Spiral tube heat exchanger suitable for aviation engine

Abstract

A disclosed spiral tube heat exchanger suitable for an aviation engine comprises a mixing chamber and a stainless steel tube bundle; the mixing chamber comprises a first-order mixing chamber and a second-order mixing chamber; the first-order mixing chamber comprises two '-' type circular pipes and two Z-shaped bend pipes; the second-order mixing chamber comprises N circular pipes; two ends of each of a part of circular pipes are respectively communicated with the two '-' type circular pipes, and the other end of each of the two '-' type circular pipes is enclosed; and two ends of each of the other part of circular pipes are respectively communicated with the upper ends of the two Z-shaped bend pipes, and the other end of each of the two Z-shaped bend pipes is enclosed; the stainless steel pipe bundle comprises multiple stainless steel pipes which are spiral pipes, and the stainless steel pipes are arranged in a circular radial manner for forming the stainless steel pipe bundle; and the two parts of the circular pipes are vertically corresponding and are in communication via stainless steel pipes. The spiral tube heat exchanger has the heat exchange efficiency substantially improved compared with the heat exchange efficiency of a common civil tube-bundle heat exchanger. The spiral pipe is capable of avoiding damage to heat exchanger structure and welding spots by absorbing engine self shock and forced shock during practical running of the aviation engine.

Description

technical field [0001] The invention relates to a helical tube heat exchanger suitable for aero-engines, belonging to the technical field of thermal protection for aerospace vehicles. Background technique [0002] With the continuous development of aero turbine engines, the performance requirements are also increasing. From a thermodynamic point of view, the improvement of engine performance is mainly achieved by increasing the pressure ratio of the compressor and the temperature before the turbine. On the one hand, the increase in the boost ratio of the compressor causes the temperature of the high-temperature turbine cooling air drawn from the subsequent stage to rise, and the cooling quality to decline. Under the premise of ensuring the cooling efficiency, it is necessary to increase the cooling air flow rate, which has caused a negative impact on the efficiency of the engine as a whole. On the other hand, when the temperature resistance of high-temperature materials cann...

AI Technical Summary

Problems solved by technology

[0005] In the existing engine structure, by adding an air / air heat exchanger (Russian 31-F) in the outer duct, the engine outer duct air is used to cool the cooling air, and a certain effect has been achieved, but its cooling capacity is small, and The pressure loss of the external air is caused, which affects the overall performance of the engine

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