Abstract: A system and method for detecting integrity of a position for a mover in an independent cart system, includes receiving multiple first position feedback signals at a first processing core and receiving multiple second position feedback signals at a second processing core. Each of the first and second position feedback signals are generated by first and second position sensors, respectively, by detecting a magnet array mounted on the mover. A first value of the position of the mover is generated with the first processing core responsive to the first position feedback signals, and a second value of the position of the mover is generated with the second processing core responsive to the second position feedback signals. The first and second values of the position of the mover are compared with either the first or second processing core to verify operation of the first and second position sensors.

Abstract: A gas turbine engine nozzle segment includes at least two circumferentially adjacent vanes joined together along an interface between the vanes. Each of the vanes includes a hollow airfoil disposed between radially inner and outer band panels and a cooling air intake duct leading to a hollow interior of the airfoil for directing cooling air into the hollow interior. The intake duct has a duct wall protruding radially outward from the outer band panel and at least one impingement cooling hole disposed through the intake duct wall and circumferentially and radially inwardly angled. A flange portion extends circumferentially along the outer band panel and an opening in the flange portion is in fluid communication with the intake duct. The hollow airfoil, radially inner and outer band panels, intake duct wall, and flange portion are integrally formed and, preferably, integrally cast such that the vane is a single piece integrally cast vane.

Abstract: A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition having a plurality of inlet holes. A plurality of film cooling gill holes extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.

Abstract: A gas turbine engine airfoil includes an axial serpentine cooling circuit therein. A plurality of the serpentine circuits are preferably stacked in a radial row along the airfoil trailing edge for cooling thereof.

Abstract: A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between the sidewalls. The second partition is common to both chambers, and both partitions include respective pluralities of first and second inlet holes sized to meter cooling air therethrough in series between the chambers.

Abstract: A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow component in the bleed flow in the flow zone facilitates discharge of the flow through apertures in a rotor into a bore portion thereof, minimizing work input and temperature rise of the coolant.

Abstract: A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.