Including Additional Means Causing Or Controlling Fluid Flow For Heat Exchanging, Lubricating Or Sealing Patents (Class 415/175)
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Publication number: 20150000298Abstract: Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent to the rotor. A coolant line extends at least partially through the stator to transfer heat out of an air flow within a compressor section of the gas turbine.Type: ApplicationFiled: December 20, 2013Publication date: January 1, 2015Applicant: ADVANCED GREEN TECHNOLOGIES, LLCInventor: Roy Edward McAlister
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Patent number: 8920109Abstract: A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.Type: GrantFiled: March 12, 2013Date of Patent: December 30, 2014Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Brian H. Terpos, Dustan M. Simko
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Publication number: 20140377058Abstract: A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.Type: ApplicationFiled: December 12, 2012Publication date: December 25, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Fathi Ahmad, Nihal Kurt, Mario Nitsche, Marco Schuler, Andreas Varnholt
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Publication number: 20140369818Abstract: A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar.Type: ApplicationFiled: September 2, 2014Publication date: December 18, 2014Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
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Publication number: 20140356146Abstract: A vacuum pump includes a rotor and a rotary bearing, which is to be supplied with an operating medium, for the rotatable support of the rotor, wherein the rotor has a conveying section, in particular a conical conveying section, for supplying the operating medium to the rotary agent. A conveying pump is provided for conveying the operating medium and/or an operating medium store is provided having an absorbent storage means for the operating medium. Further, at least one wick is provided which is in contact with the conveying section to transfer the operating medium provided from the conveying pump and/or from the absorbent storage means to the conveying section in a desired quantity.Type: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: Pfeiffer Vacuum GmbHInventors: Mirko Mekota, Peter Vorwerk, Bernd Hofmann, Johannes Schnarr
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Patent number: 8899909Abstract: The present application provides a steam turbine system. The steam turbine system may include a high pressure section, an intermediate pressure section, a shaft packing location positioned between the high pressure section and the intermediate pressure section, a source of steam, and a cooling system. The cooling system delivers a cooling steam extraction from the source of steam to the shaft packing location so as to cool the high pressure section and the intermediate pressure section.Type: GrantFiled: June 27, 2011Date of Patent: December 2, 2014Assignee: General Electric CompanyInventors: Vishwas Kumar Pandey, Debabrata Mukhopadhyay, Manikandan Srinivasan, Santhosh Donkada
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Publication number: 20140348636Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit.Type: ApplicationFiled: December 21, 2012Publication date: November 27, 2014Inventors: Jared Peter Buhler, Marshall Scott Allen, Daniel Edward Demers, Robert Francis Manning
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Patent number: 8894363Abstract: A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.Type: GrantFiled: February 9, 2011Date of Patent: November 25, 2014Assignees: Siemens Energy, Inc., Mikro Systems, Inc.Inventors: Ching-Pang Lee, Humberto A. Zuniga, Jay A. Morrison, Brede J. Kolsrud, John J. Marra
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Patent number: 8894359Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.Type: GrantFiled: December 8, 2011Date of Patent: November 25, 2014Assignee: Siemens AktiengesellschaftInventors: Mrinal Munshi, John Finneran, Ching-Pang Lee, Yevgeniy Shteyman, Daryl Graber, Matthew R. Porter, Jonathan M. Leagon
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Publication number: 20140341723Abstract: A guide tube assembly in one embodiment includes a guide tube and a collection impingement feature. The guide tube includes an inlet and at least one first impingement opening. The inlet is configured to direct a cooling air flow along the length of the tube in an inlet direction. The at least one impingement feature is configured to direct at least a portion of the cooling air received via the inlet along a first impingement direction. The collection impingement feature receives the at least a portion of the cooling airflow directed in the first impingement direction, collects particulate matter from the cooling airflow upon impingement of the cooling airflow with the collection impingement feature, and directs the at least a portion of the cooling air flow in a second impingement direction toward a surface of the turbine component to be cooled by the cooling air flow.Type: ApplicationFiled: March 15, 2013Publication date: November 20, 2014Applicant: General Electric CompanyInventor: General Electric Company
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Publication number: 20140341724Abstract: A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core.Type: ApplicationFiled: May 14, 2013Publication date: November 20, 2014Applicant: General Electric CompanyInventors: David Wayne Weber, Dustin Michael Earnhardt, Michelle Jessica Rogers
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Publication number: 20140341707Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.Type: ApplicationFiled: May 12, 2014Publication date: November 20, 2014Applicant: ROLLS-ROYCE PLCInventors: Simon Lloyd JONES, Mark John SIMMS
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Publication number: 20140334921Abstract: A pump for a water cooler is positioned inside or outside an electronic device having heating parts in order to cool heat generated by the heating parts via a circulating refrigerant.Type: ApplicationFiled: August 9, 2013Publication date: November 13, 2014Applicant: ZALMAN TECH CO., LTD.Inventors: Sang Woong PARK, Hak Bong LEE, Hyun Woo LEE
