| 主权项 |
1. An aerofoil component of a gas turbine engine, the component having a longitudinally extending aerofoil portion which spans, in use, a working gas annulus of the engine, the aerofoil portion containing an internal chamber for a flow of coolant, the internal chamber including a helical passage which spirals in a plurality of turns around a support pillar which is hollow and defines a core passage that extends along an axis that extends in a length direction of the aerofoil portion and the support pillar supports walls which define the helical passage such that coolant flows around the support pillar and along the helical passage and the support pillar tapers in a direction of coolant flow. |
