Patent application number | Description | Published |
20100236256 | FLOW DISCHARGE DEVICE - A flow discharge device, such as a compressor bleed outlet discharging into a bypass duct of a gas turbine engine, comprises an outlet panel | 09-23-2010 |
20100293917 | GAS TURBINE ENGINE HAVING A NACELLE AND A BREATHER DUCT - Breather air, containing oil mist, is discharged from a nacelle | 11-25-2010 |
20100293964 | BREATHER DUCT SHIELDING - A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port. | 11-25-2010 |
20110011477 | FLOW DISCHARGE DEVICE - A flow discharge device, such as a bleed assembly in a gas turbine engine, comprises a discharge outlet member | 01-20-2011 |
20110044796 | FLUIDFOIL TIP VORTEX DISRUPTION - A fluidfoil tip vortex disruption arrangement. There is a fluid inlet on a pressure side of the fluidfoil; and a fluid outlet in a low pressure region at or near the tip of the fluidfoil. Fluid exiting the fluid outlet inserts instability into a tip vortex to disrupt or destroy the vortex. | 02-24-2011 |
20110100475 | BOUNDARY LAYER ENERGISER - A boundary layer energiser ( | 05-05-2011 |
20110103941 | BREATHER DUCT SHIELDING - A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is at least one clean air outlet bounding the exhaust port and arranged to expel, in use, a vortical flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port. | 05-05-2011 |
20110103969 | BOUNDARY LAYER ENERGISER - A boundary layer energiser ( | 05-05-2011 |
20110309587 | SEAL - A seal having an integral attachment arrangement. The attachment arrangement comprises at least one attachment feature and at least one locking feature. The at least one attachment feature is configured and arranged to interdigitate with features of another component in a first orientation and to lock to the other component in a second orientation. The second orientation is rotationally displaced from the first orientation. | 12-22-2011 |
20120034068 | VENTILATION INLET - A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone. | 02-09-2012 |
20120137650 | FLUID IMPINGEMENT ARRANGEMENT - A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit. | 06-07-2012 |