Patent application number | Description | Published |
20110005231 | FUEL NOZZLE GUIDE PLATE MISTAKE PROOFING - A fuel nozzle guide plate has mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. The fuel nozzle guide plate is attached to an air swirler, which is mounted in an opening of a bulkhead for mixing air and fuel at an upstream side of a combustor. | 01-13-2011 |
20110011095 | WASHER WITH COOLING PASSAGE FOR A TURBINE ENGINE COMBUSTOR - A washer for a turbine engine combustor comprises a first surface, a second surface facing generally opposite from the first surface, a bore communicating through the first and second surfaces, and a cooling passage separate from the bore and communicating through the first and second surfaces. | 01-20-2011 |
20130291544 | GAS TURBINE ENGINE COMBUSTOR SURGE RETENTION - A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited. | 11-07-2013 |
20140090394 | FLOW MODIFIER FOR COMBUSTOR FUEL NOZZLE TIP - A fuel injector nozzle assembly includes a body extending along an axis and a core swirl plug positioned at least partially within the body. The core swirl plug has a flow modifying structure configured to swirl fuel at a location upstream from a distal end of the nozzle assembly. | 04-03-2014 |
20140144148 | Cooled Combustor Seal - A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter. | 05-29-2014 |
20140173896 | METHOD AND SYSTEM FOR HOLDING A COMBUSTOR PANEL DURING COATING PROCESS - A method for coating a turbine engine component comprises the steps of: providing a turbine engine component having at least one sacrificial attachment on a first side; grasping the turbine engine component via the at least one sacrificial attachment to position a first surface of the turbine engine component relative to a source of coating material; and applying a coating to said first side. | 06-26-2014 |
20150226131 | COMBUSTOR SEAL SYSTEM FOR A GAS TURBINE ENGINE - A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane. | 08-13-2015 |
20150240724 | COMBUSTOR SEAL MISTAKE-PROOFING FOR A GAS TURBINE ENGINE - A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane. | 08-27-2015 |
20150241063 | COMBUSTOR WITH GROMMET HAVING PROJECTING LIP - A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell. | 08-27-2015 |
20150241067 | FASTENED JOINT FOR A TANGENTIAL ON BOARD INJECTOR - A combustor assembly for a gas turbine engine includes a combustor shell, a TOBI, a case, and a joint for securing the combustor shell, TOBI and case together. The joint has a combustor flange integral to the combustor shell. A TOBI flange is integral to the TOBI and a case flange is integral to the case. The combustor flange, the TOBI flange and the case flange are secured together. | 08-27-2015 |