Internal cooling schemes for blades in a gas turbine engine often are subject to
compromises between increased pressure losses in return for greater levels of heat transfer …

Internal cooling channels with differing aspect ratios are typically found in gas turbine blades
due to the varying thickness of the blade from the leading to trailing edge. These serpentine …

Internal cooling channels with differing aspect ratios are typically found in gas turbine blades
due to the varying thickness of the blade from the leading to trailing edge. These serpentine …

The demand for elevated turbine inlet temperatures in gas turbine airfoils requires the
innovation of advanced internal cooling designs to enhance turbine durability and …

The thermal efficiency of gas turbine engines depends heavily on the cooling performance
of the internal channels of turbine blades. In the present study, the effects of bidirectionally …

Ribbing the internal passages of turbine blades with 45 deg inclined ribs is a common
practice to achieve a good compromise between high heat transfer coefficients and not too …

Convective cooling in a gas turbine blade internal trailing edge channel is often insufficient
at the sharp trailing edge. This study examines convective heat transfer and pressure drop …

An investigation was conducted to assess the thermal performance of W-shaped, 2W-
shaped and 4W-shaped ribs in a rectangular channel. The aspect ratios (W/H) were 2: 1, 4 …

One of the most challenging aspects of gas turbine cooling is the cooling of the first stages of
turbine blades. Here the highest external heat load is seen at the leading edge of the blade …

Numerical results for an internal ribbed cooling channel including a 180° bend with a 2: 1
inlet and 1: 1 aspect ratio outlet channel were validated against experimental results in …