Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Abstract: Systems and methods for manipulating boundary conditions are described, including rendering at least a portion of a model of a mechanical thing. The model includes mesh data and boundary condition data, which may be rendered with contour lines. User input is received indicating changing at least a segment of at least one of the contour lines. The user input may be input using a graphical user interface to produce a graphical representation of a new contour line to replace at least a segment of one of the contour lines. At least the new contour line may be outputted and/or stored as modified boundary condition data to represent the replaced segment.

Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Abstract: A turbine nozzle insert of a gas turbine engine is disclosed. The insert may comprise an elongated hollow body portion, a flange portion formed at a first end of the elongated body portion, and a contact portion formed at a second end of the elongated body portion opposite the first end.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade including a camber-line rib extending radially outward from a tip of the blade and extending from a trailing edge of the blade toward a leading edge. The camber-line rib may form pressure and suction side cooling slots at the tip of the blade. The camber-line rib my include a cooling channel positioned in the camber-line rib and in fluid communication with the at least one cavity forming the cooling system in the blade for cooling aspects of the tip at the trailing edge.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber forming a portion of the cooling system and at least partially defined by the tip wall proximate to the first end. An inner surface of the tip wall may include a plurality of curved bumper protrusions extending from the inner surface radially inward toward the root. The cooling system may include a plurality of ribs generally aligned with the trailing edge, and the curved bumper protrusions may be offset in a chordwise direction relative to the ribs. A throat section may extend between a first forwardmost curved bumper protrusion and a second immediately adjacent downstream curved bumper protrusion and may be offset radially outward from an inner tip surface, thereby creating a first recessed tip slot with a reduced tip wall thickness.

Abstract: A cooling system for a turbine airfoil of a turbine engine having an inflow mid-chord feed channel and a trailing edge feed channel that are separated by an equalizer rib having a plurality of supply holes. The supply holes enable cooling fluids to be supplied to the trailing edge from the mid-chord feed channel to satisfy the cooling requirements of the entire trailing edge, which is greater than the mid-chord region. A crossover hole may be positioned in the equalizer rib at the tip section to enable the cooling fluids to pass between the mid-chord feed channel and a trailing edge feed channel. The crossover hole may enable cooling fluids to pass from the trailing edge feed channel into the mid-chord feed channel along the tip section to reduce stagnation in the outboard turn of the mid-chord serpentine channel.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade including a camber-line rib extending radially outward from a tip of the blade and extending from a trailing edge of the blade toward a leading edge. The camber-line rib may form pressure and suction side cooling slots at the tip of the blade. The camber-line rib my include a cooling channel positioned in the camber-line rib and in fluid communication with the at least one cavity forming the cooling system in the blade for cooling aspects of the tip at the trailing edge.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber forming a portion of the cooling system and at least partially defined by the tip wall proximate to the first end. An inner surface of the tip wall may include a plurality of curved bumper protrusions extending from the inner surface radially inward toward the root. The cooling system may include a plurality of ribs generally aligned with the trailing edge, and the curved bumper protrusions may be offset in a chordwise direction relative to the ribs. A throat section may extend between a first forwardmost curved bumper protrusion and a second immediately adjacent downstream curved bumper protrusion and may be offset radially outward from an inner tip surface, thereby creating a first recessed tip slot with a reduced tip wall thickness.

Abstract: A cooling system for a turbine airfoil of a turbine engine having an inflow mid-chord feed channel and a trailing edge feed channel that are separated by an equalizer rib having a plurality of supply holes. The supply holes enable cooling fluids to be supplied to the trailing edge from the mid-chord feed channel to satisfy the cooling requirements of the entire trailing edge, which is greater than the mid-chord region. A crossover hole may be positioned in the equalizer rib at the tip section to enable the cooling fluids to pass between the mid-chord feed channel and a trailing edge feed channel. The crossover hole may enable cooling fluids to pass from the trailing edge feed channel into the mid-chord feed channel along the tip section to reduce stagnation in the outboard turn of the mid-chord serpentine channel.

Abstract: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal, and exhaust the fluids through a gap between adjacent turbine vanes. The seal may include an elongated cooling channel for channeling cooling fluids from a supply to an exhaust channel at a first end. The cooling system may remove heat from the turbine vane shroud, the seal, and other related components, thereby reducing the likelihood of premature failure.