航空发动机卡箍装配应力试验与装配参数控制方法

Clamp assembly stress test of aero-engine and assembly parameter control method

通过理论公式推导分析影响卡箍装配应力的主要参数,并通过试验方法对影响卡箍装配应力的因素进行了系统分析与研究,以3种规格、每种规格5个样本的卡箍作为试验对象,测试并统计分析螺栓拧紧力矩值、加载次数、装配方法对卡箍的应力影响规律。研究结果表明:靠近螺栓孔的卡箍表面为应力集中位置,卡箍随加载次数的增多应力呈降低趋势,但重复加载次数不宜过多,会导致卡箍局部较大的变形和磨损,增加2 mm垫片的方法对降低卡箍应力水平的效果最好,下降率可达46.8%;相比之下,限制卡箍位移后加载的方法应力下降率约为3.64%,而加载后校正的方法应力下降率约为2.86%。

The main parameters affecting the assembly stress of clamps were derived through theoretical formulas and analyzed.Further more,the factors affecting the assembly stress of the clamps were systematically analyzed and researched by test method.In the test,the effects of bolt tightening torque,loading times,and assembly plans on the stress of the clamps were tested and statistically analyzed by using 3 types of clamps with 5 samples of each type as the test object.According to the research results,the surface of the clamp near the bolt hole was a stress concentration position.The stress of the clamp decreased with the increase of loading times,but the repeated loading times should not be too much,otherwise the local area of the clamp had large deformation and wear.The test results also showed that the method of adding a 2 mm gasket had the best effect on reducing the stress level of the clamp,and the reduction rate can reach 46.8%.In contrast,the reduction rate was 3.64%and 2.86%respectively by means of loading after restricting the displacement of the clamp and the method of correction after loading.