Class / Patent application number | Description | Number of patent applications / Date published |
415142000 | SHAFT BEARING COMBINED WITH OR RETAINED BY ARM OR VANE IN SURROUNDING WORKING FLUID SPACE | 13 |
20090110543 | SEQUENTIAL STIFFNESS SUPPORT FOR BEARING ASSEMBLIES AND METHOD OF FABRICATION - A sequential stiffness support is provided for a bearing assembly to improve vibration characteristics of a gas turbine engine and to provide a variable structural stiffness to the support to minimize unbalance load transmissibility. In one embodiment, and by way of example only, the sequential stiffness support includes an inner ring, an outer ring, and means for coupling the inner ring and the outer ring. The sequential stiffness support is configured to provide a first stiffness support at a first engine speed and a second stiffness support at speeds greater than the first engine speed. Methods of manufacturing the sequential stiffness support are also provided. | 04-30-2009 |
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 |
20090142182 | Gas Turbine Engines and Related Systems Involving Offset Turbine Frame Struts - Gas turbine engines and related systems involving offset hub struts are provided. In this regard, a representative bearing assembly for a gas turbine engine includes: a bearing operative to support a rotatable shaft; an annular hub positioned about the bearing; and an annular array of struts extending radially outwardly from the hub, at least two of the struts being positioned in different planes, the planes being oriented transversely with respect to the rotatable shaft. The method of assembling the struts by mounting first and second pluralities of struts, each plurality in a common plane, between the hub and the turbine exhaust case, with the second plurality of struts longitudinally offset from the first plurality of struts. | 06-04-2009 |
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 |
20090155055 | COOLING FAN - A cooling fan for cooling a heat source includes a frame ( | 06-18-2009 |
20090246002 | GAS TURBINE ENGINE ASSEMBLY AND METHOD OF ASSEMBLING SAME - A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground. | 10-01-2009 |
20100008765 | TAILORABLE DESIGN CONFIGURATION TOPOLOGIES FOR AIRCRAFT ENGINE MID-TURBINE FRAMES - An expandable mid-turbine frame assembly includes a first bearing cone, a second bearing cone and a mid-turbine frame. The mid-turbine frame assembly connects to a gas turbine engine casing and transfers a first load from a first bearing and a second load from a second bearing towards the engine casing. The first bearing cone transfers the first load from the first bearing. The second bearing cone transfers the second load from the second bearing. The mid-turbine frame is connected to the first and second bearing cones and includes segments. Each segment includes a pre-stressed support for equilibrating the first and second loads. | 01-14-2010 |
20100272558 | Turbine rotor support apparatus and system - An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface. | 10-28-2010 |
20110110764 | HYDRAULIC MACHINE, AND AN ENERGY CONVERSION INSTALLATION INCLUDING SUCH A MACHINE - This hydraulic machine comprises a wheel supported by a shaft ( | 05-12-2011 |
20120321447 | FLEXIBLE REAR BEARING MOUNTING, HAVING AN ABUTMENT, FOR A TURBINE ENGINE - An assembly including a part for mounting at least one shaft bearing of a turbine engine and a support part that forms an abutment for the mounting part. The mounting part includes at least one channel through which engine gases pass, and connection parts that are capable of connecting the channel to an outer structure of the engine and to a housing holding the bearing. At least one of the connection parts is flexible so as to enable radial movement of the channel, an amplitude of the radial movement being limited by at least one of the elements of the mounting part coming onto an abutment supported by the support part. The support part extends longitudinally with regard to the direction of the rotational axis of the turbine engine so as to generate a turbine shroud that is configured to be positioned in alignment with a turbine wheel of the turbine engine. | 12-20-2012 |
20130011242 | GAS TURBINE ENGINE WITH ANGLED AND RADIAL SUPPORTS - A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall. | 01-10-2013 |
20130022451 | BEARING SURFACE COMBINED LOAD-LOCK SLOTS FOR TANGENTIAL ROTORS - A system for assembling a turbine engine component has a disk having a groove, which groove has a bearing surface and an upper wall, at least one locking slot being positioned at an intersection of the bearing surface and the upper wall; each locking slot having a shaped surface; and at least one lock having a shape which matches and mates with the shaped surface of the locking slot; and said locking slots providing clearance to assemble blades into the disk. | 01-24-2013 |
20130101399 | RAM AIR FAN BEARING HOUSING - A ram air fan bearing housing for a ram air fan assembly includes a bearing section, a disk section, and radial support ribs. The disk section is at one end of the bearing section for connecting the bearing section to the ram air fan assembly. The disk section includes an outer ring with a circumferential support rib; and a disk wall connecting the outer ring to the bearing section. The disk wall includes arcuate cooling slots defined by edges, including an arcuate edge having an arc center at an axis of the bearing housing and positioned adjacent to and radially inward from the circumferential support rib. The radial support ribs extend axially along most of the length of the bearing section and extend radially along the disk wall to the circumferential support rib. The radial support ribs and the cooling slots alternate about the axis of the bearing housing. | 04-25-2013 |