Novel thermoelectric circulation combined engine

An engine and turbojet engine technology, applied in the field of aero-engines, can solve the problems of insufficient utilization efficiency of engine thermal energy and unavailability of waste heat, and achieve the effects of improving thermal efficiency and fuel utilization rate, improving energy utilization efficiency, and simplifying turbine structure

Active Publication Date: 2018-11-06
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problems of insufficient thermal energy utilization efficiency of existing engines and a large amount of waste heat that cannot be utilized, and to provide a thermoelectric cycle combined engine, which can improve the cycle thermal efficiency and propulsion efficiency of the engine

Method used

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Embodiment 1

[0024] Combined thermoelectric cycle engines, such as figure 1 As shown, on the basis of the existing TBCC engine structure, increase the drive motor 2 for the turbojet engine, that is, increase the drive motor 2 in the turbojet engine; the drive motor 2 is placed in the combustion chamber 9; the drive motor 2 acts on The fixed connection shaft connecting the compressor 5 and the turbine 6; the driving force required by the compressor 5 is provided by the turbine 6 alone and becomes jointly provided by the turbine 6 and the drive motor 2 . The thermoelectric conversion material 1 is installed on the outlet wall of the nozzle of the turbojet engine to recover the waste heat of the nozzle and help the nozzle to dissipate heat, such as Figure 4 As shown; install thermoelectric material 1 at the front of the aircraft to recover the aerodynamic heat generated by the high-speed flight of the aircraft; install thermoelectric conversion material 1 at the outlet of the overall tail of...

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Abstract

The invention relates to a turbojet engine, in particular to a thermoelectric circulation combined engine and belongs to the field of aero-engines. According to the thermoelectricity circulation combined engine, on the basis of the existing TBCC engine structure, a thermoelectric conversion device is utilized to convert the afterheat and waste heat generated by the tail gas of a spray pipe when the engine works or aerodynamic heat on the surface of an aircraft into electric energy through the thermo-electric effect, and a novel thermoelectric circulation engine utilizes the generated electricenergy to drive a gas compressor through a mechanical / electric mixing turbine. When the flight Mach number of the aircraft is lower and the engine is under the turbojet operating modal, a thermoelectric conversion system provides electric power to (unit) drive the gas compressor; and when the flight Mach number of the aircraft is higher, the gas compressor stops working, and the engine enters thestamping operating modal.

Description

technical field [0001] The invention relates to a turbojet engine, in particular to a thermoelectric cycle combined engine, which belongs to the field of aeroengines. Background technique [0002] With the continuous improvement of aerospace technology in various countries, the requirements for aircraft engines are becoming higher and higher. A single type of power form cannot fully meet the needs of the current space-to-earth transportation system that is fast, cheap, free to travel to and from space, and hypersonic vehicles. Mission flight requirements. At present, conventional propulsion systems mainly include rocket engines, turbine engines, ramjet engines and so on. Among them, although the working height and speed of the rocket engine can cover the entire range, because it needs its own fuel and oxidant, the specific impulse is much smaller than that of the traditional air-breathing engine; although the specific impulse of the turbine engine is higher than that of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/00F02K7/16F02K1/82H02K7/14
CPCF02K1/82F02K3/00F02K7/16H02K7/14
Inventor 闫东峰谢侃陈江魏志军王宁飞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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