Abstract: A method facilitates fabricating an airfoil for use with a turbine blade. The method comprises forming a substantially solid ceramic airfoil core, inserting the core into a die and casting the airfoil with a pressure side wall and a suction side wall connected together at a leading edge and a trailing edge, such that a plurality of first trailing edge slots and at least one second trailing edge slot extend from the trailing edge along the pressure side wall, wherein the second trailing edge slot has a length, measured between an inlet and an exit of the slot, that is longer than a corresponding length of each of the plurality of first trailing edge slots.

Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.

Abstract: A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.

Abstract: A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. A first serpentine circuit is disposed along the pressure sidewall. A second serpentine circuit is disposed along the suction sidewall in parallel with the first circuit. And a third impingement circuit is disposed at the leading edge forward of the first and second circuits.

Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and atrailing edge, such that a cavity is defined therebetween. A plurality of rib walls extends at least partially between the first and second sidewalls, wherein the plurity of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.

Abstract: A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

Abstract: A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.

Abstract: A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.

Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.