A multi-fan super bypass ratio turbine thrust system

A bypass ratio and multi-fan technology, applied in the field of multi-fan ultra-large bypass ratio turbine thrust system, can solve the problems of reducing aircraft flight speed, increasing engine noise, and low durability, so as to achieve large operating margin and improve bypass ratio. ratio, low emission effect

Inactive Publication Date: 2016-08-24
SHANGHAI JIAO TONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this technology has the disadvantages of reducing the flight speed of the aircraft, greatly increasing the engine noise, and relatively low durability.

Method used

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  • A multi-fan super bypass ratio turbine thrust system
  • A multi-fan super bypass ratio turbine thrust system
  • A multi-fan super bypass ratio turbine thrust system

Examples

Experimental program
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Embodiment

[0045] Such as Figures 1 to 3 Shown, the multi-fan ultra-large bypass ratio turbine propulsion system of the present invention mainly consists of 2 low-pressure compressors 21, high-pressure compressors 22, combustion chambers 23, high-pressure turbines 24, intermediate turbines 25, power turbines 26, and main nozzles 28. Gas turbine-generator mechanism unit 2 composed of generator 27; 15 motor-fan propulsion units 3 composed of fan 31, motor 33 and outer nozzle 34; 2 INVERTER frequency converters 1; conductive cable 4, fuel out book The pipeline 5 and the liquid hydrogen storage tank 6 are composed. The gas passes through the compressor and the combustion chamber to generate high-temperature and high-pressure gas, which then drives the power turbine to work. This part of energy can generate electric energy by driving the motor 27 , or directly generate thrust through the main nozzle 28 . The generated electric energy is transmitted to the motor 33 through the frequency con...

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PUM

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Abstract

The invention relates to a multi-fan turbine thrust system with an ultra-large bypass ratio, wherein the system includes frequency converters (1), flue gas turbine-electric generator units (2), motor-fan propulsion units (3), an electric conductive cable (4), a flue transmission pipeline (5) and a liquid fuel storage tank (6); the flue gas turbine-electric generator units (2), the frequency converters (1) and the motor-fan propulsion units (3) are connected successively by the electric conductive cable (4); the liquid fuel storage tank (6) is connected with the flue gas turbine-electric generator units (2) through the fuel transmission pipeline (5); a gasification partial pipeline of the fuel transmission pipeline (5) is arranged on the motor-fan propulsion units (3). Compared with the prior art, the system has the advantages that the ultra-high bypass ratio of an engine is achieved in a large civil passenger plane, and at the same time, has the advantage that the weight and the gas intake area are effectively reduced.

Description

technical field [0001] The invention relates to a propulsion system of a wide-body civil aviation passenger aircraft, in particular to a multi-fan ultra-large bypass ratio turbine thrust system. Background technique [0002] The high bypass ratio turbofan engine is currently the most widely used aeroengine for large aircraft. Increasing the bypass ratio of a turbofan engine is the most effective way to reduce the fuel consumption rate of an aeroengine, but this will lead to a substantial increase in the weight and volume of the engine. For an aircraft, the increase in the weight of the engine will directly reduce the load capacity of the aircraft; the increase in the volume of the engine will reduce the ground clearance of the aircraft, thereby affecting the work of the aircraft landing gear. Therefore, the development trend of the next generation of civil aeroengines is to increase the engine bypass ratio without increasing the weight and intake area. [0003] The two mai...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C6/20F04D25/08B64D27/02
CPCY02T50/40
Inventor 刘程远斯夏依滕金芳
Owner SHANGHAI JIAO TONG UNIV
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