Patent application number | Description | Published |
20110044802 | BLADE OUTER AIR SEAL SUPPORT COOLING AIR DISTRIBUTION SYSTEM - A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments. | 02-24-2011 |
20110044803 | BLADE OUTER AIR SEAL ANTI-ROTATION - A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other. | 02-24-2011 |
20110044816 | BALANCING APPARATUS FOR ROTOR ASSEMBLY - 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. | 02-24-2011 |
20110081253 | GAS TURBINE ENGINE BALANCING - 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. | 04-07-2011 |
20110179805 | ROTOR CONTAINMENT STRUCTURE FOR GAS TURBINE ENGINE - A rotor containment structure for gas turbine engine comprises an inner containment layer having a single integral body defining an annular structure about the rotor, and having a support on the inner surface of the inner containment layer for at least one shroud segment. An outer containment layer provides containment strength to contain blade fragments and defining an annular structure about the inner containment layer. Air passage through the outer containment layer for air to pass from an exterior of the outer containment layer to an interior of the outer containment layer; and the inner containment layer being connected at a first end to the outer containment layer with a gap defined between the inner surface of the outer containment layer and the outer surface of the inner containment layer, the gap being in fluid communication with the air passage such that air flows through the gap, beyond a free second end of the inner containment layer. | 07-28-2011 |
20130104398 | ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE | 05-02-2013 |
20140304989 | ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE - 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 | 10-16-2014 |