Patent application number | Description | Published |
20100296947 | APPARATUS AND METHOD FOR PROVIDING DAMPER LIQUID IN A GAS TURBINE - A fluid distribution system for use in a gas turbine engine includes a fan shaft, a damper, a bearing, and a pump. The damper supports the bearing, and the bearing supports the fan shaft. The pump is connected to and driven by the fan shaft. The pump is also fluidically connected to the damper. | 11-25-2010 |
20110233871 | LIFTOFF CARBON SEAL - A liftoff carbon seal assembly includes a rotating seal plate adjacent to a rotating seal backer plate and a rotating seal plate retainer. The rotating seal plate defines a rotating seal plate face which extends beyond a rotating seal plate retainer face of the rotating seal plate retainer with a static carbon seal is adjacent to the rotating seal plate. | 09-29-2011 |
20110284103 | ACCESSING A VALVE ASSEMBLY OF A TURBOMACHINE - An example method of accessing a valve assembly of a turbomachine includes accessing a check valve of the valve assembly from a first position that is radially outside a flow path through the turbomachine. The method accessing a shut off valve of the valve assembly from a second position that is radially outside the flow path. The check valve and the shut off valve are configured to influence communication of lubricant along a lubricant communication path that extends between a location radially outboard the flow path and a location radially inboard the flow path. The first position is the same as the second position in some examples. | 11-24-2011 |
20110286836 | GEARED TURBOFAN ENGINE WITH INTEGRAL GEAR AND BEARING SUPPORTS - A gas turbine engine includes a bearing and a bearing support having a second wall extending between first and second ends and operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A second wall integral with and extending transversely from the first wall provides a flexible support. The second wall has a flange, and a gear train component is secured to the flange. A gas turbine engine includes a support structure which supports the main rotatable structure via bearings and gear train components. The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system. | 11-24-2011 |
20120195753 | GAS TURBINE ENGINE ARCHITECTURE WITH LOW PRESSURE COMPRESSOR HUB BETWEEN HIGH AND LOW ROTOR THRUST BEARINGS - 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. | 08-02-2012 |
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 |
20120328431 | INTEGRAL BEARING SUPPORT AND CENTERING SPRING ASSEMBLY FOR A GAS TURBINE ENGINE - A bearing support assembly for supporting a bearing assembly within a bearing compartment of a gas turbine engine includes a centering spring and a bearing support member integrally joined together to form a one piece structure. The centering spring connects to the bearing assembly and has a portion that extends conically relative to a centerline axis of the gas turbine engine. The bearing support member extends from the centering spring to connect to an engine case of the gas turbine engine. | 12-27-2012 |
20130075976 | COMPLIANT MOUNTING OF AN AXIAL FACE SEAL ASSEMBLY - A axial face seal assembly includes first and second structures rotatable relative to one another about an axis. A carrier supports a seal that engages the second structure. The carrier is configured to move along the axis. First and second springs operatively are arranged between the first structure and the carrier. The first and second springs are configured to bias the carrier relative to the second structure respectively in first and second directions along the axis for providing a desired closing force on the second structure. A method of sealing a rotating structure includes biasing a seal toward a rotating sealing surface with a first spring to provide a desired axial closing force. The axial position of the seal relative to the rotating sealing surface is changed to an undesired axial closing force. The seal is biased with a second spring to achieve the desired axial closing force. | 03-28-2013 |
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 |
20130305733 | APPARATUS AND METHOD FOR PROVIDING DAMPER LIQUID IN A GAS TURBINE ENGINE - A method for distributing liquid in a gas turbine engine is disclosed. The method includes rotating a fan shaft coupled to a spool via a fan drive gear system. The spool drives rotation of the fan shaft through the fan drive gear system during operation of the gas turbine engine. A pump is driven via the fan shaft. Liquid is supplied from a sump to the pump under a first operating condition. Liquid is supplied from an auxiliary reservoir to the pump under a second operating condition. Liquid is pumped to a damper. | 11-21-2013 |
20140030088 | FORWARD COMPARTMENT SERVICE SYSTEM FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine includes a jumper tube that extends through a first passage and a second passge. | 01-30-2014 |
20140054862 | SPRING CARRIER AND REMOVABLE SEAL CARRIER - A seal assembly includes a seal support, a spring carrier, a plurality of springs, and a seal carrier. The spring carrier is connected to the seal support by a guide assembly. The plurality of springs are disposed between the seal support and the spring carrier. The seal carrier is connected to the spring carrier and is removable therefrom. | 02-27-2014 |
20140062026 | FACE SEAL RETAINING ASSEMBLY FOR GAS TURBINE ENGINE - A face seal assembly for a gas turbine engine includes an engine static structure. A guide assembly supports a face seal for movement relative to the engine static structure in an axial direction. The guide assembly includes a guide pin having a first end that supports a washer that is retained by a circlip secured to the first end. The circlip is configured to limit movement of the face seal in the axial direction. | 03-06-2014 |
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 |
20140174252 | MOUNT WITH AN AXIAL UPSTREAM LINKAGE FOR CONNETING A GEARBOX TO A TURBINE ENGINE CASE - A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of gearbox mounts that connect the gearbox to the case. The case extends along an axis between an upstream end and a downstream end. The gearbox mounts include an axial mount that extends axially in an upstream direction from the gearbox to the case. | 06-26-2014 |
20140230403 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing. | 08-21-2014 |
20140314546 | TURBINE ENGINE GEARBOX MOUNT WITH MULTIPLE FUSE JOINTS - A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts. | 10-23-2014 |
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 |
20140356141 | GEARED TURBOFAN ENGINE WITH INTEGRAL GEAR AND BEARING SUPPORTS - A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A flexible support is provided by a second wall integral with and extending transversely from the first wall. The second wall has a first flange and a gear train component is secured to the first flange. | 12-04-2014 |