Abstract: Gas turbine engines and methods for reducing spool thrust in a combustor section thereof are provided. The engines include an impeller, a shaft coupled to the impeller, an inner cavity downstream of the impeller, a thrust bearing assembly mechanically coupled to the shaft, a seal assembly having a seal land, and a controller. The controller is configured to detect a loss of oil event to the thrust bearing assembly and, in response, actuate the seal assembly to move the seal land toward a downstream face of the impeller to form a continuous axial seal about the inner cavity, vent gases from the inner cavity to decrease pressure therein to an extent less than an operating gas pressure thereof, and maintain the axial seal and the pressure within the inner cavity and thereby reduce the axial loads on the shaft.

Abstract: Gas turbine engines and methods for reducing spool thrust in a combustor section thereof are provided. The engines include an impeller, a shaft coupled to the impeller, an inner cavity downstream of the impeller, a thrust bearing assembly mechanically coupled to the shaft, a seal assembly having a seal land, and a controller. The controller is configured to detect a loss of oil event to the thrust bearing assembly and, in response, actuate the seal assembly to move the seal land toward a downstream face of the impeller to form a continuous axial seal about the inner cavity, vent gases from the inner cavity to decrease pressure therein to an extent less than an operating gas pressure thereof, and maintain the axial seal and the pressure within the inner cavity and thereby reduce the axial loads on the shaft.

Abstract: Gas turbine engines and methods for reducing spool thrust in a turbine section thereof are provided. The engines include a turbine disk, a shaft coupled to the turbine disk, an inner cavity downstream of the turbine disk, a thrust bearing assembly mechanically coupled to the shaft, a seal assembly having a seal land, and a controller. The controller is configured to detect a loss of oil event to the thrust bearing assembly and, in response: actuate the seal assembly to move the seal land toward a downstream face of the turbine disk to form a continuous axial seal about the inner cavity, supply a pressurized gas to the inner cavity to increase pressure in therein to an extent greater than an operating pressure thereof, and maintain the axial seal and the pressure within the inner cavity and thereby reduce the axial loads on the shaft.

Abstract: Gas turbine engines and methods for reducing spool thrust in a turbine section thereof are provided. The engines include a turbine disk, a shaft coupled to the turbine disk, an inner cavity downstream of the turbine disk, a thrust bearing assembly mechanically coupled to the shaft, a seal assembly having a seal land, and a controller. The controller is configured to detect a loss of oil event to the thrust bearing assembly and, in response: actuate the seal assembly to move the seal land toward a downstream face of the turbine disk to form a continuous axial seal about the inner cavity, supply a pressurized gas to the inner cavity to increase pressure in therein to an extent greater than an operating pressure thereof, and maintain the axial seal and the pressure within the inner cavity and thereby reduce the axial loads on the shaft.

Abstract: A turbine vane airfoil and a turbine nozzle that includes the turbine vane airfoil. The turbine vane airfoil includes an airfoil defining a chamber proximate a surface, and an impingement tube. The impingement tube includes a first wall and a second wall. The first wall defines a plurality of first apertures, and each has a first upstream surface portion opposite a first downstream surface portion. The second wall defines a plurality of second apertures, and each has a second upstream surface portion opposite a second downstream surface portion. Each of the first apertures cooperate with a respective one of the second apertures to direct a cooling fluid onto the surface, and the first downstream surface portion of at least one of the first apertures includes a first point that is collinear with a second point of the second downstream surface portion of the respective one of the second apertures.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at a positive angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet.

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at a positive angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet.

Abstract: A modular man-lift apparatus includes a receiver unit having a trailer attachment along one end, a power winch, and an articulating connector along a distal end. A main shaft assembly is secured to the articulating connector, and a sliding unit having a plurality of opposing wheels is secured to the shaft assembly. A lift basket is secured onto the sliding unit, and a stabilizer unit extends outward from the receiver unit.