| 摘要 |
A first stage turbine blade for an industrial gas turbine engine, the blade includes a row of exit slots along the trailing edge region of the blade to provide cooling. The exit slots are separated by ribs that also form diffusers in the slots. Each slot includes a constant metering inlet section followed by a diffuser section. The top most exit slot adjacent to the blade tip includes a rib angled at around 20 degrees toward the tip. The slots below the top most slot have ribs that are angled at around 15 degrees, then 10 degrees, and then 5 degrees before ending with the last slot in the group with a rib angled at zero degrees. The remaining exit slots below the tip group have ribs with ends that taper at from 3 degrees to about 7 degrees to form the diffusers.
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