Patent application number | Description | Published |
20090116951 | METHOD AND APPARATUS FOR FAN SHAFT BEARING LUBRICATION - A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits. | 05-07-2009 |
20090123271 | FAN SHAFT RETENTION - A retention system for a fan in a gas turbine engine includes a shaft that is rotatable relative to a bearing support structure about an axis. The retention system includes fore and aft bearings that rotatably support the shaft, with the fore and aft bearings being spaced apart from each other in a direction along the axis. A machined spring reacts between the bearing support structure and the fore bearing to provide a desired axial preload. | 05-14-2009 |
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 |
20130111735 | TIE BOLT EMPLOYING DIFFERENTIAL THREAD - A tie bolt for joining two parts together has a shaft. The shaft in turn has a primary thread for engaging a first part and a secondary thread for engaging a second part, wherein the primary thread and the secondary thread have different pitches. The tie bolt may be used to join together any two parts which are to be locked together to transmit torque. | 05-09-2013 |
20130202349 | TURBINE ENGINE SHAFT COUPLING - A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediate tie shaft segment connected axially between a first tie shaft segment and a second tie shaft segment. The first tie shaft segment includes a first threaded tie shaft surface that is mated with a first threaded shaft surface of the first sub-shaft. The second tie shaft segment includes a second threaded tie shaft surface that is mated with a second threaded shaft surface of the second sub-shaft. The tie shaft also includes a sub-shaft bumper stop extending radially from the intermediate tie shaft segment to a bumper stop distal end, which has a radius that is greater than a radius the first and/or second threaded shaft surfaces. | 08-08-2013 |
20130251511 | TORQUE FRAME BUSHING ARRANGEMENT FOR GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM - A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is arranged in each bore and provides an aperture. At least one bushing has a bushing axis offset from the bore axis. A pin is disposed in the aperture and secures the carrier to the torque frame. | 09-26-2013 |
20130259649 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location. | 10-03-2013 |
20130259655 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location. | 10-03-2013 |
20130259657 | GAS TURBINE ENGINE GEARED ARCHITECTURE AXIAL RETENTION ARRANGEMENT - A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure. | 10-03-2013 |
20130287553 | MANIFOLD FOR GEARED TURBOFAN ENGINE - A geared architecture for a gas turbine engine includes a lubricant manifold for directing lubricant flow to the geared architecture. The manifold including annular channel and a bowl member received within the annular channel for defining a passage for directing lubricant. | 10-31-2013 |
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 |
20130319011 | GEARED ARCHITECTURE CARRIER TORQUE FRAME ASSEMBLY - A fan drive gear system for a gas turbine engine includes a carrier supporting circumferentially arranged gears within gear mount sections spaced circumferentially about a periphery. A shelf is disposed between each of the gear mounting sections. A torque frame is attached to the carrier and includes circumferentially arranged finger sections. Each of the finger sections includes first and second ends that are spaced apart to receive the shelf. A pin extends through openings in the shelf and first and second ends to secure the torque frame to the carrier. | 12-05-2013 |
20130320185 | TURBOMACHINE GEARED ARCHITECTURE SUPPORT ASSEMBLY - An example turbomachine geared architecture support assembly includes a compliant member configured to hold a geared architecture within a turbomachine. The compliant member has a compliant section that permits rotation of the geared architecture relative to a fixed portion of the turbomachine. A stop limits rotation of the geared architecture relative to the fixed portion of the turbomachine. | 12-05-2013 |
20130323047 | FRONT BEARING SUPPORT FOR A FAN DRIVE GEAR SYSTEM - A fan shaft support assembly for a gas turbine engine includes first and second bearing assembles supported by a bearing support structure. The bearing support structure includes a first support including a first support end supporting the first bearing assembly and a second support including a second support end supporting the second bearing assembly. The first support end and the second support end are spaced apart to provide a preload on the first and second bearing assemblies. | 12-05-2013 |
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 |
20140031163 | FAN DRIVE GEAR SYSTEM TORQUE FRAME PIN RETAINER - A system and method for fixing a fan drive gear system carrier to a torque frame are disclosed. The carrier and torque frame respectively have a hole and an aperture which are aligned with one another. A retainer pin is inserted in to the aligned hole and aperture in an interference fit relationship with at least one of the hole and aperture. | 01-30-2014 |
20140064932 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location. | 03-06-2014 |
20140087907 | GEAR CARRIER FLEX MOUNT LUBRICATION - An example epicyclic gear train assembly includes a flexure pin received by a carrier. The flexure pin and the carrier respectively include first and second pin apertures configured to receive a retainer pin. The flexure pin further includes a lubricant conduit separate from the first pin aperture. | 03-27-2014 |
20140165762 | Fan Drive Gear System Assembly Guide - A gas turbine engine has a fan and a turbine section including a turbine rotor to drive the fan through a gear reduction module. An input shaft downstream of the turbine rotor includes a flexible mount driving the gear reduction. The input shaft is mounted within a bearing module. The gear reduction module has static structure mounted to an engine housing through a flexible mount. Oil is supplied into the gear reduction. An oil tube supplies oil from the gear reduction to the bearing module, and is received within openings in the static structure, and a housing for the bearing module. The oil tube extends through an assembly guide having a guide opening spaced away from an outer periphery of the oil tube. The guide opening is intermediate the openings. A method is also disclosed. | 06-19-2014 |
20140219783 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section, a turbine section coupled to the fan section through a geared architecture, a first member supporting the geared architecture, and a second member supporting the first member relative to an engine static structure. The first member and the second members are spaced apart from one another at a location. A damper includes opposing ends and extending between the first member and the second member at the location for limiting relative movement between the first member and the second member. A fan drive gear system and a method are also disclosed. | 08-07-2014 |
20140290268 | GAS TURBINE ENGINE GEARED ARCHITECTURE AXIAL RETENTION ARRANGEMENT - A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed. | 10-02-2014 |
20140294558 | TURBOMACHINE FLUID DELIVERY MANIFOLD AND SYSTEM - An example turbomachine fluid delivery manifold provides a journal fluid path and a gear mesh fluid path that is separate from the journal fluid path. An example turbomachine lubrication system includes a geared architecture having a journal bearing and a gear. In this example, a manifold provides a portion of a first fluid path and a portion of a second fluid path separate from the first fluid path. The first fluid path is operative to communicate a first fluid from a fluid supply to the journal bearing. The second fluid path is operative to communicate a second fluid from the fluid supply to a gear mesh. | 10-02-2014 |
20140348577 | TIE BOLT EMPLOYING DIFFERENTIAL THREAD - A tie bolt for joining two parts together has a shaft. The shaft in turn has a primary thread for engaging a first part and a secondary thread for engaging a second part, wherein the primary thread and the secondary thread have different pitches. The tie bolt may be used to join together any two parts which are to be locked together to transmit torque. | 11-27-2014 |