Abstract: Shock wave-boundary layer interaction (SWBLI), as a typical flow phenomenon observed in critical components of high-speed flight vehicles such as control surfaces and inlets, induces detrimental effects including flow separation and reattachment, as well as localized enhancement of aerodynamic forces and heat loads, which severely compromise the vehicle's aerodynamic performance. Currently, the Reynolds-Averaged Navier-Stokes approach remains the primary numerical simulation method in industrial applications. However, the widely adopted Shear Stress Transport k-ω (SST) turbulence model, originally developed for equilibrium flows, exhibits significant deviations in regions with strong adverse pressure gradients and non-equilibrium transport characteristics within shock-dominated zones. Through comparative analysis of direct numerical simulation data for 24° compression ramp flow, this study reveals that the standard SST model underestimates turbulent kinetic energy and its production term near the corner. To address this limitation, we propose a novel pressure-gradient-dependent modulation function integrated into the TKE transport equation. This function is specifically activated within shock interaction regions while maintaining baseline behavior in other zones, aiming to selectively amplify TKE near interference areas and enhance model prediction capability for SWBLI. The improved SST model was rigorously validated using several cases, including compression ramp and oblique shock impingement on a flat plate interaction with varying intensities. Results demonstrate that the modified model retains the boundary layer prediction accuracy of the standard SST model, while achieving significant improvements in predicting key parameters such as wall skin friction, wall pressure, and the location of separation bubble in the vicinity of interaction regions.