, a huge fan is disproportionate to the small core machine, a high-pressure rotor system is matched with a low-pressure rotor system, and noise control becomes difficult. Therefore, the fan rotor systems are separated from the core machine, the core machine is reversely mounted, and the structural layout manner of the gear drive fan is adopted. By the adoption of the scheme, the gear drive turbofan engine has the beneficial effects that aerodynamic efficiency is high, the structure is simple and portable, the vibration level is low, maintainability is good, and the airworthiness requirements of advanced airliners / transport aircrafts in the future can be well met.

Description

technical field [0001] The invention relates to an integrated design scheme of an aircraft engine, in particular to a gear transmission turbofan engine with a reversely installed core engine. Background technique [0002] High bypass ratio turbofan engines have been widely used as the power system of large passenger aircraft and transport aircraft, and its structural layout has an important impact on the overall performance, airworthiness, installation and maintenance, and operating costs of the aircraft system. In order to meet the high thrust and high propulsion efficiency requirements of future advanced airliners, one of the effective ways is to increase the bypass ratio of the turbofan engine while reducing the airflow velocity entering the engine. By increasing the size of the fan and reducing the size of the core engine, the bypass ratio of the engine can be increased; by using the Boundary Layer Intake (BLI) technology, that is, by sucking in the low-speed boundary la...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K3/06
Inventor 张家瑞朱大明
Owner 中航空天发动机研究院有限公司
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