| 摘要 |
An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: determining anglesαandβof the directions of cooling air flow into the first and Nth rows, respectively; defining a change in angleφof the direction of cooling air flow between rows asφ=(β−α)/N; and positioning the pedestals 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. |
