In gas turbine engines, film cooling is an essential method for protecting turbine blades from high temperatures. By using this technique, a thin layer of cooler air is created to act as a barrier between the hot gas stream and the blade material by expelling cold air via tiny holes on the blade surface. Given its importance in many industries, a CFD study is conducted, relying on the reference paper entitled “ An experimental study on the improvements in the film cooling performance by an upstream micro-vortex generator”.

Simulation Process

Our model geometry is established from the pressure side of the blade, where the film cooling is applied. Fortunately, a structured grid made out of 146673 cells is produced by proper blocking. The installed jet injects 300K air through the blade surface while it is placed in a scorching hot zone (600K). This is the most crucial application of film cooling on blades to cool down.

Figure 1: 146673 structured cells in a multi-regional domain

Post-processing

The temperature contour demonstrates significant blade surface cooling. Blue to green cooler fluid is pumped along the blade to form a protective film. This cooler layer mixes with the hotter mainline flow (red region) as it flows downstream. Cooling efficiency is strongest near the injection point and decreases down the blade.
Around the blade, the velocity contour shows a complicated flow field. Green to blue indicates reduced velocity at the blade surface where the cooling film is injected. This buffers the blade from the higher-velocity mainstream flow (orange to red). Velocity gradients and contour differences result from the cooling jet and mainstream flow mixing and turbulence.
These findings show that film cooling reduces blade surface thermal burden and alters local flow dynamics. Tu put it in values; the film cooling could keep the blade`s temperature 55 degrees lower.