Spiral type thrust engine

A screw-type engine technology, which is applied in the field of hot gas variable displacement engine devices, can solve the problems of complex engine systems, frequent maintenance, frequent repairs, large quality, and large volume, and achieve the effects of simple structure, low energy loss, and small mass and volume

Inactive Publication Date: 2009-11-11
胡巍
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of thrust engine system will inevitably bring a lot of energy loss due to the matching and transmission of the engine with the transmission, transmission and other systems. The engine system is complex, with large mass and volume, many parts and components, and frequent maintenance and repairs

Method used

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Examples

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Embodiment Construction

[0018] As an embodiment of the present invention, such as figure 1 As shown, a helical thrust engine includes an engine housing 1 and a high-pressure working medium generating device, and also includes a helical thrust generator fixed in the engine housing 1, and the high-pressure working medium generating device is a jet engine Combustion chamber, such as the combustion chamber 3 of the turbojet engine shown in this embodiment. The helical thrust generator is arranged between the combustion chamber 3 and the turbine 5, and the shaft 6 connecting the compressor 4 and the turbine 5 runs through the front and rear end faces of the helical thruster 2 shaft core 2 and is coaxial with it. The helical thrust generator includes a shaft core 2 and a helical blade 21 that is fixed on the side of the shaft core 2 and takes its shaft as the axis of rotation to advance helically along the axial direction from its front end to the rear end, and the inner edge of the helical blade 21 is ali...

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Abstract

The invention discloses a spiral type thrust engine, relating to a hot air variable capacity type engine device. The spiral type thrust engine comprises an engine shell and a high pressure refrigerant generating device, and also comprises a spiral type thrust generator fixedly arranged inside the engine shell. The spiral type thrust generator comprises a core shaft and a spiral blade which is fixedly arranged at the lateral side of the core shaft, takes the shaft as a rotating shaft, goes forward along the axis direction spirally and extends from the front end to the back end of the core shaft. The whole spiral blade forms a spiral type variable capacity quality guide groove which extends from the front end surface to the back end surface of the core shaft and communicates the front end surface with the back end surface on the core shaft, wherein the cross-sectional area of the groove is gradually increased from front to back in equivalent ratio difference and the front opening of the groove is communicated with a refrigerant output end thereof. The invention provides a spiral type thrust engine which adopts a new thrust generating mode, can generate thrust directly and has simple structure, long service life, easy manufacture, low material requirements, low cost and smaller energy consumption.

Description

technical field [0001] The invention relates to a hot gas variable displacement engine device, in particular to a thrust engine device, which is a helical thrust engine which directly converts heat and kinetic energy of high-pressure working medium into engine driving kinetic energy. Background technique [0002] The current thrust engine system is mainly used for vehicles such as aerospace, vehicles and ships that need thrust to advance. [0003] Military aerospace vehicles generally use jet thrust engines due to the requirements of large thrust-to-weight ratio and speed. The working principle of the jet engine is to use fuel combustion to generate high-temperature and high-pressure airflow and inject it backward at a high speed to generate reaction force, that is, thrust forward. To increase the thrust, the temperature and pressure of the jet must be increased, resulting in a large amount of energy loss, which is the fundamental reason why common rockets, missiles and jet...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02G1/00
Inventor 胡巍
Owner 胡巍
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