Patent application number | Description | Published |
20080260522 | GAS TURBINE ENGINE WITH INTEGRATED ABRADABLE SEAL AND MOUNT PLATE - An abradable sealing land for a gas turbine engine includes a mount plate and an open cell portion which is to be abraded. Both portions are formed integrally from a single piece of material. | 10-23-2008 |
20080260523 | GAS TURBINE ENGINE WITH INTEGRATED ABRADABLE SEAL - An abradable land assembly for a gas turbine engine includes a mount portion and an open cell portion which is to be abraded. Both portions are formed integrally from a single piece of material. | 10-23-2008 |
20090051120 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals - Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative turbine assembly for a gas turbine engine includes a turbine having a hydrostatic seal formed by a seal face and a seal runner. | 02-26-2009 |
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 |
20090238683 | Vane with integral inner air seal - A stator vane segment for a gas turbine engine includes at least one airfoil joined to an outer shroud and an inner platform. A sealing element having a first platform radially inward of the inner platform and an abradable material covering at least a portion of the first platform is integrally joined to the inner platform. | 09-24-2009 |
20090257877 | ASYMMETRICAL ROTOR BLADE FIR-TREE ATTACHMENT - A rotor blade for a gas turbine engine includes an asymmetric attachment section received within a rotor disk rim with an asymmetric slot. | 10-15-2009 |
20110206522 | ROTATING AIRFOIL FABRICATION UTILIZING CMC - Disclosed is an airfoil comprising a plurality of ceramic matrix composite (CMC) fabric sheets which are layered to form a single, layered fabric sheet. The layered fabric sheet is formed so as to define a pressure and suction side of the airfoil. The airfoil includes primary fibers which extend radially outwardly from a rotor disk, for example. In this way, the airfoil is suitable for use in a gas turbine engine due to the temperature resistance of CMC and the strength provided by the primary fibers. | 08-25-2011 |
20120297790 | INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK GEOMETRY FOR A GAS TURBINE ENGINE - A CMC disk for a gas turbine engine includes a CMC hub defined about an axis and a multiple of CMC airfoils integrated with the CMC hub. | 11-29-2012 |
20120297791 | CERAMIC MATRIX COMPOSITE TURBINE EXHAUST CASE FOR A GAS TURBINE ENGINE - A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone. | 11-29-2012 |
20120301269 | CLEARANCE CONTROL WITH CERAMIC MATRIX COMPOSITE ROTOR ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure. | 11-29-2012 |
20120301275 | INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR MODULE FOR A GAS TURBINE ENGINE - A rotor module for a gas turbine engine includes a multiple of CMC airfoil rows which extend from a common CMC drum. | 11-29-2012 |
20120301285 | CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE - A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring. | 11-29-2012 |
20120301303 | HYBRID CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE - A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring. | 11-29-2012 |
20120301305 | INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK HUB GEOMETRY FOR A GAS TURBINE ENGINE - A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore. | 11-29-2012 |
20120301306 | HYBRID ROTOR DISK ASSEMBLY FOR A GAS TURBINE ENGINE - A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures. | 11-29-2012 |
20120301313 | CERAMIC MATRIX COMPOSITE CONTINUOUS "I"-SHAPED FIBER GEOMETRY AIRFOIL FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous āIā-shaped fiber geometry. | 11-29-2012 |
20120301314 | HYBRID ROTOR DISK ASSEMBLY WITH A CERAMIC MATRIX COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composite (CMC) airfoil for a gas turbine engine includes a CMC root section which extends to form a CMC airfoil section, the CMC root section defines a bore along a non-linear axis. | 11-29-2012 |
20120301315 | CERAMIC MATRIX COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion. | 11-29-2012 |
20120301317 | HYBRID ROTOR DISK ASSEMBLY WITH CERAMIC MATRIX COMPOSITES PLATFORM FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composite (CMC) platform for an airfoil of a gas turbine engine includes a CMC platform segment which at least partially defines an airfoil profile. | 11-29-2012 |
20130108445 | SPOKED ROTOR FOR A GAS TURBINE ENGINE | 05-02-2013 |
20130108466 | ASYMETRICALLY SLOTTED ROTOR FOR A GAS TURBINE ENGINE | 05-02-2013 |
20130119617 | TURBOMACHINERY SEAL - A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor. | 05-16-2013 |
20130219918 | BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING - A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine. | 08-29-2013 |
20130219920 | GAS TURBINE ENGINE COOLING SYSTEM - A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum. | 08-29-2013 |
20130287565 | TEC Mount Redundant Fastening - A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link. | 10-31-2013 |
20130323010 | TURBINE COOLANT SUPPLY SYSTEM - A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore. | 12-05-2013 |
20140294589 | ASYMMETRICALLY SLOTTED ROTOR FOR A GAS TURBINE ENGINE - A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path. | 10-02-2014 |