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| Number | Title | Issue Date |
| 8016549 | Turbine engine alloys and crystalline orientations A method is provided for engineering a single crystal cast gas turbine engine first component for cooperating with a second component. An at least local first operational stress on the first component is determined. The first operational stress has a first direction... | 09/13/2011 |
| 7967555 | Process to cast seal slots in turbine vane shrouds A process for casting a turbine engine component is provided. The process comprises the steps of placing a refractory core assembly comprising two intersecting plates in a die, encapsulating the refractory core assembly in a wax pattern having the form of the turbin... | 06/28/2011 |
| 7665957 | Heat shield for sealing a flow channel of a turbine engine A heat shield arrangement for local separation of a flow channel within a turbine engine, with respect to a stator housing radially surrounding the flow channel is provided. The heat shield includes two axially opposite joining contours which are each engageable wit... | 02/23/2010 |
| 7665958 | Heat accumulation segment A heat accumulation segment for local separation of a flow duct inside a turbo engine, from a stator housing that radially surrounds the flow duct is provided. The heat accumulation segment includes two axially opposed joining contoured elements that are engagable w... | 02/23/2010 |
| 7658593 | Heat accumulation segment A heat accumulation segment for local separation of a flow duct inside a turbo engine, from a stator housing that radially surrounds the flow duct is provided. The heat accumulation segment includes two axially opposed joining contoured elements that are engageable ... | 02/09/2010 |
| 7614845 | Turbomachine inner casing fitted with a heat shield The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing... | 11/10/2009 |
| 7497658 | Stacked reaction steam turbine stator assembly Disclosed herein is a stator assembly for a steam turbine. The stator assembly includes a stacked stator section and a retention device. The stacked stator section has a plurality of adjacently disposed stator plates. The retention device retains the adjacent stator... | 03/03/2009 |
| 7445425 | Seal assembly A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided betw... | 11/04/2008 |
| 7399156 | Turbine housing of an exhaust gas turbocharger with a variable turbine geometry A turbine housing of an exhaust gas turbocharger with a variable turbine geometry is provided, having a support ring to which vanes are fastened which are adjustable for controlling the charge pressure, and having a covering ring for the vanes. The support ring and ... | 07/15/2008 |
| 7360769 | Sealing arrangement A sealing arrangement, for example between adjacent nozzle guide vane platform segments (2A, 2B) in a gas turbine engine, comprises a seal (12) which extends across a gap (13) between the platform segments (2A, 2B) and engag... | 04/22/2008 |
| 7351042 | Structure of scroll of variable-throat exhaust turbocharger and method for manufacturing the turbocharger A ratio of cross sectional area A of a scroll passage to a scroll radius R (A/R) can be increased without increasing the size of a turbine casing and with very simple construction. An exhaust turbine capacity can thus be increased, so that a variable-throat exhaust ... | 04/01/2008 |
| 7347661 | Casing arrangement A casing arrangement of a gas turbine includes a casing member, which is formed to extend at least partially around the component. The casing member defines a fluid flow path for the flow of a cooling fluid therethrough. ... | 03/25/2008 |
| 7334981 | Counter-rotating gas turbine engine and method of assembling same A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of rows of turbine blades configured to rotate in a first rotational direction, providing a low-pressure turbine outer rotor that ... | 02/26/2008 |
| 7326037 | Centrifugal pumps having non-axisymmetric flow passage contours, and methods of making and using same Centrifugal pumps and methods of making and using them are disclosed. One inventive pump includes a plurality of flow passages, at least one pump component having one or more non-axisymmetric flow passage contours defined at least in part by non-equal blade or vane ... | 02/05/2008 |
| 7261514 | Sealing arrangement, in particular for the blade segments of gas turbines A sealing arrangement has two bodies with two end faces which extend along a longitudinal axis, adjoin one another while forming a gap, the width of which can vary between zero and a maximum width. The gap is covered by a sealing strip which lies transversely to the... | 08/28/2007 |
| 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 |
| 7222422 | Method for refurbishing surfaces subjected to high compression contact A process for refurbishing a worn surface of a shroud support component of a turbomachine, as well as a shroud support component refurbished with the process. The process generally entails removing a surface region of the worn surface so as to define a repair surfac... | 05/29/2007 |
| 7198465 | Fastening arrangement for a split casing A casing of a hydraulic machine such as a gas turbine is formed as a horizontally split type flangeless casing. The flangeless casing consists of an upper casing and a lower casing joined together at joint faces and fastened by fastening bolts. The fastening bolt ha... | 04/03/2007 |
| 7198454 | Variable stator vane arrangement for a compressor An axial flow compressor (16) comprises a plurality of variable stator vanes (32) circumferentially spaced apart and extending radially. Each variable stator vane (32) is rotatably mounted on a compressor casing (28). A control ring (3... | 04/03/2007 |
