Abstract: A gas turbine engine turbine blade shrouded tip has an airfoil tip with a cross-sectional airfoil shape, a blade tip shroud attached to the tip, and a shroud cooling circuit disposed within the blade tip shroud. The shroud cooling circuit is operable for cooling substantially all of the shroud and is in fluid communication with a hollow interior of the tip. One embodiment of the invention includes two circumferentially extending forward and aft seal teeth on a radially outer shroud surface of the shroud extending in a radial direction away from the hollow interior of the tip. The shroud cooling circuit includes circumferentially extending shroud cooling passages between clockwise and counter-clockwise shroud side edges of the shroud. Forward and aft pluralities of the shroud cooling passages within the tip shroud are in fluid communication with first and second cavities respectively in the hollow interior.

Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of substantially rectangular segments positioned such that circumferential gaps between adjacent centerbody segments align alternatively with and between carburetors positioned in the inner and outer domes.

Abstract: A turbine nozzle includes a vane integrally joined between outer and inner bands, with the inner band having a purge hole for discharging a portion of cooling air channeled through the vane. A checkvalve is provided in the purge hole for preventing backflow therethrough into the vane. In an exemplary embodiment, the checkvalve allows a reduction in cooling air through the vane at low power operation for increasing efficiency while preventing backflow of combustion gases into the purge hole.

Abstract: A hollow impingement baffle includes a septum extending between its bottom and top and spaced between its forward and aft edges to define a forward manifold and an aft manifold. The baffle includes an inlet having a forward portion for channeling a first portion of compressed air to the forward manifold, and an aft portion for channeling a second portion of the compressed air into the aft manifold with a predetermined pressure drop for obtaining a lower pressure in the aft manifold relative to a higher pressure in the forward manifold. The baffle includes impingement holes for discharging the compressed air against the inner surface of a surrounding airfoil for the impingement cooling thereof.