초록 ▼

A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the in

A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

대표청구항 ▼

[ What is claimed is:] [1.]1. An airfoil, comprising:an internal cavity;an external wall;at least one cooling air passage disposed in said external wall, said passage having a plurality of segments connected in series by at least one turn, wherein said passage segments each have a length over diamet

[ What is claimed is:] [1.]1. An airfoil, comprising:an internal cavity;an external wall;at least one cooling air passage disposed in said external wall, said passage having a plurality of segments connected in series by at least one turn, wherein said passage segments each have a length over diameter ratio equal to or less than 20;wherein one of said passage segments includes an inlet aperture connecting said passage to said internal cavity, and another of said passage segments includes an exit aperture connecting said passage to a region outside said airfoil; andwherein cooling air within said internal cavity may enter said passage through said inlet aperture and exit said passage through said exit aperture.