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 …

Numerical investigations of a two-pass internal cooling channel with engine representative
cross-sections related to turbine blade cooling were conducted. The channel consisted of a …

Gas turbine blades are usually cooled by using ribbed serpentine internal cooling passages
which are fed by extracted compressor air. The individual straight ducts are connected by …

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 …

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 …

Gas turbine blades are usually cooled by using ribbed serpentine internal cooling passages,
which are fed by extracted compressor air. The individual straight ducts are connected by …

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 …

Internal channel cooling is employed in advanced gas turbines blade to allow high inlet
temperatures so as to achieve high thrust/weight ratios and low specific fuel consumption …

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 …