| CPC F01D 5/187 (2013.01) [F05D 2230/21 (2013.01); F05D 2250/11 (2013.01); F05D 2260/20 (2013.01)] | 14 Claims |
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1. An aerofoil for a gas turbine engine, the aerofoil comprising a suction side wall, a pressure side wall, a leading edge and a trailing edge, the suction side wall and the pressure side wall extending from a first end to a second end and meeting to define the leading edge and the trailing edge; wherein the suction side wall and pressure side wall further comprise cooling passages extending in a radial direction with respect to a central/longitudinal axis of the aerofoil within the wall thickness of the aerofoil walls, the cooling passages comprising hollow triangular passages, wherein the hollow triangular passages further comprise roughened or dimpled inner surfaces,
wherein the hollow triangular passages are defined by first, second and third adjacent walls, wherein a length of the first adjacent wall is located to face a hot surface of the aerofoil, wherein the first adjacent wall has a longer length relative to respective lengths of the second and third adjacent walls,
wherein for a given cross-sectional area of the cooling passage, a ratio of the length of the first wall relative to a perimeter of the cooling passage is chosen to promote heat transfer between the hot surface of the aerofoil and the first wall while inhibiting pressure loss when a coolant flows through the cooling passage.
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