Patent application number | Description | Published |
20090097967 | GAS TURBINE ENGINE WITH VARIABLE GEOMETRY FAN EXIT GUIDE VANE SYSTEM - A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions. | 04-16-2009 |
20090320285 | EDM MACHINING AND METHOD TO MANUFACTURE A CURVED ROTOR BLADE RETENTION SLOT - A method of machining a curved blade retention slot with electron discharge machining. | 12-31-2009 |
20090325468 | ABRASIVE WATERJET MACHINING AND METHOD TO MANUFACTURE A CURVED ROTOR BLADE RETENTION SLOT - A method of machining a blade retention slot with an abrasive water jet machining. A straight blade retention slot along an X-axis then a at least one side of the straight blade retention slot is abrasive water jet machined to generate a curved side of the blade retention slot defined within an X-Y plane. | 12-31-2009 |
20100266415 | HYBRID STRUCTURE FAN BLADE - A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil. | 10-21-2010 |
20120068003 | WIRELESS SENSOR FOR AN AIRCRAFT PROPULSION SYSTEM - A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters. | 03-22-2012 |
20120124964 | GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY - A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions. | 05-24-2012 |
20120222397 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120222398 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120233981 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-20-2012 |
20130014512 | Ceramic Matrix Composite Combustor Vane Ring AssemblyAANM Jarmon; David C.AACI KensingtonAAST CTAACO USAAGP Jarmon; David C. Kensington CT USAANM Smith; Peter G.AACI WallingfordAAST CTAACO USAAGP Smith; Peter G. Wallingford CT US - A vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane. | 01-17-2013 |
20130039774 | HYBRID STRUCTURE AIRFOIL - A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body. | 02-14-2013 |
20140050589 | HYBRID STRUCTURE AIRFOIL - A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body. | 02-20-2014 |