| Patent application number | Description | Published |
|---|
| 20080206056 | Modular Tip Turbine Engine - A tip turbine engine assembly includes a compressor module ( | 08-28-2008 |
| 20080219833 | Inducer for a Fan Blade of a Tip Turbine Engine - A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted toward a rotational direction of the fan-turbine rotor assembly such that the inducer inlet section operates as an air scoop during rotation of the fan-turbine rotor assembly. Both axial and centrifugal compression of the airflow occurs within the inducer passage section to effectively pump the airflow through the inducer section and into the core airflow passage. | 09-11-2008 |
| 20080226453 | Balanced Turbine Rotor Fan Blade for a Tip Turbine Engine - A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section ( | 09-18-2008 |
| 20080273976 | Variable rotor blade for gas turbine engine - A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated. | 11-06-2008 |
| 20080317587 | VARIABLE-SHAPE VARIABLE-STAGGER INLET GUIDE VANE FLAP - A variable shape inlet guide vane (IGV) system includes a variable-shape IGV flap with a flexible portion that enables the desired spanwise distribution of Cx, alpha, and beta at a fan rotor inlet. An actuation system that rotates a root section of the variable-shape IGV flap to flex the flexible portion such that the twisted shape of the flap can reverse rather symmetrically during actuation from max open to max closed. | 12-25-2008 |
| 20090056306 | GAS TURBINE ENGINE FRONT ARCHITECTURE - A turbine engine is disclosed that includes a fan case surrounding a fan. A core is supported relative to the fan case by support structure, such as flow exit guide vanes, which are arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage. In one example, the example turbine engine includes a gear train arranged between the fan and a spool. The gear train is axially aligned and supported by the inlet case. An intermediate case is arranged axially adjacent to the compressor case. The support structure is arranged axially forward of the intermediate case. In one example, the support structure is axially aligned with the compressor case. | 03-05-2009 |
| 20090056343 | ENGINE MOUNTING CONFIGURATION FOR A TURBOFAN GAS TURBINE ENGINE - An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle. | 03-05-2009 |
| 20090071162 | PERIPHERAL COMBUSTOR FOR TIP TURBINE ENGINE - A tip turbine engine ( | 03-19-2009 |
| 20090074565 | TURBINE ENGINE WITH DIFFERENTIAL GEAR DRIVEN FAN AND COMPRESSOR - A gas turbine engine ( | 03-19-2009 |
| 20090074568 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes. | 03-19-2009 |
| 20090081035 | GAS TURBINE ENGINE COMPRESSOR CASE MOUNTING ARRANGEMENT - A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area. | 03-26-2009 |
| 20090081039 | GAS TURBINE ENGINE FRONT ARCHITECTURE MODULARITY - A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox. | 03-26-2009 |
| 20090092487 | Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other. | 04-09-2009 |
| 20090110544 | INFLATABLE BLEED VALVE FOR A TURBINE ENGINE - A compressor for a turbine engine includes an inflatable bleed valve that selectively bleeds core airflow from the compressor. The bleed valve has an inlet leading from the compressor and a passageway leading from the inlet. An inflatable valve selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve. | 04-30-2009 |
| 20090120058 | Tip Turbine Engine Integral Fan, Combustor, and Turbine Case - A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally | 05-14-2009 |
| 20090133401 | COMBUSTOR FOR TURBINE ENGINE - A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to an outlet that provides fuel to an interior chamber of the combustor. In one embodiment, front portions of the inner and outer walls curve toward one another and overlap to form an annular gap or manifold through which fuel is distributed to the combustion chamber. | 05-28-2009 |
| 20090142188 | SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-04-2009 |
| 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 |
| 20090148271 | Bearing mounting system in a low pressure turbine - A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft. | 06-11-2009 |
| 20090148273 | COMPRESSOR INLET GUIDE VANE FOR TIP TURBINE ENGINE AND CORRESPONDING CONTROL METHOD - A tip turbine engine ( | 06-11-2009 |
| 20090148276 | SEAL ASSEMBLY FOR A FAN ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-11-2009 |
