Patent application number | Description | Published |
20090060405 | High speed bearing system with bind-free axial displacement - A rotary bearing system that supports a shaft for rotating machinery in a housing comprises: at least one stationary rotary bearing mounted in the housing for supporting a respective journal of the shaft in a desired axial and radial alignment; at least one slidable rotary bearing, with an outer surface mounted within a respective inner support surface of the housing to form a respective linear bearing such that each slidable bearing may slide axially along the inner support surface of the housing, for supporting another respective journal of the shaft with the desired radial alignment; and at least one layer of a crystalline material that exhibits a high degree of basal cleavage bonded to at least one of the linear bearing surfaces; wherein each layer of crystalline material allows each slidable rotary bearing to slide axially along each respective linear bearing to compensate for differences in the coefficient of expansion of the housing and the shaft so as to prevent the bearing system from binding due to extreme environmental conditions. | 03-05-2009 |
20090252604 | THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE - A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage. | 10-08-2009 |
20110072830 | COMBUSTOR INTERFACE SEALING ARRANGEMENT - A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage. | 03-31-2011 |
20110272553 | REMOVABLE GAS TURBINE ENGINE STAND - A removable stand assembly for a gas turbine engine includes a first stand removably mountable to a gas turbine engine on one side of a center of gravity of the gas turbine engine and a second stand removably mountable to the gas turbine engine on a second side of the center of gravity of the gas turbine engine. | 11-10-2011 |
20120242045 | COMBUSTOR INTERFACE SEALING ARRANGEMENT - An example method of sealing an interface within a gas turbine engine includes holding a sealing ring arrangement relative to a turbine nozzle using a flange extending from a combustor liner. The method further includes urging the sealing ring arrangement toward a sealed relationship with the turbine nozzle. | 09-27-2012 |
20140003911 | TURBINE WHEEL CATCHER | 01-02-2014 |
20140102112 | ONE-PIECE FUEL NOZZLE FOR A THRUST ENGINE - A nozzle formed of one piece for a jet engine includes a mixing tube, a fuel conduit integrally formed with the mixing tube, and an opening through the fuel conduit and directed radially into the mixing tube. | 04-17-2014 |
20140208714 | Thermal Management for Gas Turbine Engine - A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine. | 07-31-2014 |