Class / Patent application number | Description | Number of patent applications / Date published |
415171100 | Dynamically created seal | 17 |
20090092484 | Vacuum pump - A vacuum pump includes a gas inlet, a quick-rotatable rotor connectable with a flange of a multi-chamber vacuum installation which flange has a plurality of suction openings separated by separation walls, and a gas path separating structure which is located in the gas inlet of the pump, dividing the gas inlet in suction regions, and which seals, together with the separation walls, chambers of the multi-chamber vacuum installation. | 04-09-2009 |
20100098530 | COMPRESSOR FOR A GAS TURBINE - A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement ( | 04-22-2010 |
20100254805 | GAS TURBINE INNER FLOWPATH COVERPIECE - A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body. | 10-07-2010 |
20110081236 | STATIC SEAL - The static seal ( | 04-07-2011 |
20110085892 | VORTEX CHAMBERS FOR CLEARANCE FLOW CONTROL - An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area. | 04-14-2011 |
20110135453 | LEAF SEAL - A leaf seal | 06-09-2011 |
20120171022 | SYSTEMS, METHODS, AND APPARATUS FOR A TURBINE INTERSTAGE RIM SEAL - Certain embodiments of the invention may include systems, methods, and apparatus for providing a turbine interstage rim seal. According to an example embodiment of the invention, a method is provided for sealing a turbine rotor-bucket interface. The method can include linking a first portion of one or more rim seal segments with one or more flow path seal segments. The method includes rotating the one or more rim seal segments, upon application of centrifugal force, to displace a second portion of the one or more rim seal segments; and sealing at least a portion of a gap between a rotor and a bucket associated with a turbine with at least one or more rotated rim seal segments. | 07-05-2012 |
20120294707 | STEAM SEAL SYSTEM - A steam seal system is disclosed. In one embodiment, the steam seal system includes: a low pressure steam turbine positioned on a shaft; a pair of end packings surrounding the shaft, each of the pair of end packings located proximate an axial end of the low pressure steam turbine along the shaft; and an pair of extraction conduits fluidly connected to the low pressure steam turbine and the shaft, the pair of extraction conduits connected to the shaft at a location axially outward of the pair of end packings and the low pressure steam turbine. | 11-22-2012 |
20130017069 | TURBINE, A TURBINE SEAL STRUCTURE AND A PROCESS OF SERVICING A TURBINEAANM GOLLER; George AlbertAACI GreenvilleAAST SCAACO USAAGP GOLLER; George Albert Greenville SC USAANM CAVANAUGH; Dennis WilliamAACI SimpsonvilleAAST SCAACO USAAGP CAVANAUGH; Dennis William Simpsonville SC USAANM LAYLOCK; MatthewAACI GreenvilleAAST SCAACO USAAGP LAYLOCK; Matthew Greenville SC US - Disclosed is a turbine, a turbine seal structure, and a process of servicing a turbine. The turbine includes the seal structure. The seal structure is mechanically secured within the hot gas path of the turbine. The process of servicing includes positioning the seal structure within the hot gas path of the turbine and mechanically securing the seal structure within the turbine. | 01-17-2013 |
20140003917 | HYDRODYNAMIC SLIDING BEARING, IN PARTICULAR OF A MAGNETIC COUPLING PUMP | 01-02-2014 |
20140112765 | FLUIDIC ACTUATOR - A fluidic actuator comprising: a fluid nozzle for delivering fluid and a tube having an open end and a closed end, the open end spaced from the fluid nozzle. Also a pair of electrodes mounted in the tube and spaced apart to create a spark gap therebetween. A voltage source is arranged to supply a voltage across the pair of electrodes wherein the voltage causes plasma formation in the spark gap thereby shortening the effective length of the tube. | 04-24-2014 |
20150098806 | SYSTEMS AND METHODS FOR DYNAMICALLY SEALING A TURBINE ENGINE - A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating. | 04-09-2015 |
20150110609 | Hybrid Cycle Rotary Engine - An internal combustion engine includes in one aspect a source of a pressurized working medium and an expander. The expander has a housing and a piston, movably mounted within and with respect to the housing, to perform one of rotation and reciprocation, each complete rotation or reciprocation defining at least a part of a cycle of the engine. The expander also includes a septum, mounted within the housing and movable with respect to the housing and the piston so as to define in conjunction therewith, over first and second angular ranges of the cycle, a working chamber that is isolated from an intake port and an exhaust port. Combustion occurs at least over the first angular range of the cycle to provide heat to the working medium and so as to increase its pressure. The working chamber over a second angular range of the cycle expands in volume while the piston receives, from the working medium as a result of its increased pressure, a force relative to the housing that causes motion of the piston relative to the housing. | 04-23-2015 |
20150132116 | METHODS AND SYSTEMS FOR SEALING A ROTARY MACHINE USING A SEGMENTED SEAL RING - A hydrodynamic face seal ring for use in a rotary machine includes a support ring having at least two support ring segments and a radially-extending, first face. The support ring is configured to releasably couple to an inner surface of an outer casing of the rotary machine. The face seal ring also includes a sealing ring substantially concentric with the support ring. The sealing ring includes at least two sealing ring segments and a radially-extending, second face. The sealing ring is releasably coupled to the support ring such that the first face is mated against the second face. | 05-14-2015 |
20160053623 | CONTACTLESS SEALS FOR GAS TURBINE ENGINES - A seal for a gas turbine engine includes a first seal structure and a second seal structure. The first seal structure is separated from the second seal structure by a gap. The first seal structure includes an injector extending into the gap with an outlet that is in fluid communication with a fluid source. Fluid issuing from the outlet and against the second seal structure magnifies a vortex formed within the gap by fluid traversing the gap. | 02-25-2016 |
20160177963 | CENTRIFUGAL PUMP, IN PARTICULAR FOR SUPPLYING POWER TO ROCKET ENGINES | 06-23-2016 |
20180023534 | HYDRAULIC TURBINE | 01-25-2018 |