F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/18 (2006.01)
Patent
CA 2381474
A gas turbine cooled blade wherein: a) sealed air is maintained to a lower temperature suppressing its heat exchange rate; and b) a cooling passage is constructed so as to enhance the average heat transfer rate in the entire cooling passage. Of the plurality of cooling passages (A, B, C, D, E) provided in the blade, the first row cooling passage (A) communicates with a second row cooling passage (B) via communication hole (6) and with the main gas flow path via film cooling hole (7). Second row cooling passage (B) communicates with blade inner peripheral cavity (10) to form a sealed air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined rib-to-rib pitch (P). Each of the plurality of ribs extends from a side end of cooling passage 22 to a position beyond a central portion thereof to be disposed alternately right and left against the cooling medium flow direction. and inclining in mutually opposing directions. The respective higher end of each rib contacts the lower side face of the immediately upstream rib at its one end beyond the central portion of cooling passage 22. At least one of the ribs includes a pin (28) projecting substantially perpendicular to a rib at a predetermined position on a longitudinal axis of the rib and wherein each rib may comprise a plurality of two or more pins being arranged on the rib at a predetermined pitch between pins. High heat transfer rate areas are formed on both side portions of the cooling passage (22) thereby enhancing heat transfer rate in the cooling passage.
Ishiguro Tatsuo
Masada Junichiro
Matsuura Masaaki
Suenaga Kiyoshi
Takeishi Kenichiro
Mitsubishi Heavy Industries Ltd.
Riches Mckenzie & Herbert Llp
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