| 摘要 |
A turbine blade ( 10 ) includes internal channels ( 16 ) which provide a flow passage for a cooling medium to assist in cooling the blade ( 10 ) when in use, wherein the channels ( 16 ) include a plurality of turbulence promoting ribs ( 28, 60, 64, 70 ) mounted on the wall surfaces ( 44, 62, 66, 72 ) thereof. Each rib ( 28, 60, 64, 70 ) comprises two rib portions ( 30, 32 ) joined at one end to form a chevron junction ( 34 ), wherein the chevron junction ( 34 ) defines an angle ( 36 ) of between 80° and 120° and is directed into the flow of the cooling medium through the channels ( 16 ). Each rib portion ( 30, 32 ) of a rib ( 28, 60, 64, 70 ) defines a gap ( 40, 42 ) therein.
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