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| Number | Title | Issue Date |
| 8001792 | Turbine inlet nozzle guide vane mounting structure for radial gas turbine engine Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet... | 08/23/2011 |
| 8001791 | Turbine engine frame having an actuated equilibrating case The turbine engine assembly has a frame and a turbine engine spool. A strut couples the frame to the spool and an actuator couples the strut to the frame. The actuator has a spring. ... | 08/23/2011 |
| 7823392 | Turbomachine combustion chamber arrangement having a collar deflector An arrangement for a turbomachine combustion chamber is disclosed. The arrangement includes a chamber end wall pierced by at least one substantially circular opening, a deflector mounted from the downstream side of the chamber end wall in the opening by an annulus, ... | 11/02/2010 |
| 7793507 | Expansion joint for gas turbines An expansion joint for use between a turbine duct and an exhaust duct. The expansion joint may include a flange attached to the turbine duct and a number of plates attached to the exhaust duct that extend towards the flange. The plates and the flange may include a g... | 09/14/2010 |
| 7770401 | Combustor and component for a combustor A sacrificial liner is provided for an injector access aperture in a combustor casing. The liner has an outer annular surface and an eccentric inner annular surface. The liner serves to protect the combustor outer casing from wear by a series of piston rings mounted... | 08/10/2010 |
| 7661273 | Turbomachine with annular combustion chamber Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the in... | 02/16/2010 |
| 7565807 | Heat shield for a fuel manifold and method The manifold includes supports which slidably engage a heat shield to floatingly suspend it around the manifold. The manifold is part of a heat shield assembly inside a gas turbine engine. The assembly comprises a plurality of radially-extending supports extending f... | 07/28/2009 |
| 7555906 | Mounting system for a flame pipe or liner A mounting system for a liner within a combination chamber of a gas turbine, where the liner is secured at one upstream end to a burner and at an opposite downstream end to a transition duct, the mounting system comprising: a first... | 07/07/2009 |
| 7338259 | High modulus metallic component for high vibratory operation A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, ... | 03/04/2008 |
| 7296415 | Labyrinth seal device for gas turbine engine This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamb... | 11/20/2007 |
| 7287384 | Bearing chamber pressurization system A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing. ... | 10/30/2007 |
| 7258525 | Guide blade fixture in a flow channel of an aircraft gas turbine An arrangement for detachably fixing a guide blade segment that forms part of a transition channel of an aircraft gas turbine comprises high-pressure and low-pressure turbines. The arrangement has a groove-hook-type connection in the front area of the outer platform... | 08/21/2007 |
| 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 |
| 7163206 | Fluid seal A jet pipe assembly containing at least one joint provided with a seal assembly to isolate, substantially, the fluid flowing in the pipe from the fluid external to the pipe. The dynamic member of the seal assembly is provided with both radial and cylindrical sealing... | 01/16/2007 |
| 7152411 | Rabbet mounted combuster A combustor includes an outer wall and an inner liner joined to an inner shell in turn mounted to an inner casing. The casing includes a first rabbet at an end flange in which is mounted a corresponding flange of the inner shell. The inner shell also includes a seco... | 12/26/2006 |
| 7134286 | Gas turbine floating collar arrangement A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a spaced-apart mounting flange and cap, and slidably trapped therebetwe... | 11/14/2006 |
| 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 |
| 7101173 | Plug sealing device that is not welded to the chamber wall The invention provides a combustion chamber comprising a chamber wall disposed radially inside a casing, an igniter plug for igniting the air-fuel mixture, the plug being mounted on said casing and comprising a body with a free end that is disposed in an opening for... | 09/05/2006 |
| 7096668 | Cooling and sealing design for a gas turbine combustion system An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received... | 08/29/2006 |
| 7086219 | Cowl structure for a gas turbine engine A cowl structure (18) for a gas turbine engine (10) comprises an outer skin (26) defining a first path for a load applied to the engine (10). The cowl structure (18) includes an inner skin (24) defining a second path for the... | 08/08/2006 |
