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April 3, 2026Aerospace0 citationsOpen Access

Intelligent Design and Optimization of a 3 mm Micro-Turbine Blade Profile Using Physics-Informed Neural Networks and Active Learning

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YHYizhou HuLZLeheng ZhangSGSirui Gong

Key Points

  • The aim is to develop a framework for the design and optimization of micro-turbine blade profiles to enhance performance while considering fabrication constraints.
  • Parameterization of blade morphology using 22 design variables.
  • Use of a physics-informed neural network surrogate model.
  • Implementation of a two-stage active learning strategy combining KD-tree exploration and residual-based sampling.
  • Multi-objective optimization via Non-dominated Sorting Genetic Algorithm II.
  • Achieved a 38.6% increase in rotational speed of the optimized blade.
  • Retained 75.1% of thrust at an inlet pressure of 0.2 MPa.
  • Validated the optimization framework's effectiveness through experimental results.

Abstract

The design of millimeter-scale micro-turbine blades is challenging due to conflicting requirements: achieving aerodynamic performance while remaining compatible with microfabrication, and exploring high-dimensional morphological design spaces without prohibitive computational cost. To address these challenges, this study proposes an intelligent framework for the design and optimization of the three-dimensional blade profile of a 3 mm diameter micro-turbine. The blade morphology is parameterized using 22 variables, ensuring geometric feasibility for micro-EDM (Electrical Discharge Machining) fabrication. A physics-informed neural network (PINN) surrogate model, efficiently trained through a two-stage active learning strategy combining KD-tree exploration and residual-based sampling, provides accurate predictions of flow fields. Multi-objective optimization using Non-dominated Sorting Genetic Algorithm II (NSGA-II) is then performed to maximize torque and thrust. Experimental results show that the optimized blade achieves a 38.6% increase in rotational speed while retaining 75.1% of thrust at 0.2 MPa inlet pressure, validating the framework’s effectiveness. This methodology offers a systematic solution for designing microfluidic devices characterized by high-dimensional parameters and high-fidelity simulation requirements.

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Cite This Study

Hu et al. (2026) studied this question.

synapsesocial.com/papers/69cf5ebc5a333a821460d46bhttps://doi.org/10.3390/aerospace13040331
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