Patent application number | Description | Published |
20080258016 | NACELLE ASSEMBLY WITHOUT LOWER BI-FI SPLITTER - A nacelle assembly provides thrust reverser doors and core cowl doors with separate thrust reverser door hinge lines and core cowl doors hinge lines for independent operation to eliminate the requirement of a lower bi-fi splitter. The removal of the lower Bi-Fi splitter provides improved aerodynamic packaging with improved performance by reducing drag in the bypass fan stream. | 10-23-2008 |
20090000308 | Generator with separate oil system for improved nacelle performance - An electrical generator assembly for use in a gas turbine engine, which assembly includes an electrical motor configured to connect to an accessory gearbox arranged radially outward of a main axis of the gas turbine engine and inside a nacelle, and fluid connections between the electrical motor and a generator oil system. The generator oil system is offset from the electrical motor such that the generator oil system is not located radially outward of the electrical motor and inside the nacelle. | 01-01-2009 |
20090129922 | ACCESS DOOR FOR GAS TURBINE ENGINE COMPONENTS - An access door is provided in a housing for a gas turbine engine, with the access door being movable to an access position independent of any required movement of any cowl door or a fan duct door. | 05-21-2009 |
20090266912 | FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH SLIDING ACTUATION SYSTEM - A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area. | 10-29-2009 |
20090271086 | Hybrid Engine Accessory Power System - A system for generating accessory power from a gas turbine engine is provided by the present invention. The system includes an electronic control device for monitoring at least one parameter which provides information about an incipient change in power demand, a control valve operated by the control device for supplying bleed air from the engine during a transient state in response to the at least one monitored parameter, and a pneumatically operated device for receiving the bleed air and for generating power to operate equipment onboard an aircraft. The pneumatically operated device may be an air turbine or a pneumatically integrated generator. | 10-29-2009 |
20090288386 | TRI-BODY VARIABLE AREA FAN NOZZLE AND THRUST REVERSER - A gas turbine engine system includes a fan ( | 11-26-2009 |
20110167790 | TRANSLATABLE CASCADE THRUST REVERSER - A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section. | 07-14-2011 |
20140090386 | GEARED TURBOFAN WITH FAN AND CORE MOUNTED ACCESSORY GEARBOXES - A disclosed accessory drive system provides for the reduction in the overall diameter of the outer nacelle by splitting the number of accessory components between a first gear box mounted within the outer nacelle and a second gearbox mounted to the core engine. The first gear box mounted to the fan case of the gas turbine engine drives a first plurality of accessory components. The second gear box mounted to a core engine case of the gas turbine engine drives a second plurality of accessory components. | 04-03-2014 |
20140165589 | Gas Turbine Engine With Accessory Gear Box - A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall. At least one drive shaft extends through the inner wall. The at least one drive shaft is connected to a gas turbine engine receiving the nacelle. The at least one drive shaft is connected to drive at least two accessory gear boxes, with the at least two accessory gear boxes being received between the inner and outer walls of the nacelle. A gas turbine engine is also disclosed. | 06-19-2014 |
20140246514 | TURBOMACHINE THRUST REVERSER - An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position. | 09-04-2014 |
20140252161 | DE-COUPLE GEARED TURBO-FAN ENGINE AND AIRCRAFT - A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section. | 09-11-2014 |