Non axi-symmetric shaped cooling liner within a gas turbine engine exhaust duct

摘要

A cooling liner (24) having a liner hot sheet (26) is formed as a relatively thick iso-grid structure having iso-grid ribs (34), which extend from a surface between the ribs (34). A multitude of metering sheets (38) are mounted directly to the liner hot sheet surface. Each metering sheet (38) is mounted to the iso-grid to define a multitude of discrete chambers (40). A seal (42) is located in a pattern along a subset of the iso-grid ribs (34) to further segregate the surface covered by each metering sheet (38) into a further number of discrete subchambers (40'). Each metering sheet (38) includes a multitude of metering sheet apertures (44) and the surface between the iso-grid ribs (34) of the liner hot sheet (26) include a multitude of hot sheet apertures (46). By varying the ratio between the number of metering sheet apertures (44) and the number of hot sheet apertures (46), the pressure in each chamber (40) is defined to efficiently maintain the minimum desired pressure ratio across the hot sheet (26) without undue wastage of cooling airflow.