| 摘要 |
A gas turbine engine aerofoil 21 is provided with a linear cooling air passage 38 interconnecting the hollow aerofoil interior 33 with its exterior surface 39. The passage 38 is generally normal with respect to part of the surface 41 defining the hollow aerofoil interior 33 local thereto. Blockage of the cooling air passage 38 by airborne particulate material is thereby substantially avoided. The passage entrance may be formed in a protection (46) supporting an air inlet tube (43) (Figure 4) or a flared recess (49) or channel (52) (Figures 5 and 6). There may be a plurality of passages. <IMAGE>
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