| Patent application number | Description | Published |
|---|
| 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 |
| 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 |
| 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 |
