Wall-bounded turbulent flow simulation is essential in aerospace engineering, offering critical aerodynamic data for aircraft design. Due to the high Reynolds number nature of such flows, the hybrid Reynolds-averaged Navier–Stokes (RANS)/large eddy simulation (LES) method is seen to be the most promising way under computational cost constraints. Conventional hybrid methods typically employ artificial shielding functions to prevent LES from improperly intruding into the boundary layer, avoiding issues such as grid-induced separation and log-layer mismatch. However, this forces the use of RANS within the boundary layer even when the local grid is sufficiently refined for LES, thereby limiting the resolution of the hybrid method. To improve the resolution of the hybrid method, a new RANS/LES hybrid approach has been presented, allowing LES to reasonably enter the boundary layer. This approach classifies the flow field into three zones based on local turbulence resolution: RANS region, poor LES region, and fine LES region. In the poor LES region, modelled turbulent stress is properly offset by a Reynolds stress and subgrid-scale stress relation. This enables a seamless global transition between RANS and LES without relying on artificial shielding functions. A numerical validation of the new hybrid RANS/LES method for wall-bounded turbulent flow simulation is investigated in plane channel and boundary layer turbulent flows. Results demonstrate that the method effectively avoids log-layer mismatch while capturing turbulent structures in the inner boundary layer.