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| Number | Title | Issue Date |
| 7958735 | Turbine static structure for reduced leakage air A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending ... | 06/14/2011 |
| 7926291 | Bearing supported rotor shaft of a gas turbine engine A small gas turbine engine that operates at high rotational speeds and includes a rotor shaft that is supported on both ends by ball bearings. The aft end ball bearings includes an outer race mounted to the support structure in such a way that axial displacement of ... | 04/19/2011 |
| 7540158 | Multistage turbine with single blade row, and gas turbine using same In order to desirably prevent leakage of a working fluid from the tip clearance to reduce loss of a heat drop of the working fluid, a first corresponding blade of a second stationary blade row, which corresponds to a first reference blade of a first stationary blade... | 06/02/2009 |
| 7530233 | Gas turbine and sealing means for a gas turbine A gas turbine, with a fixed inner housing, arranged concentric to the rotor, with a through flow of working medium, is disclosed. The housing comprises at least two serial rings with an annular gap left between two directly adjacent rings, whereby an annular sealing... | 05/12/2009 |
| 7448221 | Turbine engine rotor stack A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transm... | 11/11/2008 |
| 7424360 | Overspeed control system for gas turbine electric powerplant A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control subsystem. When an overspeed condition of the gas turbine engine is de... | 09/09/2008 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7340881 | Gas turbine combustor The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed a... | 03/11/2008 |
| 7328098 | Determining bleed valve failures in gas turbine engines The invention detects gas turbine bleed valve position discordances. The invention derives a modified exhaust gas temperature derivative as the predictive criteria in conjunction with a control logic to determine bleed valve position discordances that may indicate a... | 02/05/2008 |
| 7326917 | Wear monitor for turbo-machine A wear determination device for determining vibration in a turbine engine component to reduce wear in a turbine engine. The wear determination device may be capable of measuring vibrations in a turbine engine component. The vibration measurement may be used to deter... | 02/05/2008 |
| 7241106 | Combined cycle boundary layer turbine A two staged fluid propulsion apparatus of the type which utilizes prior art pitched blades combined with solid boundary layer disks supported by a novel rotating tubular flow conduit perforated to allow fluid flow to from the interior of the tube to the exterior su... | 07/10/2007 |
| 7229249 | Lightweight annular interturbine duct An interturbine duct for channelling combustion gases between two axial turbine stages. The interturbine duct is made of sheet material to provide a relatively lightweight construction. ... | 06/12/2007 |
| 7229247 | Duct with integrated baffle An integrated duct and baffle arrangement employing a hairpin transition area such that the construction is adapted to flex under thermal conditions. ... | 06/12/2007 |
| 7195446 | Counter-rotating turbine engine and method of assembling same A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rota... | 03/27/2007 |
| 7185484 | Methods and apparatus for assembling a gas turbine engine Methods and apparatus for assembling a gas turbine engine are provided. The method includes coupling a first turbine shaft that includes m rows of turbine blades within the gas turbine such that the first turbine shaft is rotatable in a first direction, and coupling... | 03/06/2007 |
| 7174719 | Gas turbine engine with seal assembly A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid... | 02/13/2007 |
| 7168913 | Twin-spool turbojet with means for driving ancillary machines A turbojet includes a differential gear with a first planetary pinion driven by the shaft of the high pressure spool and a second planetary pinion driven by the shaft of the low pressure spool. The planetary pinions drive satellite pinions mounted in a cage by which... | 01/30/2007 |
| 7153023 | Methods and apparatus for installing process instrument probes A method of mounting an instrument probe using an adapter post is provided. The method includes coupling an attachment end of the adapter post to a first wall defined between a cavity and an annulus, coupling an opposite sealing end of the adapter post to a second w... | 12/26/2006 |
| 7114322 | Gas-turbine power generating installation and method of operating the same A gas-turbine power generating installation capable of effectively utilizing gases produced in overage gas fields, etc. and a method of operating the installation are provided. The gas-turbine power generating installation is installed in the vicinity of an outrage ... | 10/03/2006 |
| 7093448 | Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured betwee... | 08/22/2006 |
