Abstract: An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust.

Abstract: A hollow turbine airfoil includes pressure and suction sidewalls extending in span between a root and tip and extending in chord between opposite leading and trailing edges. The pressure sidewall includes a first pattern of first holes distributed in span and chord over a majority thereof, and a second pattern of different second holes also distributed in span and chord over a minority of the pressure sidewall between the tip and the midspan of the airfoil.

Abstract: A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a funnel-shaped fillet along the pressure side of the airfoil which decreases in size from the leading edge towards the trailing edge. A field of film cooling holes extends through the platform along the fillet for discharging film cooling air.

Abstract: A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.

Abstract: A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.

Abstract: A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a corresponding arcuate fillet which is larger along the pressure side of the airfoil and smaller along the suction side as it varies in size around the leading edge. A film cooling root hole is disposed in the root fillet in flow communication with an internal cooling circuit in the airfoil for discharging cooling air along the fillet for energizing boundary layer flow of combustion gases flowing through the flow passages during operation.

Abstract: A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.

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 turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

Abstract: A turbine nozzle includes a vane joined to opposite inner and outer bands. The inner band includes a pocket adjoining a flange which recesses in part the inner surface of the band. The pocket undercuts the flange to form a notch at the base thereof.

Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges and root and tip. The tip includes squealer ribs extending from a tip floor forming an open tip cavity. The rib along the pressure sidewall has a squared external corner, and a flute extends along the base of the rib at the tip floor.

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. Each circuit includes an inlet channel extending through the dovetail. One of the circuits includes multiple longitudinal channels separated by corresponding perforate partitions each including a row of impingement holes for cascade impingement cooling the inner surface of the airfoil.

Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls spaced apart between opposite leading and trailing edges and interconnected by a plurality of partitions to define first and second independent cooling circuits therein. The cooling circuits have corresponding inlets in a dovetail of the blade and extend through a platform of the blade and through the airfoil to its tip. A common discharge chamber is disposed below the airfoil tip and includes a plurality of outlet holes for discharging cooling air from the circuits.

Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.

Abstract: An outer combustor wall (36) includes an outer support shell (40) surrounding an outer combustion liner (42). The shell (40) includes a first radial aft flange (46), and the liner (42) includes a second radial aft flange (48) axially adjoining the first flange. An annular retainer (50) and seal (62) are joined to the first flange for slidingly trapping the second flange therebetween for thermally floating the liner on the shell.

Abstract: A turbine airfoil includes opposite pressure and suction sides joined together at leading and trailing edges. An outwardly convex nose bridge bridges the pressure and suction sides behind the leading edge, and is integrally joined to a complementary thermally insulating shield spaced therefrom to define a bridge channel. The shield includes the leading edge and wraps laterally aft around the nose bridge along both the pressure and suction sides.

Abstract: A turbine nozzle includes outer and inner bands integrally joined to a doublet of hollow vanes extending radially therebetween. Each of the vanes includes opposite pressure and suction sidewalls extending between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between the bands for receiving an air coolant. The vanes are spaced apart from each other to define a flow passage for channeling hot combustion gases which are bound by corresponding pressure and suction sidewalls of the vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of the vanes facing outboard. The vanes include different cooling configurations to bias more of the coolant to the inboard sidewalls than to the outboard sidewalls.

Abstract: A turbine blade includes an airfoil having an internal cooling circuit with a first flow passage disposed directly behind the leading edge followed by a second flow passage separated therefrom by a corresponding bridge. The bridge includes a row of impingement apertures for cooling the leading edge. The suction sidewall of the airfoil includes a row of diffusion film cooling first holes extending in flow communication with the first passage. The first holes have a compound inclination angle, with a quadrilateral cross section forming a generally teardrop shaped outlet in the convex contour of the suction sidewall.

Abstract: An impingement baffle includes a perforate plate having a pattern of impingement holes. An imperforate deflector is spaced from the plate and is smaller than the plate for deflecting inlet air around the deflector to the holes. The baffle is disposed between a turbine shroud and supporting hanger, and the deflector is disposed between the hanger and the baffle.