Flat tube fin air-oil heat exchanger suitable for aero-engine

Abstract

The invention discloses a flat tube fin air-oil heat exchanger suitable for an aero-engine. The flat tube fin air-oil heat exchanger comprises a first annular header pipe, a second annular header pipe and a plurality of porous flat tube assemblies. The second annular header pipe and the first annular header pipe are coaxially arranged in a spaced mode in the front-back direction, and the second annular header pipe is located in front of the first annular header pipe; the multiple porous flat pipe assemblies are spaced in the circumferential direction and arranged in a radial mode to form an annular column shape, the multiple porous flat pipe assemblies communicate between the first annular header pipe and the second annular header pipe in parallel, and therefore aviation kerosene enters the first annular header pipe from the oil inlet, flows through the multiple porous flat pipe assemblies and then converges in the second annular header pipe, and the aviation kerosene is discharged from the oil outlet and finally enters a combustion chamber to be combusted, and the high-temperature and high-pressure air skims over and is cooled from front to back in gaps between the porous flat pipe assemblies to cool hot end components of the aero-engine. The flat tube fin air-oil heat exchanger is compact in structure, good in heat exchange effect and wide in application range, and meanwhile the energy utilization rate is increased.

Description

technical field [0001] The invention relates to the technical field of aero-engine cooling, in particular to a flat tube-fin air-oil heat exchanger suitable for aero-engines. Background technique [0002] To increase the efficiency and thrust of an aeroengine, the cooling of the engine is crucial. With the further improvement of the engine performance requirements, the engine is required to have a higher temperature before the turbine and a larger boost ratio. A larger boost ratio means that the cooling quality of the high-pressure air used for cooling is reduced, and the engine hot-end components According to the statistics of technical data, the temperature in front of the turbine increases by an average of 22K each year, among which the average annual temperature is 8K due to the improvement of temperature-resistant materials, and the remaining 14K is solved by heat transfer workers. of. Cooling technology is of great significance to improve the cycle efficiency of aero...

AI Technical Summary

Problems solved by technology

The heat exchanger arranged on the aero-engine has restrictions on the volume and weight of the heat exchanger, so the commonly used civilian heat exchanger cannot be directly applied to the aero-engine

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