Abstract: An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114?) defining plugged holes (115) and cooling holes (116) along a radial direction (117). A selective group (314) of the cooling and plugged holes are based on a reduced cooling fluid requirement at the trailing edge (114?) resulting from an improved thermal barrier coating (126). A process (200) is also provided including removing (202) an airfoil from service in a gas turbine engine and adding or improving (204) a thermal barrier coating on the airfoil. The process also includes selectively (206) plugging holes in the airfoil in response to a reduced cooling fluid required through the airfoil as a result of the added or improved thermal barrier coating.

Abstract: An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.

Abstract: An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114?) defining plugged holes (115) and cooling holes (116) along a radial direction (117). A selective group (314) of the cooling and plugged holes are based on a reduced cooling fluid requirement at the trailing edge (114?) resulting from an improved thermal barrier coating (126). A process (200) is also provided including removing (202) an airfoil from service in a gas turbine engine and adding or improving (204) a thermal barrier coating on the airfoil. The process also includes selectively (206) plugging holes in the airfoil in response to a reduced cooling fluid required through the airfoil as a result of the added or improved thermal barrier coating.

Abstract: An apparatus (100) is presented for reducing a temperature gradient (30) of mainstream fluid (118) downstream of an airfoil (112) in a gas turbine engine (110). The apparatus includes a passage (116) in a trailing edge (114) of the airfoil having an inlet (132) and an outlet (134). The apparatus also includes a cooling fluid source (136) coupled to the inlet to transmit cooling fluid into the passage. The apparatus also includes a vortex generator (138) within the passage effective to generate a vortex fluid (140) at the outlet. The outlet is positioned to inject the vortex fluid into the mainstream fluid with sufficient mixing energy to cause a reduced temperature gradient (130) downstream of the airfoil.

Abstract: An apparatus (10) is presented for controlling a boundary layer (30) in a diffusing flow path (14) of a power generating machine (16). The apparatus includes a passage (18) in the power generating machine with an inlet (20) and an outlet (22). The apparatus also includes a fluid source (24) coupled to the inlet to transmit fluid into the passage. The apparatus also includes a vortex generator (26) within the passage effective to generate a vortex fluid (12) at the outlet. The outlet is positioned to inject the vortex fluid into the diffusing flow path of the power generating machine in order to control the boundary layer of the diffusing flow path. An apparatus is also provided to enhance the diffusion of a flow path within a power generating machine.

Abstract: An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.

Abstract: A turbine bucket including an airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 as contained herein wherein the Z values are non-dimensional values from approximately 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by substantially smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined substantially smoothly with one another to form a complete airfoil shape.

Abstract: An apparatus (10) is presented for controlling a boundary layer (30) in a diffusing flow path (14) of a power generating machine (16). The apparatus includes a passage (18) in the power generating machine with an inlet (20) and an outlet (22). The apparatus also includes a fluid source (24) coupled to the inlet to transmit fluid into the passage. The apparatus also includes a vortex generator (26) within the passage effective to generate a vortex fluid (12) at the outlet. The outlet is positioned to inject the vortex fluid into the diffusing flow path of the power generating machine in order to control the boundary layer of the diffusing flow path. An apparatus is also provided to enhance the diffusion of a flow path within a power generating machine.

Abstract: A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation.

Abstract: A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation.

Abstract: A turbine bucket including an airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 as contained herein wherein the Z values are non-dimensional values from approximately 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by substantially smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined substantially smoothly with one another to form a complete airfoil shape.