Patent application number | Description | Published |
20090050714 | FUEL NOZZLE FOR A GAS TURBINE ENGINE - In the fuel nozzle, the fuel is circulated in a helical path around the interface of a stem of the fuel nozzle and a flange for increase the cooling. | 02-26-2009 |
20090060636 | POSITIONING ARRANGEMENT FOR COMPONENTS OF A PRESSURE VESSEL AND METHOD - The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses. | 03-05-2009 |
20090159725 | MODULAR FUEL NOZZLE AIR SWIRLER - A modular fuel nozzle air swirler for a gas turbine engine has a body defining a fuel passage extending between an inlet end and a discharge end of the body. An annular cap is removably secured to the discharge end of the body via cooperating interlocking members. | 06-25-2009 |
20090320479 | NESTED CHANNEL DUCTS FOR NOZZLE CONSTRUCTION AND THE LIKE - A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets. | 12-31-2009 |
20100257864 | REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR - A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite. | 10-14-2010 |
20110120142 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 05-26-2011 |
20110173982 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fuel manifold for mounting the fuel manifold within the gas turbine engine. The attachment lugs re adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 07-21-2011 |
20120227415 | POSITIONING ARRANGEMENT FOR COMPONENTS OF A PRESSURE VESSEL AND METHOD - The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses. | 09-13-2012 |