Countercurrent tangential type micro turbojet engine

Abstract

The invention discloses a countercurrent tangential type micro turbojet engine. The countercurrent tangential type micro turbojet engine comprises a rotor system, a shell, a flame tube, a diffuser, a turbine guider, a fuel supply system, a lubricating system, a starting gas path and an exhaust system, wherein for the overall direction of the entire device, the position of the diffuser is defined as the left end direction of the entire device, the position of the turbine guider is defined as the right end direction of the entire device, by taking the rotor system as the center, the diffuser is fixed at the front end of the rotor system, the turbine guider is fixed at the right end of the rotor system, the exhaust system is positioned at the right end of the turbine guider, the flame tube is concentric with the rotor system and contains the rotor system, the fuel supply system and the starting gas path are fixed on the wall surface of the outer side of the flame tube, and the lubricating system is fixed on the outer side of the rotor system, positioned between the inner side of the flame tube and the rotor system and fixed with the shell of the micro turbojet engine through the diffuser and the turbine guider. The countercurrent tangential type micro turbojet engine reduces the pollutant discharge, and can effectively reduce the carbon deposition of the flame tube, so that the working life of the engine is prolonged.

Description

technical field [0001] The invention belongs to the field of aircraft power systems, and in particular relates to a reverse-flow tangential micro turbojet engine, in particular to a micro turbojet engine which obtains high combustion efficiency by increasing the swirl effect of gaseous fuel. Background technique [0002] At present, the commonly used micro-turbojet main air flow channel often uses T-type or Γ-type evaporator tubes as fuel atomization and evaporation devices. Among them, the T-shaped evaporating tube is mixed with the air ejected from the spoiler, and the Γ-shaped evaporating tube is mixed with the air from the small holes of the matching air cup to create the air mixing conditions suitable for combustion. Both of these two fuel supply methods require fuel to be atomized under the action of gas, and special air supply systems or components are required. The fuel sprayed from the fuel pipeline often hits the wall of the flame tube, and generates carbon black ...

AI Technical Summary

Problems solved by technology

French-made JPX T240xing micro-turbojet engine that runs on propane (C 3 h 8 ) as a fuel, which is not conducive to use and is more dangerous

Fig. 2 is a miniature turbojet engine designed by US005782079A. This engine uses a V-shaped stabilizer as a flame stabilizing device, but increases the flow resistance in the engine, and uses a centripetal turbine, which is heavy in weight and has a heavy thermal load on the turbine, which affects the life of the engine.

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