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建立了较完整的涡轮盘疲劳寿命评估流程,并以一个涡轮转子模型的分析实例给出了寿命评估流程的实施过程,同时探索了涡轮盘考核部位模拟试验件设计的方法。结果表明:所建立的涡轮盘寿命评估流程具有较强的工程实用性,所发展的寿命方程参数确定方法可有效利用现有材料手册中各种材料基础试验数据并能获得一组物理意义明确的参数,此寿命方程预测的寿命精度在2倍分散带之内;通过涡轮盘计算分析发现应力梯度是影响涡轮盘中心孔、螺栓孔边以及过渡圆角等部位寿命的关键因素,需在设计过程中重点关注;通过带缺口的平板模型算例模拟了涡轮盘危险部位的应力梯度特征,实现试验件缺口部位的应力梯度与涡轮盘考核部位的相对梯度特征接近,并提供了缺口模拟试验件设计方法,为使用简单缺口试验件评估涡轮盘考核点的寿命提供了技术途径。
A more complete turbine disk fatigue life assessment process is established. The implementation process of the life assessment process is given based on an example of a turbine rotor model. Meanwhile, the design of the simulation test part for the turbine disk inspection site is explored. The results show that the established turbine disk life assessment process has strong engineering practicability. The developed life equation parameter determination method can effectively utilize the basic test data of various materials in the existing material manual and obtain a set of data with clear physical meaning The life span predicted by this life equation is within 2 times of the dispersion zone. Through the calculation and analysis of the turbine disk, it is found that the stress gradient is the key factor that affects the life of turbine disk center hole, bolt hole edge and transition fillet. The stress gradient of the dangerous part of the turbine disk was simulated by the example of the plate model with notches, the stress gradient at the notched part of the test piece was close to the relative gradient of the test part at the turbine disk, and the design of notched simulation test piece Method, which provides a technical approach for evaluating the service life of turbine disk test points using a simple notched test piece.