In order to generate more power and further increase the thermal efficiency of modern gas turbines, it is crucial to raise the turbine inlet temperature (TIT). On average, the TIT is continuously increased by approximately 20ºC per year and can reach around 1,700ºC for a modern gas turbine. This progress has been made possible, in large part, due to research efforts in the field of materials and alloys that are more resistant to high temperatures. As a result, the operating temperature of the blades has increased from 1,080°C to 1,180°C. Alongside these advancements, cooling techniques have been introduced and evolved into more comprehensive and complex systems. Starting from solid, uncooled blades, we have witnessed the successive development of forced internal convection systems, air film protection devices, and surface treatment methods acting as thermal barriers. Numerous efforts have been made to optimize these different techniques.

Air film cooling is the most commonly used technique in the industry. In such a setup, cold air is supplied from the compressor to the turbine blades. The cold air is expelled through rows of holes in the cascade passage, creating a protective film around the blade. The primary objective of film cooling is to reduce the coolant air flow rate while maintaining minimal aerodynamic losses with high thermal protection. Taking inspiration from previously published research that introduced an upstream ramp just prior to the cooling jet rows, this study introduces a novel ramp design that exhibits excellent cooling performance while minimizing aerodynamic losses. In the The novel geometry, The ramp exhibits a pyramid-like shape positioned upstream, precisely centered between the two adjacent holes focuses but is extended all the way to the hot air inlet.

Key words: Film Cooling, heat transfer, CFD, gas turbine, finite volume.