| 7044718 | Radial-radial single rotor turbine A rotor for use in turbine applications has a radial compressor/pump having radially disposed spaced apart fins forming passages and a radial turbine having hollow turbine blades interleaved with the fins and through which fluid from the radial compressor/pump flows... | 05/16/2006 |
| 7042111 | System, method and apparatus for a redundant prime mover system The present invention provides a system, method and apparatus for a redundant prime mover system to drive a machine having an engine coupled to the machine, and a motor/generator coupled to the machine and an electrical network connection. The controller operates th... | 05/09/2006 |
| 7036313 | Co-generation turbocharged turbine system A co-generation turbocharged turbine system that utilizes a gas turbine (10) connecting the exhaust to a turbocharger (24) to introduce pressurized air into the inlet of the turbine for improving power and efficiency. A second embodiment places a work ... | 05/02/2006 |
| 7028487 | Coolant recovery type gas turbine An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality ... | 04/18/2006 |
| 7028486 | Coolant recovery type gas turbine An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality ... | 04/18/2006 |
| 7021042 | Geartrain coupling for a turbofan engine Molybdenum disulfide (MoS2) is used as a journal coating for a gearing system. A particular application is the planetary gear system of a geared turbofan engine. Particularly advantageous coatings are deposited via physical vapor deposition (PVD) techniqu... | 04/04/2006 |
| 7007475 | Conical helical of spiral combustor scroll device in gas turbine engine A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift re... | 03/07/2006 |
| 6996992 | Gas collection pipe carrying hot gas A gas collection pipe (1) carrying hot gas establishes the connection between the combustion chambers (9) of a gas turbine plant and the flow channel (13) of the gas turbine. The gas collection pipe (1) has two inlet pipe connections (... | 02/14/2006 |
| 6983604 | Thermodynamic pressure generator A thermodynamic pressure generator having an oscillating valve that allows premixed fuel to enter a combustion chamber in turbulence, until it comes into contact with an annular spoiler, which converts a portion of the fuel into a Karmon vortex ring for delayed igni... | 01/10/2006 |
| 6978621 | Turbo recuperator device A device and method for recuperating a gas turbine engine comprises a compressor being configured to receive a coolant fluid stream, to compress the coolant fluid stream and to discharge the compressed coolant fluid stream to a turbine in fluid communication with th... | 12/27/2005 |
| 6973792 | Method of and apparatus for a multi-stage boundary layer engine and process cell A multi-staged boundary layer engine and process cell, (based on the effect known as adhesion and viscosity) which achieves high thermal efficiencies and high mechanical power output for use in the power generation, geothermal, energy recovery, solar, transportation... | 12/13/2005 |
| 6973771 | Diffuser for terrestrial or aviation gas turbine A diffuser for a gas turbine engine, said diffuser being disposed between a last stage of a turbine and an exhaust casing, and comprising an outer annular wall and an inner annular wall together defining an annular passage for fluid that diverges in the flow directi... | 12/13/2005 |
| 6968672 | Collar for a combustion chamber of a gas turbine engine This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connec... | 11/29/2005 |
| 6948320 | Expansion turbine stage An expansion turbine stage for compressed gases has a housing and a turbine rotor. The housing has flow guide channels for feeding the compressed gas to the turbine rotor. The turbine rotor, which is over-mounted and has centripetal flow through it, is followed by a... | 09/27/2005 |
| 6851264 | Self-aspirating high-area-ratio inter-turbine duct assembly for use in a gas turbine engine In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-... | 02/08/2005 |
| 6834507 | Convoluted seal with enhanced wear capability An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the are-like sections of the aft... | 12/28/2004 |
| 6796130 | Integrated combustor and nozzle for a gas turbine combustion system A gas turbine combustion system and method used for generating electrical power includes a compressor that receives and compresses air. A first stage turbine nozzle is flowise connected to the compressor and receives a portion of the compressed air from the compress... | 09/28/2004 |
| 6792763 | Coated seal article with multiple coatings An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft... | 09/21/2004 |
| 6779964 | Viscous drag impeller components incorporated into pumps, turbines and transmissions The present invention relates generally to systems and methods for facilitating the movement of fluids, transferring mechanical power to fluid mediums, as well as deriving power from moving fluids. The present invention employs an impeller system in a variety of app... | 08/24/2004 |
| 6735957 | Coolant recovery type gas turbine An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality ... | 05/18/2004 |
