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| Number | Title | Issue Date |
| 8152454 | Stator vane for a gas turbine engine A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and i... | 04/10/2012 |
| 8033784 | Compressor rotor A compressor has a rotor (13), which rotor (13) has a number of rows of rotor blades (14, 14′) which are at a distance from one another, one behind the other in the axial direction, with a number of thermal barrier segments (10), which ... | 10/11/2011 |
| 7824152 | Multivane segment mounting arrangement for a gas turbine A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround i... | 11/02/2010 |
| 7798769 | Flexible, high-temperature ceramic seal element A ceramic seal element (200) for use in a turbo-machine comprises a first, rigid portion (210) comprising ceramic fibers (212) bound within a ceramic matrix binder (214), a second, flexible portion (220) comprising ceramic fibers (... | 09/21/2010 |
| 7798768 | Turbine vane ID support A turbine vane ID support system usable to support the ID of a turbine vane and including a transition seal system and a turbine vane ID forward rail seal system. The transition seal system may seal the turbine vane ID support body to a transition, and the turbine v... | 09/21/2010 |
| 7771159 | High temperature seals and high temperature sealing systems A high temperature seal that may include an interior region comprising a material that swells when exposed to a high temperature environment and at least one projection that is able to be inserted into a slot, and a coating that substantially prevents swelling to co... | 08/10/2010 |
| 7625174 | Methods and apparatus for assembling gas turbine engine stator assemblies A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and se... | 12/01/2009 |
| 7625175 | Link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, each tube including a bell... | 12/01/2009 |
| 7594792 | Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing device The gastight sealing device associated with a functional clearance existing between two sectors of a turbomachine includes an annular plate wound up on itself over at least one turn, covering functional clearance. ... | 09/29/2009 |
| 7575415 | Methods and apparatus for assembling turbine engines A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and se... | 08/18/2009 |
| 7540707 | Link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, one end of each tube being... | 06/02/2009 |
| 7452182 | Multi-piece turbine vane assembly Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as ... | 11/18/2008 |
| 7452183 | Thermally compliant turbine shroud assembly A shroud assembly is provided for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes at least one arcuate shroud segment adapted to surround a row of ro... | 11/18/2008 |
| 7448846 | Thermally compliant turbine shroud mounting A shroud segment is adapted to surround a row of rotating turbine blades in a gas turbine engine. The shroud segment includes: an arcuate, axially extending first mounting flange having a first radius of curvature, and an arcuate, axially extending first overhang ha... | 11/11/2008 |
| 7445426 | Guide vane outer shroud bias arrangement A compressor includes a stator having a plurality of vane sectors each with an outer shroud having a forward and a rearward guide vane extending there form, the vane sector being mounted in an annular slot of the casing, the guide vanes forming a gap between the tip... | 11/04/2008 |
| 7442004 | Thermally compliant C-clip A C-clip for a gas turbine engine includes an arcuate outer arm having a first radius of curvature; an arcuate, inner arm having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate extending flange connectin... | 10/28/2008 |
| 7438520 | Thermally compliant turbine shroud mounting assembly A shroud assembly is provided for a gas turbine engine that has a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes: at least one arcuate shroud segment adapted to surround a row of... | 10/21/2008 |
| 7434670 | Support apparatus and method for ceramic matrix composite turbine bucket shroud A shroud support method and apparatus for a ceramic component of a gas turbine having: an outer shroud block having a coupling to a casing of the gas turbine; a spring mass damper attached to the outer shroud block and including a spring biased piston extending thro... | 10/14/2008 |
| 7367567 | Low leakage finger seal A seal for an exhaust duct includes a metal mesh member sandwiched between an outer plate and an inner plate. The seal includes a plurality of flexible members defined by a plurality of slots in both the inner and outer plates. The flexible members provide for expan... | 05/06/2008 |
| 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 |
| 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 |
| 7316402 | Segmented component seal A seal for restricting leakage of a fluid from a first chamber, through a gap between two components, to a second chamber is provided. A slot is formed in each of the two components. The slots face one another and are open to the gap. Each slot contains a longitudin... | 01/08/2008 |
| 7303371 | Gas turbine having a sealing element between the vane ring and a vane carrier of the turbine The invention relates to a gas turbine. The aim of the invention is to provide an axial sealing between a vane ring and a moving blade ring, which has an excellent sealing effect, is easy to install and inexpensive to produce. For this purpose, a sealing element is ... | 12/04/2007 |
| 7303372 | Methods and apparatus for cooling combustion turbine engine components A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each includ... | 12/04/2007 |
| 7300246 | Integrated turbine vane support A unitary component for retaining a vane ring in a gas turbine engine comprises a retaining plate portion to restrain axial vane movement, a retaining ring portion to restrain circumferential vane movement, and a baffle portion to split a cooling air flow between th... | 11/27/2007 |
| 7293957 | 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 its resis... | 11/13/2007 |
| 7290769 | Sealing device with a brush gasket and flexible washer for a high-pressure turbine of a turbomachine A sealing device for sealing between two static portions of a turbomachine includes a brush gasket formed by a plurality of resilient bristles which are, at least in part, held in a housing. Each bristle has a main portion and a secondary portion interconnected by a... | 11/06/2007 |
| 7291946 | Damper for stator assembly A damper for a stator assembly, the stator assembly comprising a stator segment and a seal mounted to the stator segment. The damper locates between the stator segment and the seal, and comprises: a medial section; and opposed arms extending from the medial section.... | 11/06/2007 |
| 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 |
| 7238003 | Vane attachment arrangement A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing. ... | 07/03/2007 |
| 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 |
| 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 |
| 7220099 | Sealing arrangement for a rotor of a turbo machine A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, ... | 05/22/2007 |
| 7207771 | Turbine shroud segment seal A ring seal for sealing an annular gap defined between opposed surfaces of concentric inner and outer annular engine parts in a gas turbine engine. The ring seal being wholly disposed within the annular gap and having a wave pattern with alternating peaks. The ring ... | 04/24/2007 |
| 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 |
| 7195452 | Compliant mounting system for turbine shrouds The mounting of low expansion full ring shrouds in a turbine engine requires radial compliance to limit the stresses experienced by the shroud due to thermal growth differences between the shroud and its support. A method provides radial compliance with no looseness... | 03/27/2007 |
| 7185498 | Modular gas turbine Method and arrangement for providing a gas turbine (1) having a duct (11) for carrying gas from a gas turbine inlet (9) to a gas turbine outlet (10) and an outer housing (19, 20, 21) arranged radially outside a wall structure (1... | 03/06/2007 |
| 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 |
| 7147429 | Turbine assembly and turbine shroud therefor A turbine assembly includes a shroud for being mounted around a last stage of the low pressure turbine rotor. The shroud includes an arcuate body having spaced-apart forward and aft ends and spaced-apart circumferential ends. Attachments are provided for securing th... | 12/12/2006 |
