TY - JOUR
T1 - Flow mechanism-embedded deep learning for modeling geometric uncertainty effects on aerodynamic stability
AU - Guo, Zhengtao
AU - Zhang, Guobin
AU - Li, Chaolong
AU - Bao, Lei
AU - Gao, Xianzhong
AU - Chu, Wuli
N1 - Publisher Copyright:
© 2026 Elsevier Masson SAS.
PY - 2026/12
Y1 - 2026/12
N2 - Aerodynamic stability is a critical prerequisite for designing the next generation of high-load aero-compressors that achieve both high performance robustness and superior aerodynamics. However, the aerodynamic stability of compressors is highly vulnerable to manufacturing-induced geometric uncertainties, which significantly degrade the surge margin under off-design conditions. To efficiently quantify this complex relationship, the study proposes a novel Flow Mechanism-Informed Neural Network (FMINN) framework. The FMINN incorporates the axial momentum ratio of tip leakage flow directly into the hidden layers of a deep neural network, thereby embedding flow physics into the learning process. Geometric uncertainties are modeled based on actual blade measurements from a multi-axis rotary overspeed measurement system. Through Principal Component Analysis, high-dimensional scan data are reduced to a compact set of interpretable components without sacrificing essential geometric information. The FMINN outperforms traditional surrogate models with sparse geometric training samples, delivering an order-of-magnitude lower relative error than conventional neural networks and adaptive polynomial chaos expansions. Applied to an 8-stage axial compressor working at a medium‑to‑high design rotational speed, FMINN-based uncertainty quantification reveals a pronounced non-Gaussian distribution in stability margin variation, indicating a 1.14% probability of severe aerodynamic degradation. Further sensitivity analysis using Shapley Additive exPlanations quantifies how key geometric deviation features independently and interactively influence aerodynamic stability in a nonlinear manner. Flow mechanism analysis further reveals how specific deviations propagate uncertainties into the flow field. The findings of this study aim to drive the intelligent transformation of aero-compressor design from an “experience-driven” to a “model-driven” paradigm.
AB - Aerodynamic stability is a critical prerequisite for designing the next generation of high-load aero-compressors that achieve both high performance robustness and superior aerodynamics. However, the aerodynamic stability of compressors is highly vulnerable to manufacturing-induced geometric uncertainties, which significantly degrade the surge margin under off-design conditions. To efficiently quantify this complex relationship, the study proposes a novel Flow Mechanism-Informed Neural Network (FMINN) framework. The FMINN incorporates the axial momentum ratio of tip leakage flow directly into the hidden layers of a deep neural network, thereby embedding flow physics into the learning process. Geometric uncertainties are modeled based on actual blade measurements from a multi-axis rotary overspeed measurement system. Through Principal Component Analysis, high-dimensional scan data are reduced to a compact set of interpretable components without sacrificing essential geometric information. The FMINN outperforms traditional surrogate models with sparse geometric training samples, delivering an order-of-magnitude lower relative error than conventional neural networks and adaptive polynomial chaos expansions. Applied to an 8-stage axial compressor working at a medium‑to‑high design rotational speed, FMINN-based uncertainty quantification reveals a pronounced non-Gaussian distribution in stability margin variation, indicating a 1.14% probability of severe aerodynamic degradation. Further sensitivity analysis using Shapley Additive exPlanations quantifies how key geometric deviation features independently and interactively influence aerodynamic stability in a nonlinear manner. Flow mechanism analysis further reveals how specific deviations propagate uncertainties into the flow field. The findings of this study aim to drive the intelligent transformation of aero-compressor design from an “experience-driven” to a “model-driven” paradigm.
KW - Deep learning
KW - Flow mechanism-informed neural network
KW - Multi-stage compressor
KW - Shapley additive explanations
KW - Uncertainty quantification
UR - https://www.scopus.com/pages/publications/105046354633
U2 - 10.1016/j.ast.2026.113198
DO - 10.1016/j.ast.2026.113198
M3 - 文章
AN - SCOPUS:105046354633
SN - 1270-9638
VL - 179
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 113198
ER -