| 20090148287 | FAN BLADE WITH INTEGRAL DIFFUSER SECTION AND TIP TURBINE BLADE SECTION FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section. | 06-11-2009 |
| 20090148297 | FAN-TURBINE ROTOR ASSEMBLY FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly ( | 06-11-2009 |
| 20090155057 | COMPRESSOR VARIABLE STAGE REMOTE ACTUATION FOR TURBINE ENGINE - A turbine engine locates an actuator ( | 06-18-2009 |
| 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 |
| 20090162187 | COUNTER-ROTATING COMPRESSOR CASE AND ASSEMBLY METHOD FOR TIP TURBINE ENGINE - A tip turbine engine ( | 06-25-2009 |
| 20090169385 | FAN-TURBINE ROTOR ASSEMBLY WITH INTEGRAL INDUCER SECTION FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly for a tip turbine engine includes a fan hub with an outer periphery scalloped by a multitude of elongated openings which extend into a fan hub web. Each elongated opening defines an inducer section and a blade receipt section to retain a hollow fan blade section. The blade receipt section retains each of the hollow fan blade sections adjacent each inducer section. The inducer sections are cast directly into the fan hub which minimizes leakage between each fan blade section and each of the respective inducer sections to minimize airflow leakage and increase engine efficiency. | 07-02-2009 |
| 20090169386 | ANNULAR TURBINE RING ROTOR - A fan-turbine rotor assembly ( | 07-02-2009 |
| 20090183512 | MOUNTING SYSTEM FOR A GAS TURBINE ENGINE - A mounting system for a gas turbine engine includes a thrust ring and a linkage assembly. The linkage assembly is at least partially received by the thrust ring. The linkage assembly reacts at least a side load and a thrust load communicated from the thrust ring. | 07-23-2009 |
| 20090188232 | THERMAL MANAGEMENT SYSTEM INTEGRATED PYLON - A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes. | 07-30-2009 |
| 20090188234 | SHARED FLOW THERMAL MANAGEMENT SYSTEM - A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship. | 07-30-2009 |
| 20090188334 | Accessory Gearboxes and Related Gas Turbine Engine Systems - Accessory gearboxes and related gas turbine engine systems are provided. In this regard, a representative accessory gearbox for a gas turbine engine is operative to be driven by rotational energy extracted from the gas turbine engine and imparted to the gearbox by multiple tower shafts. | 07-30-2009 |
| 20090191045 | LOW PRESSURE TURBINE WITH COUNTER-ROTATING DRIVES FOR SINGLE SPOOL - A low pressure turbine for a gas turbine engine includes inner and outer counter-rotating rotor sets, with both said rotor sets driving a common shaft. | 07-30-2009 |
| 20090236469 | MOUNTING SYSTEM FOR A GAS TURBINE ENGINE - A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine. | 09-24-2009 |
| 20090290976 | Gearbox assembly - An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct. | 11-26-2009 |
| 20090314881 | ENGINE MOUNT SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE - A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis. | 12-24-2009 |
| 20090317229 | INTEGRATED ACTUATOR MODULE FOR GAS TURBINE ENGINE - An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing. | 12-24-2009 |
| 20100218478 | Turbine engine compressor - A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least one compressor blade stage and at least one turbine blade stage. A combustor is located between the at least one compressor blade stage and the at least one turbine blade stage along a core flowpath. The at least one counter-rotating compressor blade stage is interspersed with the first spool at least one compressor blade stage. A transmission couples the at least one additional compressor blade stage to the first spool for counter-rotation about the engine axis. | 09-02-2010 |
| 20100242496 | GAS TURBINE ENGINE WITH STACKED ACCESSORY COMPONENTS - An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis. | 09-30-2010 |
| 20100247306 | GAS TURBINE ENGINE WITH 2.5 BLEED DUCT CORE CASE SECTION - A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a structural wall. | 09-30-2010 |
| 20110127368 | SINGLE PLANE MOUNT SYSTEM FOR GAS TURBINE ENGINE - A mounting system for a gas turbine engine assembly includes a plurality of mounting links attached the gas turbine engine along a single plane transverse to the engine centerline for separating the loads from the core engine. | 06-02-2011 |
| 20110142601 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes. | 06-16-2011 |
