Patent application number | Description | Published |
20120134777 | ENGINE CASE WITH WASH SYSTEM - A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct. | 05-31-2012 |
20120251313 | APPARATUS AND METHOD FOR GAS TURBINE ENGINE VANE RETENTION - A vane assembly of a gas turbine engine has a plurality of vanes extending radially and inwardly from an annular casing. An outer end of each vane radially and outwardly projects from the casing and is received in one of apertures defined in an elastomeric ring which is placed around the casing. A strap of a non-metallic material is placed in a pre-tensioned condition around the elastomeric ring to compress the elastomeric ring and to radially retain the outer end of each vane. | 10-04-2012 |
20130202440 | SEGMENTED RINGS WITH CAPTIVE NUTS FOR FAN BOLTS - An apparatus and method for connecting a fan rotor to a shaft of a gas turbine engine includes a segmented clinch nut plate having a plurality of clinch nuts installed in pre-drilled holes in each segment. A plurality of mounting bolts extending through the holes in the rotor shaft and holes in a mounting device of the shaft threadedly engage the clinch nuts of the clinch nut plate. The segments of the clinch nut plate are disposed separately one from another. | 08-08-2013 |
20130202442 | FAN AND BOOST JOINT - A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft, the second link being less rigid then the first link. | 08-08-2013 |
20130202450 | FASTENING SYSTEM FOR FAN AND SHAFT INTERCONNECTION - A fan and shaft assembly for a turbofan gas turbine engine comprises a shaft and a fan. Sets of aligned throughbores are respectively of the shaft and the fan, at a junction between the shaft and the fan. Fastening systems are provided for the sets of aligned throughbores. Each fastening system comprises a sleeve received in one of the sets of aligned throughbores and sized to fit without play in the set of aligned throughbores. A head of the sleeve abuts a surface at the junction between the shaft and the fan. A fastener is inserted in the sleeve and extends beyond both ends of the sleeve to clamp the fan to the shaft, the fastener being loosely received in the sleeve. A method for replacing a component of a fastening system retaining a fan to a shaft is provided as well. | 08-08-2013 |
20130249172 | SEAL ARRANGEMENT FOR GAS TURBINE ENGINES - A seal arrangement for a gas turbine engine comprises a seal support having a hub portion and a peripheral rim portion. A seal member is mounted to a radially inner surface of the hub portion. A first set of circumferentially spaced-apart channel segments project from the peripheral rim portion of the seal support. A second set of circumferentially spaced-apart channel segments projects from a mating stationary structure of the gas turbine engine. The first and second sets of circumferentially spaced-apart channel segments circumferentially may be aligned to complementary form a circumferentially extending channel. A retaining ring may be mounted in the circumferentially extending channel for retaining the seal support on the mating stationary structure of the engine. The seal support may be provided with a diaphragm to provide flexibly between the seal member and the point of attachment of the seal support to the mating structure of the engine. | 09-26-2013 |
20130251517 | GROMMET FOR GAS TURBINE VANE - A vane assembly for a gas turbine engine includes an annular shroud having openings therein and a plurality of vanes extending radially from the shroud and each having an extremity received within one of the openings. A grommet is positioned within each opening for shielding the vane extremity from the annular shroud. The grommet includes an annular protrusion for providing sealing between the opening and the vane extremity, and an annular restraint element adjacent the protrusion for retaining the vane in place relative to the shroud. | 09-26-2013 |
20140026591 | AXIAL RETENTION FOR FASTENERS IN FAN JOINT - In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor. | 01-30-2014 |