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| Number | Title | Issue Date |
| 8177495 | Method and apparatus for turbine interstage seal ring A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a sec... | 05/15/2012 |
| 8172519 | Abradable seals In one embodiment, an abradable seal includes a soft material that may be worn away and a hard material that may provide mechanical strength for the abradable seal. The soft material and the hard material may include different compositions of a base material. ... | 05/08/2012 |
| 8038388 | Abradable component for a gas turbine engine A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. ... | 10/18/2011 |
| 7988411 | Flow machine for a fluid with a radial sealing gap A flow machine for a fluid is presented with a radial sealing gap (9) between stator parts (4) and a rotor (3), wherein at least one wear ring (5) is provided at the sealing gap and is fastened to a stator part (4) via an elastical... | 08/02/2011 |
| 7695244 | Vane for a gas turbine engine A vane for a gas turbine engine includes an aerofoil part and a shroud that forms a sealing part at one end of the aerofoil part. The sealing part defines a cavity and an opening to the cavity. The sealing part may include a pair of opposed side walls extending from... | 04/13/2010 |
| 7425115 | Thermal turbomachine A thermal turbomachine is disclosed having at least one row of rotor blades. At least one first rotor blade has a greater radial length than the others and at the blade tip is equipped with a first abrasive layer. At least one rotor blade which has a shorter radial ... | 09/16/2008 |
| 7390161 | Composite containment case for turbine engines A composite fan casing for a gas turbine engine includes, in an exemplary embodiment, a core having a plurality of core layers of reinforcing fiber bonded together with a thermosetting polymeric resin. Each core layer includes a plurality of braided reinforcing fibe... | 06/24/2008 |
| 7338255 | Turbo-type fluid machine and a stepped seal apparatus to be used therein A turbo-type fluid machine comprises a mouth ring part provided between a shroud of an impeller and a pump casing and having a seal function. The mouth ring part comprises an impeller ring on a side of the shroud of the impeller and a casing ring provided on a side ... | 03/04/2008 |
| 7334983 | Integrated bladed fluid seal Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extendi... | 02/26/2008 |
| 7334982 | Apparatus for scavenging lubricating oil An apparatus for scavenging lubricating oil comprises an integrated slinger/runner rotatable with the turbine engine rotor discourages oil seepage out of an oil sump of a forward bearing for a gas turbine engine during all operating conditions of the gas turbine eng... | 02/26/2008 |
| 7291403 | Thermal barrier coating system A TBC system suitable for protecting the surface of a substrate subjected to a hostile thermal environment. The TBC system comprises a bond coat on the substrate surface, an alumina scale on the bond coat, and a multilayer TBC comprising a thermal-sprayed first cera... | 11/06/2007 |
| 7287956 | Removable abradable seal carriers for sealing between rotary and stationary turbine components The turbine includes a diaphragm having a seal carrier mounted in opposition to seal teeth carried by the rotary component. The seal carrier includes a seal face having a coating of abradable material enabling the rotary component to abrade the material from the sea... | 10/30/2007 |
| 7287957 | Inner shroud for the stator blades of the compressor of a gas turbine An inner shroud (6) for the stator blades (3) of the compressor of a gas turbine is a plastic component and includes certain additives, which may be concentrated in partial areas for specific functionality, and/or pre-manufactured inserts for sealing, ... | 10/30/2007 |
| 7247002 | Lamellate CMC structure with interlock to metallic support structure A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperat... | 07/24/2007 |
| 7241108 | Cantilevered stator stage A cantilevered stator stage for the axial compressor 14 of a gas turbine engine 10 in which the stator tips 26 rub against an abrasive section 24 on the rotor drum 22 during initial running of the engine 10 to abrade the tip... | 07/10/2007 |
| 7223067 | Flow machine with a ceramic abradable The flow machine is furnished with an abradable (10) made of a particle composite material. This so-called composite (1) contains granular core particles (2) of a ceramic material. The surfaces (20) of the granular core particles carry fu... | 05/29/2007 |
| 7189054 | Self-compensating clearance seal for centrifugal pumps A radial seal is provided for installation within a centrifugal pump of the type having an impeller, a pump casing having a suction inlet, a sealing ring groove formed in the pump casing, and means for supplying flushing water to the sealing ring groove. The radial ... | 03/13/2007 |
| 7178808 | Layer system for the rotor/stator seal of a turbomachine A layer system for the rotor/stator seal of a turbomachine, in particular of a gas turbine, is applied to a metallic component and can be run in with respect to a further component which can move relative to the metallic component, which, in order to improve the ser... | 02/20/2007 |
| 7175387 | Seal arrangement for reducing the seal gaps within a rotary flow machine A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots ( | 02/13/2007 |
