Abstract: Shock wave-boundary layer interaction (SWBLI), a typical flow phenomenon observed in critical components of high-speed flight vehicles such as control surfaces and inlets, induces adverse effects including flow separation and reattachment and localized enhancement of aerodynamic forces and heat loads, which severely compromise the vehicle's aerodynamic performance. The shear stress transport (SST) k-ω turbulence model, which is widely adopted in current industrial applications, behaves strong predictive capabilities in equilibrium boundary layers. However, it exhibits significant limitations when applied to shock-wave/boundary-layer interaction flows with strong adverse pressure gradients. Through a comparative analysis of direct numerical simulation data for 24° compression ramp flow, it was observed that the original SST model underestimates both the turbulent kinetic energy (TKE) and its production term near the corner. To address this problem, a novel pressure-gradient-dependent adjustment function, dynamically activated within shock interaction regions while maintaining original behavior in other zones, was incorporated into original SST model. It enables a localized adaptive correction of the TKE transport equation near interaction regions. The improved SST model was rigorously validated using several cases, including flows over compression ramps and oblique shock wave impingement on flat plates interaction with varying intensities. The results indicate that the improved SST model maintains consistent predictive accuracy for boundary layer properties compared to the original one, while significantly enhancing the prediction of wall skin friction, pressure distribution, and separation bubble characteristics in the vicinity of the interaction