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External parallel fan turbine engine and application thereof in field of flying wing aircrafts

A turbine engine and main engine technology, which is applied in the aerospace field, can solve the problems of difficult integration of turbofan engines and flying wing aircraft, and achieve the effects of improving propulsion efficiency, increasing bypass ratio, and large bypass ratio

Inactive Publication Date: 2019-07-26
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a turbofan engine with an external parallel fan and its application in the field of flying-wing aircraft to solve the technical problem that the existing high bypass ratio turbofan engine and flying-wing aircraft are difficult to integrate

Method used

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  • External parallel fan turbine engine and application thereof in field of flying wing aircrafts
  • External parallel fan turbine engine and application thereof in field of flying wing aircrafts
  • External parallel fan turbine engine and application thereof in field of flying wing aircrafts

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Embodiment Construction

[0028] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways as defined and covered below.

[0029] figure 1 It is a schematic diagram of the structure of the fan turbine engine according to the preferred embodiment of the present invention.

[0030] like figure 1 As shown, the external parallel fan turbine engine of this embodiment includes a main engine assembly 1, a ducted fan assembly 2 and a bevel gear transmission assembly 3, the main engine assembly 1 is a turboshaft engine or a turboprop engine, and two sets of ducted fans The assembly 2 is symmetrically placed on both sides of the main engine assembly 1, and the power turbine shaft 106 of the main engine assembly 1 is arranged in parallel with the fan shaft of the ducted fan assembly 2. The bevel gear transmission assembly 3 includes the main engine built-in bevel gear transmission ass...

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Abstract

The invention discloses an external parallel fan turbine engine and application thereof in the field of flying wing aircrafts. The external parallel fan turbine engine comprises a main engine assembly, bypass fan assemblies and a bevel gear transmission assembly; the main engine assembly is a turboshaft engine / turboprop engine; the two or more sets of bypass fan assemblies are symmetrically and externally arranged on the two sides of the main engine assembly; a power turbine shaft of the main engine assembly and fan rotary shafts of the bypass fan assemblies are arranged in parallel; the transmission assembly comprises a main engine built-in transmission assembly and bypass fan built-in transmission assemblies; and the main engine assembly is connected with the bypass fan assemblies through the transmission assembly. Compared with conventional turbofan engines, the high bypass ratio design of the external parallel fan turbine engine can be achieved under a small engine height dimension, fuel consumption can be reduced, and the external parallel fan turbine engine is suitable for providing propulsion power for the flying wing aircrafts as blended wing bodies and is a power device with great potential for the new generation of passenger aircrafts with blended wing bodies.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular, to an external parallel fan turbine engine. In addition, the present invention also relates to the application of the above-mentioned external parallel fan turbine engine in the field of flying wing aircraft. Background technique [0002] The fan of a traditional turbofan engine is on the same axis as other rotating parts of the engine, such as the high-pressure compressor and turbine. For turbofan engines, the larger the bypass ratio (outer bypass flow / inner flow), the lower the engine fuel consumption. Therefore, the bypass ratio of modern advanced civil turbofan engines is getting larger and larger, resulting in an increasingly larger diameter of the fan. For example, the diameter of the GE90NX engine is as high as 2.7 meters, and the diameter of the Trent XWB engine is as high as 3 meters. Further As a result, the integration design of the engine and the aircraft is becomin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/06F02C7/36
CPCF02C7/36F02K3/06
Inventor 谢买祥
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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