Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring.

Abstract: A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure.

Abstract: A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

Abstract: A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring.

Abstract: A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.

Abstract: An apparatus and method for balancing a gas turbine engine rotor includes a plurality of balancing weights adapted to be selectively attached to at least one of inlets or outlets of a cooling passage of the rotor. The weights include cooling access which permits coolant to communicate with the cooling passage.

Abstract: A turbine rotor for a gas turbine engine including a disc having a hub defining a central bore for receiving an engine shaft. A nut retains the disc on the shaft. The disc retaining nut has at least one cooling passage defined therein and disposed for directing a flow of cooling air passing through the bore of the disc.

Abstract: An apparatus and method for balancing a gas turbine engine rotor includes a plurality of balancing weights adapted to be selectively attached to at least one of inlets or outlets of a cooling passage of the rotor. The weights include cooling access which permits coolant to communicate with the cooling passage.

Abstract: A turbine rotor for a gas turbine engine comprises a disc having a hub defining a central bore for receiving an engine shaft. A nut retains the disc on the shaft. The disc retaining nut has at least one cooling passage defined therein and disposed for directing a flow of cooling air passing through the bore of the disc.

Abstract: A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

Abstract: A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.

Abstract: The surface of a gas turbine blade is machined with a material-removing tool and simultaneously, an anti-oxidation coating is deposited on the surface using eletrospark deposition.

Abstract: For the early detection of an abnormal rise in the temperature in an enclosure to be protected, a large number of micro-containers are arranged in the enclosure. These micro-containers are, for example, incorporated in the paint coating the walls of the enclosure. The micro-containers are filled with an extinguishing gas and produce when they burst a characteristic noise which is detected by microphones. The installation also comprises for the purpose of avoiding false alarms and achieving an adequate discrimination of the useful signal from that produced by the normal surrounding noise, a filtering and processing circuit which operates in an essentially digital manner.