Bearing cooling structure of small turbojet engine

Abstract

The invention discloses a bearing cooling structure of a small turbojet engine. A first fuel nozzle is arranged on an oil inlet pipe, a second fuel nozzle is arranged on an oil return pipe, a plurality of air guiding holes and a plurality of choke holes are formed in a bearing support, the choke holes are right opposite to a bearing, and a labyrinth sealing structure is arranged between the bearing support and a main shaft. The labyrinth sealing structure is located on the left side of the air guiding holes, the main shaft is provided with a plurality of first flow guiding holes, a plurality of second flow guiding holes and a third flow guiding hole, the first flow guiding holes and the second flow guiding holes extend in the radial direction of the main shaft, the third flow guiding hole extends in the axial direction of the main shaft, and the first flow guiding holes are located in the left side of the bearing. The multiple second flow guiding holes are located in the right side of the bearing, the multiple first flow guiding holes and the multiple second flow guiding holes communicate with the third flow guiding hole, and a flow guiding ring is further fixedly arranged on the main shaft. The bearing cooling structure has the advantages that the bearing can be lubricated and cooled, fuel oil can be preheated, and the combustion chamber efficiency is improved.

Description

technical field [0001] The invention relates to a bearing cooling structure, in particular to a bearing cooling structure of a small turbojet engine. Background technique [0002] At present, small turbojet engines are mainly developed in the direction of high thrust-to-weight ratio, low cost, and simple and reliable structure. The lubricating oil lubrication system for small turbojet engines usually includes lubricating oil tank, lubricating oil pump, oil filter and complex air sealing system, which greatly increases the weight, manufacturing cost and design difficulty of small turbojet engines. Moreover, setting such a complex lubricating oil lubrication system in the relatively limited space of the small turbojet engine will restrict the design of other components. [0003] As we all know, no matter what kind of support method is used for small turbojet engines, due to the influence of heat transfer and radiation of high-temperature components (that is, the turbine struc...

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Problems solved by technology

[0004] Small turbojet engines operating at high altitudes must face the problem of low fuel temperature. The internal space of small aero-engines is limited, and the heat transfer distance of fuel pipelines in small aero-engines is short, which cannot fully preheat the fuel before combustion, resulting in The te

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