| 7080513 | Seal element for sealing a gap and combustion turbine having a seal element The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposi... | 07/25/2006 |
| 7040098 | Provision of sealing for the cabin-air bleed cavity of a jet engine using strip-type seals acting in two directions The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external c... | 05/09/2006 |
| 7037071 | Device for maintaining joints with sealing leaves The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements havi... | 05/02/2006 |
| 7007480 | Multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 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 |
| 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 |
| 6942452 | Grommeted bypass duct penetration A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and the external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an interior periphery ... | 09/13/2005 |
| 6920762 | Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a... | 07/26/2005 |
| 6912838 | Coated crossfire tube assembly A crossfire tube assembly is provided having an increased resistance to wear and oxidation. This increased resistance is provided by the application of coatings to the mating surfaces between the crossfire tube and crossfire tube clip. In the preferred embodiment, a... | 07/05/2005 |
| 6904756 | Transition duct support bracket wear cover A wear cover for use on a gas turbine transition duct support bracket is disclosed. The wear cover, which is manufactured from a single piece of sheet metal, does not require complex manufacturing processes or tools, thereby reducing component cost. The wear cover c... | 06/14/2005 |
| 6892526 | Cowl structure for a gas turbine engine A cowl structure (18) for a gas turbine engine (10) comprises an outer skin (26) defining a first path for a load applied to the engine (10). The cowl structure (18) includes an inner skin (24) defining a second path for the... | 05/17/2005 |
| 6880341 | Low cost combustor floating collar with improved sealing and damping A floating collar assembly for damping vibration and sealing between a combustor and a fuel nozzle of a gas turbine engine. The combustor has a nozzle opening with an outer peripheral abutment surface and the nozzle is integral with an internal fuel manifold that is... | 04/19/2005 |
| 6843061 | Gas turbine with flexible combustion sensor connection A gas turbine engine (40) having an active combustion control system (54) including a sensor element (44) positioned proximate the combustion chamber (46) as part of a sensor assembly (84) including a spring-action bellows (74 | 01/18/2005 |
| 6810670 | Corrugated catalyst support structure for use within a catalytic reactor A catalytic section of a combustor is formed from a spaced tandem array of corrugated panels. The exterior top and bottom surfaces of the panels are coated with a catalyst and the space between panels defines a passage for a fuel-rich/air mixture. The interior of th... | 11/02/2004 |
| 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 |
| 6786052 | Insulation system for a turbine and method Turbine insulation is disclosed, and comprises blankets, ribs and coupling members. The blankets define, with the turbine, an annular channel in receipt of the turbine vertical joint and a pair of longitudinal channels each in receipt of a respective turbine horizon... | 09/07/2004 |
| 6766639 | Acoustic-structural LPC splitter An acoustic-structural LPC splitter assembly which comprises a structural acoustic splitter through which are arranged a plurality of bleed exhaust ports, the acoustic splitter having a first and second end, an inner and outer surface, a front joint for securing the... | 07/27/2004 |
| 6705088 | Advanced crossfire tube cooling scheme for gas turbine combustors A crossfire tube assembly with telescoping inner and outer crossfire tubes with an enhanced cooling mechanism for connecting adjacent combustors in a gas turbine is disclosed. The enhanced cooling configuration includes a plurality of channels formed in the telescop... | 03/16/2004 |
| 6679045 | Flexibly coupled dual shell bearing housing A bearing housing includes inner and outer shells through which a rotor shaft may extend. A service tube is fixedly joined to the inner shell and extends through a service aperture in the outer shell. A flexible coupling sealingly joins the service tube t... | 01/20/2004 |
| 6662568 | Hollow structure with flange The present invention provides a hollow structure with at least one flange which can eliminate the possibility of creating crackings due to the thermal fatigue, thereby improving the durability thereof. A hollow structure with an flange according to the p... | 12/16/2003 |
