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| Number | Title | Issue Date |
| 8162603 | Vane frame for a turbomachine and method of minimizing weight thereof A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shrou... | 04/24/2012 |
| 8128357 | Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated gui... | 03/06/2012 |
| 8070432 | Static gas turbine component and method for repairing such a component A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load c... | 12/06/2011 |
| 7946811 | Assembly of sectorized fixed stators for a turbomachine compressor An assembly of sectorized fixed compressors for a turbomachine compressor is disclosed. The assembly is a single piece and includes two coaxial rings connected by radial airfoils. The outer ring includes two annular mounting lugs on a casing of the compressor. At le... | 05/24/2011 |
| 7794203 | Joining device for joining two assemblies, for example for a stator of a turbomachine A joining device including a clevis and a connecting member is disclosed. The connecting member includes a through hole which is housed between a first and a second lug of the clevis. These lugs respectively have a first clevis hole and a second clevis hole. The dev... | 09/14/2010 |
| 7748956 | Non-stablug stator apparatus and assembly method A method of assembling a stator apparatus includes providing a first vane having an airfoil section located between a first platform section and a second platform section, positioning a first shroud ring adjacent to the first vane, welding the first platform section... | 07/06/2010 |
| 7648336 | Apparatus and method for assembling a gas turbine stator A gas turbine stator includes a vane assembly, and a platform that is configured to receive the vane assembly. The vane assembly includes a vane and a cap. The vane extends radially from the cap. The vane includes a pressure side shell and a separate suction side sh... | 01/19/2010 |
| 7470109 | Machine tooled diaphragm partitions and nozzles Partitions have an airfoil coupled at opposite ends to inner and outer side walls. The side walls each mount radially extending male dovetails. The inner web and outer ring of a diaphragm include complementary shaped dovetail grooves. The male dovetails have reduced... | 12/30/2008 |
| 7434313 | Method for repairing a turbine engine vane assembly and repaired assembly A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or... | 10/14/2008 |
| 7427187 | Welded nozzle assembly for a steam turbine and methods of assembly A steam turbine nozzle singlet having a blade or airfoil between inner and outer sidewalls is provided. The sidewalls include steps or flanges which are received in complementary recesses in the rings enabling axially short low heat input welds e.g., e-beam welds. T... | 09/23/2008 |
| 7410342 | Airfoil support A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer ... | 08/12/2008 |
| 7360990 | Methods and apparatus for assembling gas turbine engines A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional ... | 04/22/2008 |
| 7363281 | Reduction of fitness evaluations using clustering techniques and neural network ensembles The invention relates to an evolutionary optimization method. First, an initial population of individuals is set up and an original fitness function is applied. Then the offspring individuals having a high evaluated quality value as parents are selected. In a third ... | 04/22/2008 |
| 7329096 | Machine tooled diaphragm partitions and nozzles Partitions have an airfoil coupled at opposite ends to inner and outer side walls. The side walls each mount radially extending male dovetails. The inner web and outer ring of a diaphragm include complementary shaped dovetail grooves. The male dovetails have reduced... | 02/12/2008 |
| 7329087 | Seal-less CMC vane to platform interfaces A stator vane assembly for a gas turbine includes a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein an interface between the airfoil and at least one of the radially inner and outer platforms is shaped to create a circu... | 02/12/2008 |
| 7311495 | Vane support in a gas turbine engine A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane ... | 12/25/2007 |
| 7278821 | Methods and apparatus for assembling gas turbine engines A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within ea... | 10/09/2007 |
| 7249462 | Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils... | 07/31/2007 |
| 7249929 | Bleed housing A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint ... | 07/31/2007 |
| 7246484 | FLADE gas turbine engine with counter-rotatable fans An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans. A core en... | 07/24/2007 |
| 7229245 | Vane platform rail configuration for reduced airfoil stress A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their res... | 06/12/2007 |
| 7195453 | Compressor stator floating tip shroud and related method A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade... | 03/27/2007 |
| 7195454 | Bullnose step turbine nozzle A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and s... | 03/27/2007 |
| 7185433 | Turbine nozzle segment and method of repairing same A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the... | 03/06/2007 |
| 7179052 | Assembly type nozzle diaphragm, and method of assembling the same A nozzle diaphragm assembly includes a diaphragm outer ring having a groove opened toward an inner diameter side to be continuous in an inner peripheral direction; a diaphragm inner ring having a groove opened toward an outer diameter side to be continuous in an out... | 02/20/2007 |
| 7172388 | Multi-point seal A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and sec... | 02/06/2007 |
| 7172389 | Method for making a repaired turbine engine stationary vane assembly and repaired assembly A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the ... | 02/06/2007 |
| 7160078 | Mechanical solution for rail retention of turbine nozzles A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment se... | 01/09/2007 |
| 7147434 | Nozzle ring with adhesive bonded blading for aircraft engine compressor Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive. ... | 12/12/2006 |
| 7121793 | Undercut flange turbine nozzle A turbine nozzle includes a vane joined to opposite inner and outer bands. The inner band includes a pocket adjoining a flange which recesses in part the inner surface of the band. The pocket undercuts the flange to form a notch at the base thereof. ... | 10/17/2006 |
| 7114917 | Vane assembly for a gas turbine engine An exhaust diffuser unit for a gas turbine engine includes an outer ring, a diffuser cone and vanes, all made from a ceramic matrix composite material. Each vane has end components which have apertures through which a metallic support strut extends. The support stru... | 10/03/2006 |
| 7114920 | Shroud and vane segments having edge notches Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent ... | 10/03/2006 |
| 7108480 | Method and apparatus for balancing turbine rotors A method facilitates balancing a gas turbine rotor. The method includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opp... | 09/19/2006 |
| 7104756 | Temperature tolerant vane assembly A vane assembly 10 suitable for a turbine engine features a refractory vane 12 with an internal cavity 20 and a pair of flexible metallic baffles 26 extending into the cavity from spanwisely opposite ends of the vane. A rigid fastener ... | 09/12/2006 |
| 7097432 | Sliding vane turbocharger with graduated vanes A turbocharger having a variable geometry turbine inlet incorporating a cylindrical piston movable to vary the area of the inlet nozzle into the turbine. Vanes mounted to the piston for flow control in the nozzle are received through a slotted heat shield which prov... | 08/29/2006 |
| 7070387 | Gas turbine stator housing A housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, th... | 07/04/2006 |
| 7070388 | Inducer with shrouded rotor for high speed applications An inducer rotor rotatably mountable in an inducer for pressurizing fluid traveling through the inducer. The inducer rotor includes a hub. The hub has a central axis and a plurality of blades extending radially outward from the hub. Each blade extends from a root po... | 07/04/2006 |
| 7063505 | Gas turbine engine frame having struts connected to rings with morse pins A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced ap... | 06/20/2006 |
| 7052234 | Turbine vane collar seal A collar seal is configured for a turbine nozzle vane. The seal includes a retainer having a circumferential airfoil contour conforming with the airfoil contour of the vane. A flexible leaf is surrounded by the retainer and fixedly joined thereto. A woven sheath enc... | 05/30/2006 |
| 7048499 | In-line centrifugal fan An inline centrifugal mixed flow fan (20) includes an axially extending intake conduit (22). An inlet cone (28) is disposed at an intake end (24). An impeller (30) is disposed downstream of the inlet cone and includes a centrally d... | 05/23/2006 |
