Class / Patent application number | Description | Number of patent applications / Date published |
416191000 | Segmental shroud | 17 |
20100061856 | STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The cover comprises a first flat section, a second flat section, and a depression section located laterally between the first flat section and second flat section. The depression section is located below the first flat section at a first end where the first flat section and depression section are contiguous. The depression section rises above to the second flat section at a second end where the second flat section and depression section are contiguous. The second flat section is raised above the first flat section. The cover is positioned at an angle relative to the tip section, wherein the angle ranges from about 10 degrees to about 30 degrees. | 03-11-2010 |
20110008170 | SHROUD AND ROTARY VANE WHEEL OF PROPELLER FAN AND PROPELLER FAN - A shroud includes a body portion | 01-13-2011 |
20110268575 | SPOKE FOR A STATOR COMPONENT, STATOR COMPONENT AND METHOD FOR MANUFACTURING A STATOR COMPONENT - A spoke for a stator component for conducting a gas flow during operation includes at least two wall parts connecting a leading edge and a trailing edge of the spoke, and a middle portion between a first and a second end portion along a longitudinal extension. A first imaginary extension line from a first segment of the first wall part to a second segment of the second wall part and a second imaginary extension line from a second segment of the first wall part to a first segment of the second wall part are intersecting within the wall parts in the middle portion. | 11-03-2011 |
20120107123 | Shroud Segment to be Arranged on a Blade - A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas. | 05-03-2012 |
20120275919 | HIGH EFFICIENCY WIND TURBINE HAVING INCREASED LAMINAR AIRFLOW - A wind turbine is provided with turbine blades mounted for axial rotation about an axis. The blades are surrounded by a shroud to define an axial air passage. A conical ring is attached to the shroud and includes vanes for directing the airflow. Plates are attached to the shroud at a position radially outward from the shroud forming an air passage between the shroud and the plates. The plates have gaps between the adjacent plates so that air exiting the downstream opening of the shroud and air moving through the axial air passage between the shroud and the plates are mixed and a portion of the mixed air exits through the gaps. | 11-01-2012 |
20130011265 | CHEVRON PLATFORM TURBINE VANE - Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge. | 01-10-2013 |
20130209258 | TIP SHROUDED BLADE - A tip shrouded blade includes an airfoil rotatable about an axial centerline. Also included is a tip shroud connected at a radially outer tip of the airfoil, wherein the tip shroud includes at least one portion angled about a tangential axis defined by the radially outer tip of the airfoil. | 08-15-2013 |
20130266447 | ANNULUS FILLER - A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine. | 10-10-2013 |
20140023506 | DAMPER SYSTEM AND A TURBINE - A damper system and a turbine are provided. The damper system includes a plurality of CMC blades. Each CMC blade has a first member of a tip shroud, the first member opposite a second member of the tip shroud, a radial flange extending between the first member and the second member of the tip shroud, and at least one aperture in the radial flange for receiving a damping member, the dampening member joining and dampening adjacent CMC blades. The turbine includes a plurality of turbine blade tip shroud segments, each tip shroud segment having a first surface that cooperates with the first surface in an adjacent tip shroud segment to form a first opening, each tip shroud segment having a first receiving surface. The turbine includes a damper member that abuts the first receiving surface of each tip shroud segment. | 01-23-2014 |
20140154082 | PRE-SINTERED PREFORM REPAIR OF TURBINE BLADES - A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade. | 06-05-2014 |
20150147179 | BLADE WITH 3D PLATFORM COMPRISING AN INTER-BLADE BULB - A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface. | 05-28-2015 |
20150315918 | SHROUDED TURBINE BLADE WITH CUT CORNER - A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attacked to a shroud. A corner of the shrouded turbine blade can be removed after determining the vibration characteristic. | 11-05-2015 |
20150377035 | SEGMENTED TURBINE SHROUD WITH SEALS - A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier segment, a blade track segment, and a radial seal element that seals a radial interface between the carrier segment and the blade track segment. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments. | 12-31-2015 |
20160024939 | Rotor blade assembly, turbomachine comprising a rotor blade assembly and method of assembling a rotor blade assembly - A rotor blade assembly has aerofoil, root and supplementary components. The aerofoil component includes an aerofoil shaped section and aerofoil connection section for connecting the aerofoil component with the root component. The root component includes a first platform section, first root connection section and root section arranged for securing the root component to a further component. The supplementary component includes a second platform section and second root connection section. The aerofoil shaped section includes metal foam. The aerofoil component, root component and supplementary component are arranged such that the root component and supplementary component are attached to each other; the first platform section and second platform section build a common platform of the rotor blade assembly; the first root connection section and the second root connection section build a common cavity between the common platform and the root section; and the aerofoil connection section is secured in the common cavity. | 01-28-2016 |
20160076385 | TURBOMACHINE BLADE TIP SHROUD - Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion. | 03-17-2016 |
20160108749 | TURBINE BLADE TIP SHROUD - A turbine blade tip shroud ( | 04-21-2016 |
20160194973 | FAN PLATFORM WITH LEADING EDGE TAB | 07-07-2016 |