Gas turbine blade
AssigneeDoosan Heavy Industries Construction Co., Ltd
InventorsKi Don Lee, Seok Beom Kim
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Abstract
A gas turbine blade according to an embodiment of the present invention includes a turbine blade provided in a gas turbine; and a plurality of film coolers formed in a section from a leading edge to a trailing edge of the turbine blade, in which the film cooler includes a cooling channel through which cooling air is introduced and formed in an oval shape; and an outlet through which the cooling air passing through the cooling channel is discharged and extending from an extended end of the cooling channel toward an outer side thereof and formed in an oval shape.
Claims13
A gas turbine blade including an airfoil formed between a leading edge and a trailing edge of the turbine blade and a plurality of film coolers formed in an outer surface of the airfoil, each film cooler comprising:
- a cooling channel through which cooling air is introduced;
- an outlet extending from one end of the cooling channel to the outer surface of the turbine blade;
- and
- a guide disposed in a width change portion of the film cooler where a width of the film cooler changes from a width of the cooling channel to a width of the outlet that is wider than the width of the cooling channel, the width change portion consisting of a cooling channel portion occupying a first region of the film cooler next to the outlet and an outlet portion occupying a second region of the film cooler next to the cooling channel,
- wherein the guide has a plate shape having straight sides respectively contacting opposite inner walls of the cooling channel and a concavely curved face configured to guide a direction of the cooling air entering the first region such that the cooling air entering the first region is guided into the second region and is guided outwardly in a width direction of the width change portion.
Dependencies are inferred from the claim text.