| 7198459 | Casing arrangement for a turbocharger of an internal combustion engine A casing assembly for a turbocharger of an internal combustion engine includes a rotor casing having an intake duct and an exhaust flow passage which is connected to an exhaust flange and constructed for attachment to the rotor casing such as to allow a relative mov... | 04/03/2007 |
| 7188477 | High temperature dynamic seal for scramjet variable geometry A seal assembly for use in an engine, such as a scramjet engine, having a movable element, such as inlet cowl flap, is provided. The movable element has an outboard structural member which requires thermal protection. The seal assembly includes a sealing element and... | 03/13/2007 |
| 7152864 | Seal assembly It is disclosed a seal assembly (5) which comprises a layered structure. It consists of a first layer (9, 12) of a base material, a second layer (10) of thermal insulating material on top of the base material and a third layer (11, 12) of... | 12/26/2006 |
| 7124572 | Recuperator and turbine support adapter for recuperated gas turbine engines A recuperator and turbine support adapter for securing a recuperator to a combustor case is provided. The recuperator and turbine support adapter comprises an outer strutted body, an inner strutted body and a thermal spring. The thermal spring allows for thermal exp... | 10/24/2006 |
| 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 |
| 7100358 | Turbine exhaust case and method of making A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner a... | 09/05/2006 |
| 7096712 | Material testing system for turbines The wear resistance of impellers used in multi-stage turbine pumps is tested by using a multi-stage turbine pump having impellers with different physical properties to pump a fluid containing small amounts of an abrasive material. After the fluid has been pumped for... | 08/29/2006 |
| 7097422 | Hoop stress relief mechanism for gas turbine engines A hoop stress relief mechanism is disclosed for use on a rotary body to relieve stress caused by both thermal and centrifugal forces. The mechanism may consist of a J-shaped slot cut from the outer rim of the rotary body a distance inwardly toward the axis of rotati... | 08/29/2006 |
| 7097423 | Endface gap sealing for steam turbine diaphragm interstage packing seals and methods of retrofitting Spline seals are disposed in circumferentially registering slots of adjacent arcuate packing seal segments disposed in grooves on inner hooks of a steam turbine diaphragm assembly. The spline seals extend in a gap between the endfaces of the segments and minimize or... | 08/29/2006 |
| 7086830 | Tube-type vortex reducer with retaining ring A tube-type vortex reducer conducts cooling air in a compressor (1) of a gas turbine. Radial secondary air tubes (2) are arranged in a disk interspace (5) and attached to a compressor disk (3) with their radial outward end sections. The e... | 08/08/2006 |
| 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 |
| 7052235 | Turbine engine shroud segment, hanger and assembly A turbine engine shroud segment comprises a body including an outer surface from and along which a segment projection extends away from and in an axial direction. The segment projection includes circumferentially spaced apart segment support surfaces. A shroud hange... | 05/30/2006 |
| 7033138 | Ring segment of gas turbine An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the pre... | 04/25/2006 |
| 7021061 | Heat shield arrangement for a hot-gas conducting component, in particular for structural pieces of gas turbines and method for production of said arrangement The invention relates to a heat shield arrangement for a hot gas conducting structure, in particular a metal component of a gas turbine unit or combustion chamber, with the heat shield elements anchored adjacently on a support structure to cover a surface. Said heat... | 04/04/2006 |
| 7013652 | Gas turbo set A gas turbo set comprises a compressor, combustion chamber and turbine, a common rotor shaft having arranged on it, within the compressor, a plurality of rows of compressor moving blades and, within the turbine, a plurality of rows of turbine moving blades, which al... | 03/21/2006 |
| 6988869 | Turbine installation, especially steam turbine installation The invention relates to a turbine installation, especially a steam turbine installation. The inventive turbine installation comprises at least two partial turbines, each of the partial turbines having a rotor disk that extends along the main axis. Said rotor disks ... | 01/24/2006 |
| 6939106 | Sealing of steam turbine nozzle hook leakages using a braided rope seal A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle ... | 09/06/2005 |
| 6910858 | Seal A turbine engine has a rotor shaft rotatably carried within a support structure. A seal is carried by the support structure circumscribing the shaft and having a brushpack for sealing with the shaft. A first plate on a first side of the brushpack has a first radial ... | 06/28/2005 |
| 6685425 | Inlet bleed heater for heating inlet air to a compressor and methods of fabricating and transporting the heater An inlet bleed heater for flowing heated air to the inlet of a compressor is fabricated wholly at a factory site. The heater interconnects a manifold which receives extraction air from the compressor to down tubes in the inlet air duct to supply heated ex... | 02/03/2004 |
| 6524062 | Retention sleeve for a thermal medium carrying tube in a gas turbine Multiple tubes are connected to steam supply and spent cooling steam return manifolds for supplying cooling steam to buckets and returning spent cooling steam from the buckets to the manifolds, respectively. The tubes are prevented from axial movement in ... | 02/25/2003 |
| 6471478 | Axial seal system for a gas turbine steam-cooled rotor An axial seal assembly is provided at the interface between adjacent wheels and spacers of a gas turbine rotor and disposed about tubes passing through openings in the rotor adjacent the rotor rim and carrying a thermal medium. Each seal assembly includes... | 10/29/2002 |