| 7165931 | Compact molecular-drag vacuum pump A molecular drag vacuum pump configured for pumping a gas stream from an inlet to an outlet, the pump including a high-speed spinning disk or rotor disposed within a housing. A passageway is formed inside the housing adjacent the disk, and gas comes in contact with ... | 01/23/2007 |
| 7153091 | Gas turbine engine A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a pluralit... | 12/26/2006 |
| 7144602 | Process for obtaining a flexible/adaptive thermal barrier The invention proposes a process for obtaining a flexible/adaptive thermal barrier, the thermal barrier comprising a ceramic layer deposited on a substrate covered with a sublayer, the ceramic layer being deposited by thermal spraying using a torch. The ceramic laye... | 12/05/2006 |
| 7125217 | Cellular materials A structural member comprises a main body formed from a cellular material. The structural member may be a casing for a rotary assembly e.g. a fan of a gas turbine engine. The main body may incorporate strengthening ribs and conduits and may have a random or graduate... | 10/24/2006 |
| 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 |
| 7097412 | Turbine engine bearing support A bearing support for a rotor of an aircraft turbine engine which includes a front bearing and a front bearing support and bearing strut for securely attaching the front bearing, to the aircraft turbine engine support structure, wherein the front bearing support and... | 08/29/2006 |
| 7044710 | Gas turbine arrangement A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (... | 05/16/2006 |
| 7037069 | Impeller and wear plate In one aspect, there is provided a wear plate for use in combination with a centrifugal pump and impeller. The wear plate has a wear surface defined by a substantially flat surface, a truncated conic section, and/or a curvilinear solid of revolution formed by revolv... | 05/02/2006 |
| 7029232 | Abradable seals A sealing element for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure comprising a plurality of radially inwardly projecting walls. The walls may be abradable and may define cells for recei... | 04/18/2006 |
| 7025356 | Air-oil seal An air-oil seal having a runner surface comprising at least one component selected from the group consisting of: polyetheretherketone; polyetherimide; polyphenylene sulfide; and polyetherketoneketone. ... | 04/11/2006 |
| 7011490 | Compressor in a multi-stage axial form of construction A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stag... | 03/14/2006 |
| 6984107 | Turbine blade for the impeller of a gas-turbine engine In a turbine blade for a gas-turbine engine impeller, which is rotationally mounted in a housing, the turbine blade has a blade tip, a leading-edge positioned upstream in the direction of flow, and trailing edge positioned downstream, and includes a blade section, w... | 01/10/2006 |
| 6971841 | Cellular materials A structural member comprises a main body formed from a cellular material. The structural member may be a casing for a rotary assembly e.g. a fan of a gas turbine engine. The main body may incorporate strengthening ribs and conduits and may have a random or graduate... | 12/06/2005 |
| 6969231 | Rotary machine sealing assembly A sealing assembly for disposition in a rotary machine is disposed between a rotary component and a stationary component of the rotary machine. The sealing assembly includes at least one sealing strip affixed by caulking to one of the rotary and stationary component... | 11/29/2005 |
| 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 |
| 6887037 | Boat impeller seal assembly A boat impeller seal assembly for preventing leakage of debris into the impeller assembly between the impeller housing and the impeller mount. The boat impeller seal assembly includes an impeller assembly including an impeller housing having an open end and also hav... | 05/03/2005 |
| 6887039 | Stationary blade in gas turbine and gas turbine comprising the same A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direct... | 05/03/2005 |
| 6887036 | Turbine and manufacturing method therefor A tip of rotor blade which rotates is an abradable surface. An inner wall of a shroud as a jacket for the rotor blade is an abrasive surface. A part of an abrasive particle protrudes from the abradable surface. When the tip of the rotor blade which rotates contacts ... | 05/03/2005 |
| 6857847 | Simplified support device for nozzles of a gas turbine stage A simplified support device (110) for nozzles (112) of a gas turbine stage, of the type in which the support device (110) is interposed in a rotor of the gas turbine, between an upstream blading disc (122) and a downstream blading disc ( | 02/22/2005 |
| 6837676 | Gas turbine A sealing air bypass flow path is provided in a gas turbine for supplying sealing air to a sealing air supply flow path by bypassing the flow path between each tangential on board injection (TOBI) nozzles and disk holes. ... | 01/04/2005 |
| 6832890 | Gas turbine engine casing and rotor blade arrangement An arrangement for a gas turbine engine comprises a compressor and its surrounding casing. The casing has a generally cylindrical inner surface, one cylindrical section of the inner casing being provided with a circumferential array of recesses. An axially adjacent ... | 12/21/2004 |
