Cooling arrangement for a combustion chamber

摘要

A cooling arrangement for a surface of a wall in a gas turbine engine, the wall having a plurality of effusion holes each with an outlet onto the surface for supplying an effusion flow to the surface and an inlet, the inlets of the effusion holes being arranged at the peripheries of groups tessellated on an opposing surface of the wall, each inlet being located on the peripheries of three groups. The arrangement comprises a second wall spaced apart from the opposing surface having impingement orifices each for directing a flow of air in use to a respective impingement location on the opposing surface, each group having a centrally positioned impingement location.

主权项

1. A cooling arrangement for a gas turbine, comprising:
a surface of a wall of the gas turbine, the wall having a plurality of effusion holes arranged in groups tessellated on the surface, the outlet of each effusion hole being located on a periphery of three groups; wherein each group has the shape of an irregular hexagon having two axes of reflective symmetry and four sides of equal length and two sides of a shorter length.