| 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 |
| 20090214331 | Curved tooth coupling for a miniature gas turbine engine - A rotor assembly for a miniature gas turbine propulsion system comprises a centrifugal compressor wheel, a turbine wheel, a shaft and a tie bolt. The centrifugal compressor wheel includes a first curved tooth coupling, and the turbine wheel includes a second curved tooth coupling interconnected with the first curved tooth coupling. The shaft extends from the centrifugal compressor wheel, and the tie bolt extends between the shaft and the turbine wheel to bring the first curved tooth coupling into compression with the second curved tooth coupling. As such, the compressor wheel and the turbine wheel are assembled and remain, over the operational envelope of the propulsion system, in a reliably robust aligned configuration. | 08-27-2009 |
| 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 |
| 20100037623 | High Efficiency Turbine Engine - A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet; an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet; a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet; a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet; a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet; a radial turbine with a radial turbine inlet coupled to the combustor inlet and a turbine outlet coupled to the recuperator warm side inlet; at least one exhaust nozzle with an exhaust nozzle inlet coupled to the recuperator warm side outlet and an exhaust nozzle outlet that discharges into the by-pass duct between the by-pass duct inlet and outlet; and a propelling nozzle coupled to the by-pass duct outlet. | 02-18-2010 |
| 20100276893 | Dynamic Sealing System - A dynamic sealing assembly for a rotating shaft to seal an forward portion of the shaft from an aft portion of the shaft, comprises: a stationary member that has an aperture with a spiral grooved aperture surface that passes through it to receive the shaft; and generally linear shaft surface undulations between the forward and aft portions of the shaft that are at least partially within the sealing member aperture; wherein rotation of the shaft causes the undulations to propagate fluid from between the rotating shaft and the aperture into the grooved aperture surface back toward the forward portion of the shaft. | 11-04-2010 |
| 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 |
| 20110280731 | Blade Retainer Clip - A blade retainer clip for retaining a foot of a turbine blade in a shoe of a turbine disc of a turbine wheel includes: a clip shank that fits into a mating slot in the blade foot; a protuberance along a central portion of the clip shank that fits into a mating recess along the mating slot in the blade foot; a clip heel on one end of the clip shank that engages a heel of the blade foot and a heel of the disc shoe that expands radially from at least opposite sides of the clip shank; and a clip toe that extends beyond a toe of the disc shoe that is deformable to contact at least the toe of the disc shoe. | 11-17-2011 |
| 20110302912 | COMPRESSOR DIFFUSER VANE DAMPER - An auxiliary power unit is disclosed that includes a compressor section having a compressor inlet and a compressor exit. A turbine section is arranged downstream from the compressor exit. A diffuser is disposed in fluid communication with and between the compressor section and the turbine section. The diffuser has multiple generally radially extending circumferentially arranged vanes. A shroud housing is secured against the vanes. A damper is arranged between at least one vane and the shroud housing and configured to damp vibration of the at least one vane relative to the shroud housing during operation of the auxiliary power unit. | 12-15-2011 |
