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目前国内外的宇航运载器上,大多采用线圈式(亦称蛇形管或螺旋管式)换热器,其结构设计并不甚难,但传热的理论计算,由于影响因素甚多,则与试验值相差较大,较好的理论计算误差也要达20～30％,有的甚至更大,故只能通过试验进行调整。本文翻译的目的,试图扩大有关设计者的眼界,以便在理论计算和设计方面有所裨益。本文是从《换热器设计手册》中摘译的,考虑到本文的独立性和完整性,该手册中凡是与本文有关的主要部分,都尽量译出附后,以便查阅。个别地方因涉及的篇幅太多,又基本上不影响本文的完整性,就未译出。读者如感兴趣,请查阅原文。
At present, aerospace vehicles at home and abroad mostly adopt the coil type (also known as a serpentine tube or a spiral tube type) heat exchanger, and its structural design is not difficult, but the theoretical calculation of heat transfer due to many influencing factors, And test values vary greatly, the better the theoretical calculation error should reach 20 ~ 30%, and some even larger, it can only be adjusted by the test. The purpose of this translation is to try to broaden the horizons of the designers involved in order to benefit from theoretical calculations and design. This article is excerpted from the “Heat Exchanger Design Manual”, taking into account the independence and integrity of this article, all of the relevant parts of this manual are as far as possible attached, for easy reference. In some places due to the space involved too much, but basically does not affect the integrity of this article, it has not been translated. Readers interested, please see the original.