F - Mech Eng,Light,Heat,Weapons – 23 – R
Patent
F - Mech Eng,Light,Heat,Weapons
23
R
F23R 3/42 (2006.01) F02C 7/12 (2006.01) F02C 7/18 (2006.01) F23R 3/00 (2006.01)
Patent
CA 2288557
Cooling structure of gas turbine combustor in which cooling medium flows through grooves in wall is improved so that adjustment of flow velocity, pressure loss and heat transfer rate of cooling medium flow in the wall becomes possible and cooling effect thereof is enhanced. Wall of combustor tail tube is made in double structure in which outer plate (1) and inner plate (4) are jointed together being lapped one on another. The outer plate (1) has air inlet hole (3) and groove (2) formed therein. The groove (2) is closed by jointing of the inner plate (4) to the outer plate (1). The inner plate (4) has air outlet hole (5) formed therein. The groove (2) communicates with the air inlet hole (3) and the air outlet hole (5). Cross sectional shape of the groove (2) is changed two-dimensionally or three-dimensionally such that width enlarges toward the hole (5) from the hole (3) or depth is constant or changed in tapered form. Cooling air flows into the groove (2) from the air inlet hole (3) of tail tube surface to flow toward both sides along the groove (2) for cooling of the wall. The air is thereby heated to expand to increase flow velocity and pressure loss, but flow passage enlarges toward the hole (5) and flow velocity is suppressed and pressure loss is reduced.
Nishida Koichi
Sato Yoshichika
Mitsubishi Heavy Industries Ltd.
Riches Mckenzie & Herbert Llp
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