Patent application number | Description | Published |
20090301095 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle. | 12-10-2009 |
20090320488 | GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE - A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance. | 12-31-2009 |
20100074739 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle. | 03-25-2010 |
20110120078 | VARIABLE AREA FAN NOZZLE TRACK - A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that is more closely controlled than the first interface. A VAFN cowl is mounted to the second track slider. | 05-26-2011 |
20110120079 | VARIABLE AREA FAN NOZZLE STIFFENERS AND PLACEMENT - A nacelle assembly for a high-bypass gas turbine engine is disclosed and includes a variable area fan nozzle (VAFN) including at least one second fan nacelle section movable relative to the first fan nacelle section to modify an area of the bypass flow path. At least one stiffener is mounted between the first fan nacelle section and the second fan nacelle section. The stiffeners modify mode shapes and natural frequencies to substantially reduce or eliminate flutter within operating ranges that are produced by unsteady aerodynamic loads. | 05-26-2011 |
20110120080 | VARIABLE AREA FAN NOZZLE COWL AIRFOIL - A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin. | 05-26-2011 |
20110120081 | VARIABLE AREA FAN NOZZLE BEARING TRACK - A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider. | 05-26-2011 |
20120011825 | GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE - A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius. | 01-19-2012 |
20120076635 | NACELLE WITH POROUS SURFACES - A fan nacelle for a gas turbine engine includes a leading edge region with a flow path between an intake region in a nacelle outer surface and an exhaust region in a nacelle inner surface to locally modify a flow around the leading edge region during a predefined off-design condition. | 03-29-2012 |
20140237990 | VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION - A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN. | 08-28-2014 |
20140259661 | VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION - A method of controlling flutter of a fan nozzle includes, for a given design of a fan nozzle, determining a vibration mode that causes a flutter characteristic of the fan nozzle and, in response to the determined vibration mode, establishing a wall thickness distribution of at least one wall of the fan nozzle to include local thick portions and local thin portions that alter the flutter characteristic. | 09-18-2014 |
20140321970 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section. | 10-30-2014 |
20140348630 | NOISE REDUCING VANE - A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure. | 11-27-2014 |
20140366554 | CROSS REFERENCE TO RELATED APPLICATIONS - A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section. The first acoustic system is defined at least in part within a trailing edge region of the first fan nacelle section. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle is also disclosed. | 12-18-2014 |