F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/18 (2006.01)
Patent
CA 2381484
A gas turbine cooled blade is constructed without an increase in number of parts or time requirements, in which seal air is maintained at a lower temperature with heat exchange rate being suppressed and heat transfer rate of cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at blade inner and outer peripheries and communicates with second row cooling passage (B) through communication holes (6) and with main flow gas path through film cooling holes (7). Second row cooling passage (B) is separated from the first row cooling passage (A) by a partition wall, and is closed at the inner peripheral side. Second row cooling passage (B) has at least one communication hole in the partition wall for allowing communication between an interior of the second row cooling passage and the interior of the first row cooling passage. At least one seal air passage (C, D or E) arranged downstream of the second row cooling passage has a seal air supply hole at the inner peripheral side for allowing communication between an interior of the seal air passage (C, D or E) and an inner cavity of the turbine adjacent to the inner peripheral side.
Ishiguro Tatsuo
Masada Junichiro
Matsuura Masaaki
Suenaga Kiyoshi
Takeishi Kenichiro
Mitsubishi Heavy Industries Ltd.
Riches Mckenzie & Herbert Llp
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