Small turbine jet engine

Abstract

The invention provides a small turbine jet engine which comprises a compressor component and a combustion chamber component. The compressor component and the combustion chamber component are respectively located an air inlet end and a jet end of the small turbine jet engine. The compressor component comprises a compressor and a turbine, and the compressor and the turbine are integrally designed. By the adoption of the integral design of compressed air turbine blades, difficulty in design is reduced, and machining and assembling of a small structure are benefited; by the adoption of a reversed-flow type combustion chamber, compactness of the overall layout is benefited, dimensions in design are well controlled, and sufficient space is reserved for improving combustion efficiency; besides, the temperature of a whole shafting is effectively lowered due to outside motion of a bearing, overall system reliability is improved, service life is prolonged, requirements on bearing quality is lowered, and overall cost can be beneficially reduced.

Description

technical field [0001] The invention relates to the field of engines, in particular to a micro turbojet engine. Background technique [0002] With the development of aviation technology, aircrafts put forward higher and higher requirements for the performance of the propulsion system. As a main aviation propulsion engine, the turbojet engine has high mechanical efficiency. Among the various rotating machinery currently known, the general In general, turbojet engines are the most efficient. With the diversification of lifestyles, personalization, miniaturization, and lightweight have become inevitable trends in various fields, and micro turbojet engines have also inevitably become a hot topic. [0003] The working principle of the micro-turbine engine is the same as that of the traditional gas turbine engine, and it is mainly composed of a micro-compressor, a micro-turbine, and a micro-combustion chamber. Its basic working process is as figure 1 As shown, first when the en...

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Problems solved by technology

[0005] However, the micro-turbojet engine has a small structural size, and the design of the micro-turbojet engine is not a simple miniaturization of the traditional engine. Because it is one percent of the size of an ordinary aero-engine, its thrust-to-weight ratio has reached an ordinary It is more than a hundred times that of the engine, but the working efficiency of the whole engine is smaller than that of the ordinary engine, because the structural space limits the mechanical loss of the internal gas flow, and the small size of the engine combustion chamber also leads to the phenomenon of low combustion efficiency. The key The processing and assembly of parts are relatively difficult to achieve

At the same time, due to the small structure and relatively large thrust weight, the temperature of the bearing is relatively high, so the bearing is easily damaged and the service life is very short

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