Enhanced film cooling system
AssigneeDoosan Heavy Industries Construction Co., Ltd
InventorRonald RUDOLPH
Life of this patent
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Abstract
A turbine blade in an industrial gas turbine includes a blade surface to be cooled by a film of cooling fluid, a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion, and a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole, wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.
Claims19
A turbine blade in an industrial gas turbine, comprising:
- a blade surface to be cooled by a film of cooling fluid;
- a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion;
- and
- a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole,
- wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.
A turbine, comprising:
- a rotating shaft;
- and
- one or more turbine blades connected to the rotating shaft, each turbine blade including:
- a blade surface to be cooled by a film of cooling fluid;
- a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion;
- and
- a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole,
- wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.
A masking apparatus for a turbine blade in an industrial gas turbine, comprising:
- a base configured to fit over a tip of the turbine blade;
- and
- one or more masking arms extending from the base in a radial direction and configured to cover a plurality of cooling holes formed on a surface of the turbine blade to form a trench surrounding the plurality of cooling holes.
Dependencies are inferred from the claim text.