Design technique of swept and bowed axial compressor

To increase the pressure ratio is the key for future fuel-efficient turbofan engines, and the compact light-weight high-capacity axial compression system has always been the focus. Composite swept bending, with a low aspect ratio which can efficiently control the supersonic flow losses and flow separation at substantial turning angles, remains the core of high-capacity design exploration. Based on a forward-swept rim-driven fan, we develop a whole new design method of low aspect ratio and 3D swept, centering on the alignment of flows in high-capacity two-stage fan supersonic segments. The refinement of one-dimensional and two-dimensional characteristic models is accomplished according to test results. Optimization techniques are employed to establish a performance alignment protocol that spans all operational scenarios, effectively verified through empirical experiments. To further elevate performance, the study pioneers the concept design and experimental verification of low aspect ratio cascaded blade front-stage deceleration compression and rear-stage turning compression. Validation through numerical simulations confirmed the dynamic blade adsorption within a self-recirculation system. Ultimately, the paper discusses the challenges in designing highly efficient, fully supersonic dynamic blades, especially within variable-flow Flade configurations. It also explores the complex management of low-loss supersonic flow along the annular inner wall and the potential integration of flexible blades and smart materials in shape design methodologies.