| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415210100 | Fixed between radially separate surfaces | 12 |
| 20080213092 | REPAIRED VANE ASSEMBLIES AND METHODS OF REPAIRING VANE ASSEMBLIES - Methods are provided for repairing a vane assembly, where the vane assembly includes an inner annular housing, an outer annular housing, and a vane extending therebetween. In one embodiment, the method includes removing an identified section of the vane to thereby form a pocket in an inner surface of the outer annular housing, a slot through the inner annular housing, and an edge on the vane, inserting a replacement vane portion with an advanced coating through the formed slot such that a first edge of the replacement vane portion is disposed in the pocket and at least a portion of the first edge is spaced apart from at least a portion of the outer annular housing inner surface, and welding a section of the replacement vane portion to the annular inner annular housing. The repaired vane assembly is also provided. | 09-04-2008 |
| 20120087788 | STEAM TURBINE NOZZLE ASSEMBLY HAVING FLUSH APERTURES - A steam turbine nozzle assembly having a flush aperture is disclosed. In one embodiment, the steam turbine nozzle assembly includes a diaphragm assembly comprising: an inner diaphragm ring segment; an outer diaphragm ring segment; a static nozzle blade positioned between the inner diaphragm ring segment and the outer diaphragm ring segment; and a first cavity between the static nozzle blade and one of the inner diaphragm ring segment or the outer diaphragm ring segment; wherein the one of the inner diaphragm ring segment or the outer diaphragm ring segment includes a first aperture fluidly connected with the first cavity. | 04-12-2012 |
| 20120163969 | TURBINE INCLUDING EXHAUST HOOD - A turbine includes an inner casing, a rotor extending in a longitudinal direction, and rows of buckets transversely disposed on the rotor. A bearing cone covering a portion of the rotor and a flow guide extending from the inner casing define an annular passage for flow of exhaust gases. Exhaust gas movement is facilitated by a guide cap having a streamlined surface and situated in a downstream direction of the flow guide, a tip leakage flow injection channel to inject exhaust gases at the inner surface of the flow guide, an incline of the casing of the turbine surrounding the last stage buckets relative to the longitudinal axis, or use of a first portion of the annular passage with a substantially constant surface area and a second portion of the annular passage with a progressively increasing surface area. | 06-28-2012 |
| 20120315136 | INNER PERIPHERAL SURFACE SHAPE OF CASING OF AXIAL-FLOW COMPRESSOR - A generating line of a casing surrounding an outer periphery of vanes of a stator disposed downstream of a rotor of the axial-flow compressor includes: a recessed region recessed outward in a radial direction from a position forward of a front edge of each of the vanes to a position rearward of a rear edge of the vane; and a protruding region bulging inward in the radial direction at an intermediate position of the recessed region in a front-rear direction thereof. Thus, a distribution of static pressure in the radial direction on a surface of the vane is improved by a first recessed portion forward of the protruding region, and the static pressure on the tip side is raised by a second recessed portion rearward of the protruding region. | 12-13-2012 |
| 20130195643 | STRESS RELIEVING SLOTS FOR TURBINE VANE RING - A turbine vane ring has a radially outer and inner annular shrouds defining therebetween an annular gaspath. Circumferentially spaced-apart airfoil vanes extend radially across the gaspath between the outer and the inner shrouds. The radially outer shroud has a circumferentially continuous cylindrical wall extending axially from a leading edge to a trailing edge. A set of circumferentially distributed stress relieving slots is defined in the leading edge of the cylindrical wall at locations adjacent to the leading edge of at least some of said airfoil vanes. The stress relieving slots extend radially through the cylindrical wall from the radially inner surface to the opposed radially outer surface thereof. | 08-01-2013 |
| 20140322007 | TURBINE DIAPHRAGM CONSTRUCTION - A turbine diaphragm has radially inner and outer hollow diaphragm rings ( | 10-30-2014 |
| 20140356159 | LOW HUB-TO-TIP RATIO FAN FOR A TURBOFAN GAS TURBINE ENGINE - A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (R | 12-04-2014 |
| 20150030443 | SPLIT DAMPED OUTER SHROUD FOR GAS TURBINE ENGINE STATOR ARRAYS - A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud. | 01-29-2015 |
| 20150139790 | STEAM TURBINE NOZZLE SEGMENT HAVING TRANSITIONAL INTERFACE, AND NOZZLE ASSEMBLY AND STEAM TURBINE INCLUDING SUCH NOZZLE SEGMENT - Various embodiments include steam turbine static nozzles having transitional interfaces. In one embodiment a steam turbine static nozzle blade includes: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a first side having one of: an arcuate concave surface extending substantially an entire length of the sidewall, or an arcuate convex surface extending substantially the entire length of the sidewall; and a second side opposing the first side and having an angled interface extending substantially the entire length of the sidewall. | 05-21-2015 |
| 20150139791 | AIRCRAFT ENGINE DRIVESHAFT VESSEL ASSEMBLY AND METHOD OF ASSEMBLING THE SAME - A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane. The driveshaft vessel includes a forward face, an aft face, and opposing side faces and is configured to house at least a portion of a radial driveshaft. The outlet guide vane includes a leading edge and a trailing edge. The length of the trailing edge is substantially equal to a length of the forward face of the driveshaft vessel such that the trailing edge of the outlet guide vane is faired into the forward face of the driveshaft vessel. | 05-21-2015 |
| 20160123166 | TURBINE VANES WITH VARIABLE FILLETS - An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed. | 05-05-2016 |
| 20160377053 | VERTICAL AXIS WIND TURBINE - A vertical axis wind turbine (VAWT) with improved and optimized wind-directing, wind-shaping, and wind-power conversion features is disclosed. The shapes of these features directly affect the ability of the VAWT to use the power of moving air, such as wind, to spin a rotor and create torque on a rotor shaft to generate electricity. The wind-power-conversion mechanical efficiency of the invention is significantly improved over previous efforts, to the point that the invention can convert wind energy into electrical power at a price-to-performance ratio that competes with or surpasses existing alternative energy technologies. | 12-29-2016 |
