Patent application number | Description | Published |
20090121441 | DUAL CONFIGURATION SEAL ASSEMBLY FOR A ROTATIONAL ASSEMBLY - A seal assembly for a rotational assembly includes a first seal, a second seal and a crossover support. The crossover support includes a first geometry that interacts with the first seal and a second, different geometry that interacts with the second seal. | 05-14-2009 |
20120011824 | INTEGRAL LUBRICATION TUBE AND NOZZLE COMBINATION - An assembly includes a tube fitting integrally joined with a nozzle and adapted with a plurality of passages to spray lubricating oil at components within a bearing compartment of a gas turbine engine. In another aspect, the tube fitting and the nozzle are attached to a lubrication tube such that the tube fitting and nozzle can be inserted or removed from the bearing compartment along with the lubrication tube without disassembling the bearing compartment. | 01-19-2012 |
20120027570 | SHAFT ASSEMBLY FOR A GAS TURBINE ENGINE - A shaft assembly for a gas turbine engine includes a shaft, an annular fluid collection cavity, and a bearing. The shaft is rotatable around an axially extending shaft centerline. The annular fluid collection cavity is formed by an axial panel extending between a forward radial panel and an aft radial panel. The aft radial panel includes a plurality of fluid apertures, each fluid aperture having a center disposed at a first radius from the shaft centerline. The bearing includes an inner race having a shaft mounting surface and a plurality of axially extending race fluid passages. The shaft mounting surface is engaged with an exterior surface of the shaft, and is disposed at a second radius from the shaft centerline, wherein the second radius is less than the first radius. At least some of the axially extending race fluid passages are fluidly connected with at least some of the fluid apertures in the aft radial panel. | 02-02-2012 |
20120260623 | COUPLING SHAFT FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A coupling shaft assembly for a gas turbine engine includes a forward coupling shaft section with a forward interface spline and a forward mid shaft interface spline and an aft coupling shaft section includes an aft mid shaft interface spline and an aft interface spline, the aft mid shaft interface spline engageable with the forward mid shaft interface spline. | 10-18-2012 |
20120260669 | FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE - A front center body support for a gas turbine engine includes a front center body section, a bearing section and a frustro-conical interface section, the frustro-conical interface section between the front center body section and the bearing section. | 10-18-2012 |
20120263578 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment. | 10-18-2012 |
20120263579 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes first splines. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes second splines that intermesh with the first splines for transferring torque there between. | 10-18-2012 |
20130170958 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support. | 07-04-2013 |
20130192242 | SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE - A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool, which is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. A second turbine is coupled through a second spool to drive the second compressor. A speed sensor probe is operable to determine a rotational speed of the first spool. The speed sensor probe is located axially aft of the first axial position and the second axial position. | 08-01-2013 |
20130199206 | SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE - A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan about an engine central axis, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool. The first spool is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. The turbine section also includes a second turbine coupled through a second spool to drive the second compressor. A sensor probe is operable to determine a rotational speed of the first spool. The sensor probe is located at a third axial position that is axially forward of the first axial position and axially aft of the second axial position. | 08-08-2013 |
20140079546 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - Disclosed is a gas turbine engine configured to include a propulsor section having a fan drive geared architecture. The gas turbine engine includes a gas generator section that includes a compressor section having a first rotor rotationally mounted to a first spool. The engine further includes a bearing package adapted for rotationally supporting the first spool. The bearing package is configured for supporting the first rotor during at least one of (1) a period prior to installation of the fan drive geared architecture into the engine and (2) a period after removal of the fan drive geared architecture from the engine. | 03-20-2014 |
20140140818 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package. | 05-22-2014 |
20140317926 | FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE - A method for maintaining a gas turbine engine includes providing access from a forward section of a front center body assembly to a flex support mounted to a front center body support. The flex support is mounted to a geared architecture. | 10-30-2014 |