发明授权
US06280140B1 Method and apparatus for cooling an airfoil 有权
用于冷却机翼的方法和装置

Method and apparatus for cooling an airfoil
摘要:
An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.
信息查询
0/0