| Citation: | DONG Shaojing, FANG Yufan, HU Wentong, et al. Prejudgment method of tenon structure in aero-engine preliminary design stage[J]. Journal of Aerospace Power, 2022, 37（11）：2362-2375 doi: 10.13224/j.cnki.jasp.20220356
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In order to adapt to the range of non-orthogonal parameters caused by the self-constrained parametric modeling method, a mapping method was proposed to map the sampling points of the traditional orthogonal design space to the non-orthogonal space. A feasible domain boundary identification method based on machine learning logistic regression was constructed to judge the compliance of the sample space response with relevant criteria. This method was applied to a high pressure turbine two-/ three-tooth tenon structure, finding that an engine preliminary design scheme may fail to meet the design requirements in the detailed design phase of tenon structure, and tenon structure parameters may be advanced to the preliminary design stage, together with the superior parameter design, to prevent the design difficulties in the detailed design stage. Through the boundary identification method, it was found that when the speed was reduced to 15 575 r /min or the outer diameter of the wheel was reduced to 303 mm, the two-tooth tenon structure can be designed. When the speed was reduced to 15 584 r /min or the outer diameter of the wheel was reduced to 301 mm, the three-tooth tenon structure can be designed. This method can be used as an iterative feedback information among various disciplines in the initial engine design stage. The proposed method can be generalized to other details of the engine structure design.
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