Patent application number | Description | Published |
20110243719 | NON-CIRCULAR AFT NACELLE COWLING GEOMETRY - A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section. | 10-06-2011 |
20130221124 | GAS TURBINE ENGINE THRUST REVERSER SYSTEM - An example thrust reverser blocker door includes a blocker door that is movable from a stowed position to a deployed position. Flow moves through an area of a bypass flowpath when the blocker door is in the stowed position. The blocker door blocks no less than about 70% and no more than about 85% of flow through this area when the blocker door is in the deployed position, wherein the area does not extend circumferentially past the blocker door. | 08-29-2013 |
20130319002 | NACELLE BIFURCATION FOR GAS TURBINE ENGINE - A nacelle structure for a gas turbine engine includes a core engine nacelle disposed about an engine axis and an outer nacelle disposed about the core engine nacelle. A bifurcation extends between the outer nacelle and the core engine nacelle along a bifurcation axis extending between the outer nacelle and the core engine nacelle. The bifurcation includes at least one mounting surface that is disposed at a non-normal angle relative to the bifurcation axis. | 12-05-2013 |
20140216005 | Gas Turbine Engine Assembly Including A Thrust Reverser - An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position. | 08-07-2014 |
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 |
20140283501 | ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO - A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (D | 09-25-2014 |
20140286754 | Elongated Geared Turbofan With High Bypass Ratio - A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (D | 09-25-2014 |
20150044028 | LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE - According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45. | 02-12-2015 |