| Patent application number | Description | Published |
|---|
| 20090056309 | Gas Turbine Engine Systems and Related Methods Involving Multiple Gas Turbine Cores - Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly. | 03-05-2009 |
| 20090067993 | COATED VARIABLE AREA FAN NOZZLE - A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions. | 03-12-2009 |
| 20090142184 | VECTORING TRANSITION DUCT FOR TURBINE ENGINE - A transition duct ( | 06-04-2009 |
| 20090145101 | PARTICLE SEPARATOR FOR TIP TURBINE ENGINE - A particle separator ( | 06-11-2009 |
| 20090145102 | Gas Turbine Engine Systems Involving Tip Fans - Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the first rotatable set of blades defining an inner fan and a tip fan; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades. | 06-11-2009 |
| 20090145105 | REMOTE ENGINE FUEL CONTROL AND ELECTRONIC ENGINE CONTROL FOR TURBINE ENGINE - A controller is mounted remotely from a turbine engine and provided with an independent power source ( | 06-11-2009 |
| 20090145135 | TURBINE BLOW DOWN STARTER FOR TURBINE ENGINE - In order to start a turbine engine ( | 06-11-2009 |
| 20090148292 | AXIAL COMPRESSOR FOR TIP TURBINE ENGINE - A tip turbine engine ( | 06-11-2009 |
| 20090155079 | STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES - Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies ( | 06-18-2009 |
| 20090185911 | Systems and Methods Involving Localized Stiffening of Blades - Systems and methods involving localized stiffening of blades are provided. In this regard, a representative a gas turbine engine blade includes: a recess located in a surface of the blade; and material positioned at least partially within the recess such that the material provides a localized increase in stiffness of the blade. | 07-23-2009 |
| 20090211221 | Auxiliary propulsor for a variable cycle gas turbine engine - A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the stream of pressurized air to generate streams of combustion air and supercharged auxiliary air. A peripheral case surrounds the engine case to form a peripheral duct. An auxiliary combustor and propulsor are positioned within the peripheral duct. A bleed duct extends from the high pressure spool to the auxiliary combustor. Variable ductwork directs airflow through the bleed duct and peripheral duct in two modes. A first mode comprises directing the stream of auxiliary air to the auxiliary combustor, and directing stream of inlet air through the peripheral duct. A second mode comprises directing the stream of auxiliary air into the stream of bypass air, and preventing inlet air from entering the peripheral duct. | 08-27-2009 |
| 20090211222 | Rear propulsor for a variable cycle gas turbine engine - A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air and combustion air. The bypass air flows through a bypass duct and the combustion air flows through a core engine. The peripheral duct surrounds the turbofan engine and is configured to selectively receive peripheral inlet air. The annular frame is disposed aft of the bypass duct and the peripheral duct, and is rotatable to alternately guide the bypass air out the bypass duct or the peripheral duct. The auxiliary turbine is connected to an aft end of the core engine and is configured to receive the combustion air. The auxiliary fan is connected to the auxiliary turbine and is configured to receive airflow from the peripheral duct. | 08-27-2009 |
| 20110056208 | REVERSED-FLOW CORE FOR A TURBOFAN WITH A FAN DRIVE GEAR SYSTEM - A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor. | 03-10-2011 |
