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本文是“斯贝发动机喘振故障试验研究”专题工作的一部分内容。本文着重论述了两个有价值的试验结论: 1.混合排气式涡扇发动机在不同压气机可调静子叶片转角规律下及在加速过程中,低压压气机共同工作线可能变化不大(斯贝发动机就是这样),这与典型的(P.W.公司提供)性能曲线是不相同的,提高了认识。 2.对R.R.公司历年出厂的发动机涡轮导向器叶片(Ⅰ导和Ⅱ导)的调整规律进行了定量分析,找出了规律,对民航内场有实用价值。通过试验研究,发现了喘振发生的部位;明确了斯贝发动机喘振的确切原因;找到了排故的具体途径,试验结果是分析问题的依据。本文对同类民航机种有一定的参考价值。
This article is part of the special work on “Experimental Study on Spey Engine Faults”. This article focuses on two valuable experimental conclusions: 1. Mixed exhaust turbofan engine in different compressor adjustable stator blade angle law and in the acceleration process, low pressure compressor working common line may not change much This is the case with Beckhoff engines.) This is not the same as the typical (PW company) performance curve, raising awareness. The quantitative analysis of R.R. engine turbine governor blade (Ⅰ guide and Ⅱ guide) factory regulation over the years, to find out the law of civil aviation infield has practical value. Through experimental study, the site of surge was found out; the exact reason of Spey’s engine surge was identified; and the specific ways of troubleshooting were found out. The test results are the basis for the analysis of the problem. This article has certain reference value for similar civil aircraft models.