Gas turbine cooled blade

Details Gas turbine cooled blade Gas turbine cooled blade

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 11/00 (2006.01)

Patent

CA 2266140

Gas turbine cooled blade is constructed without increase in number of parts and man-hour wherein seal air is maintained to lower temperature with heat exchange rate being suppressed and heat transfer rate of cooling medium in cooling passage is enhanced. Of plurality of cooling passages (A, B, C, D, E) provided in blade, first row cooling passage (A) is covered at blade inner and outer peripheries and communicates with second row cooling passage (B) via communication hole (6) and with main flow gas path via film cooling hole (7). Second row cooling passage (B) commu- nicates with blade inner peripheral cavity (10) to form seal air supgly passage. Plurality of ribs (31) are disposed on inner wall of cooling passage (22) with predetermined pitch (P) alternately and inclinedly against cooling medium flow with respective higher end contacting with lower side face of immediate upstream rib at position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22) and average heat transfer rate in cooling passage is enhanced.

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