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在×××航空发动机压气机定型试验中,我们设计了五点普朗特管,安装在进口截面的畸变网络之后。此处工作条件比较恶劣,要求却很严格,希望准确可靠无干扰。它与其它探针一起,成功地测出了有处理机匣的压气机特性线、沿叶高的总静压分布以及临界畸变角。在寻找实壁机匣压气机的临界畸变角、喘振到138次时(净喘振共414次),发生了根部焊缝的疲劳断裂,在当前探针的疲劳寿命难以给出的条件下,又在连续喘振的恶劣条件中,此探针经受了如此大的考验,实在是一次理论上难以得到的宝贵数据和经验积累。
In the ××× Aeroengine Compressor Steering Test, we designed a five-point Plano tube that was installed after the distorted network of the inlet cross-section. Here the working conditions are harsh, the requirements are very strict, hope accurate and reliable without interference. Together with the other probes, it successfully measures the compressor characteristic line, the total static pressure distribution along the blade height, and the critical distortion angle of the casing with the casing. In looking for the critical distortion angle of the solid casing compressor, the fatigue fracture of the root welds occurred when the surge was 138 times (net surging 414 times) and the fatigue life of the current probe was hard to give , And again in the harsh conditions of continuous surge, this probe has withstood such a great test, it is a theoretically difficult to get valuable data and experience accumulation.