Gas turbine engine component

An internally cooled gas turbine engine component, the component comprising:

• a line of cooling air discharge holes,
• an internal cooling channel disposed forward of and extending substantially parallel to the line of discharge holes,
• an internal feed cavity disposed between the channel and the line of discharge holes for feeding cooling air from the channel to the discharge holes, and
• a plurality of flow disrupting pedestals extending between opposing sides of the feed cavity,
• the pedestals being arranged in a number N of rows, which extend substantially parallel to the line of discharge holes, each row of the number N of rows forming flow inlet angles that vary along the length of the rows,
• a first row of the number N of rows being located closer to an entrance of the feed cavity than an Nth row of the number N of rows,
• remaining rows of the number N of rows being spaced between the first row and the Nth row, and the pedestals being spaced apart from each other within each row,
• the first row defining a flow inlet angle α of a direction of cooling air flow into the first row at one or more radial positions,
• the Nth row defining a flow outlet angle β of the direction of cooling air flow from the Nth row,
• a change in angle φ of the direction of cooling air flow between the rows being defined as φ=(β−α)/N for the one or more radial positions, and
• the pedestals being positioned such that a line extending forward from the centre of each pedestal in the ith row at an angle {α±φ(i−1)} intersects the (i−1)th row at a location which is midway between two neighbouring pedestals of the (i−1)th row, i being an integer from 2 to N,
• wherein each pedestal is positioned such that a plurality of streak lines of cooling air advancing on the pedestals split substantially equally to both sides of each pedestal and then substantially completely recombine downstream of each pedestal.