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.

Abstract: A turbine blade retention system includes a turbine blade including a blade section and a blade platform on which the blade section is attached, the blade platform including a forward angel wing and an aft angel wing, the forward angel wing including a front blade seal groove, a disk configured to receive a plurality of the turbine blades, the disk including a front disk seal groove and an aft disk seal groove, a front seal plate, and an aft seal plate, wherein the front seal plate is slidably connectable to the turbine blade and the disk via the front blade seal groove and the front disk seal groove, and the aft seal plate is removably connectable to the turbine blade and the disk via the aft disk seal groove and a lower wall formed on the aft angel wing.

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.

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.

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.

Abstract: A turbine blade retention system includes a turbine blade including a blade section and a blade platform on which the blade section is attached, the blade platform including a forward angle wing and an aft angle wing, the forward angle wing including a front blade seal groove, a disk configured to receive a plurality of the turbine blades, the disk including a front disk seal groove and an aft disk seal groove, a front seal plate, and an aft seal plate, wherein the front seal plate is slidably connectable to the turbine blade and the disk via the front blade seal groove and the front disk seal groove, and the aft seal plate is removably connectable to the turbine blade and the disk via the aft disk seal groove and a lower wall formed on the aft angle wing.