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Patent number: 8882454Abstract: A ram air fan bearing housing for a ram air fan assembly includes a bearing section, a disk section, and radial support ribs. The disk section is at one end of the bearing section for connecting the bearing section to the ram air fan assembly. The disk section includes an outer ring with a circumferential support rib; and a disk wall connecting the outer ring to the bearing section. The disk wall includes arcuate cooling slots defined by edges, including an arcuate edge having an arc center at an axis of the bearing housing and positioned adjacent to and radially inward from the circumferential support rib. The radial support ribs extend axially along most of the length of the bearing section and extend radially along the disk wall to the circumferential support rib. The radial support ribs and the cooling slots alternate about the axis of the bearing housing.Type: GrantFiled: October 24, 2011Date of Patent: November 11, 2014Assignee: Hamilton Sundstrand CorporationInventors: Eric Chrabascz, Brent J. Merritt
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Publication number: 20140321980Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.Type: ApplicationFiled: April 29, 2013Publication date: October 30, 2014Inventors: Ching-Pang Lee, Ralph W. Matthews, Gm Salam Azad, Manjit Shivanand
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Publication number: 20140321967Abstract: The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat system in communication with the compressor discharge manifold via an inlet bleed heat line, and an auxiliary compressor in communication with the compressor discharge manifold via the inlet bleed heat line.Type: ApplicationFiled: April 30, 2013Publication date: October 30, 2014Applicant: General Electric CompanyInventors: Jianmin Zhang, Tailai Hu, Bradly Aaron Kippel
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Publication number: 20140321961Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.Type: ApplicationFiled: May 31, 2012Publication date: October 30, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey S. Beattie, Scott D. Lewis, Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Jeffrey Michael Jacques, Brandon M. Rapp
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Publication number: 20140321996Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.Type: ApplicationFiled: January 8, 2014Publication date: October 30, 2014Applicant: SNECMAInventors: Serge Louis Antunes, Arnaud Bessy
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Publication number: 20140321994Abstract: A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.Type: ApplicationFiled: March 29, 2013Publication date: October 30, 2014Applicant: General Electric CompanyInventor: General Electric Company
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Publication number: 20140321995Abstract: A ram air fan inlet shroud for a ram air fan assembly is provided. The ram air fan inlet shroud includes a shroud portion extending outwardly from a conical portion. The conical portion provides a transition between a central portion and an inner ram air fan hub interface portion. The conical portion includes a plurality of inner cooling slots having a slot arc length and spaced apart by a slot spacing angle. A ratio of the slot spacing angle to the slot arc length is between about 1.24 and 1.4. The ram air fan inlet shroud also includes a recessed portion located between the inner ram air fan hub interface portion and an outer ram air fan hub interface portion. The recessed portion includes a plurality of outer cooling holes.Type: ApplicationFiled: April 26, 2013Publication date: October 30, 2014Applicant: Hamilton Sundstrand CorporationInventors: Craig M. Beers, Darryl A. Colson, Clarence J. Wytas
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Patent number: 8864448Abstract: A ram air turbine system for generating electrical power in an aircraft when the system is exposed to an airstream exterior of the aircraft. The ram air turbine system includes a turbine, a housing defining an interior, a gearbox having a speed-increasing gear train, and a generator.Type: GrantFiled: September 21, 2011Date of Patent: October 21, 2014Assignee: General Electric CompanyInventors: Dinesh Nath Taneja, John Andrew Layer
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Patent number: 8858163Abstract: A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone.Type: GrantFiled: July 6, 2011Date of Patent: October 14, 2014Assignee: Rolls-Royce PLCInventor: Zahid M. Hussain
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Patent number: 8858168Abstract: A method for assembling a ventilation system is provided. The method includes providing a ventilation hood that includes a cover portion and a discharge portion extending from the cover portion. The cover portion includes a first aperture, an opposite second aperture, and a cavity therein, wherein an interior of the discharge portion is in flow communication with the cover portion cavity. The method also includes coupling a rotatable member at least partially within the ventilation hood, such that the rotatable member extends at least partially through at least one of the first and second apertures, and such that rotation of the rotatable member induces a windage-driven flow of fluid between a portion of the rotatable member and at least one of the first and second apertures.Type: GrantFiled: March 3, 2008Date of Patent: October 14, 2014Assignee: General Electric CompanyInventors: Richard Lynn Loud, Carlos Andres Rodriguez, Timothy Andrew Melsert
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Publication number: 20140301834Abstract: A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system. The air may then be passed to a heating air supply system via an air movement device. The heating air supply system may be in communication with a turbine cylinder cavity of the turbine engine positioned radially outward from at least one turbine assembly. The heated air may be passed into the turbine cylinder cavity to reduce the cooling rate of the turbine vane carriers after shutdown and before a warm restart to limit tip rubbing.Type: ApplicationFiled: April 3, 2013Publication date: October 9, 2014Inventors: Barton M. Pepperman, Yan Yin, Jose L. Rodriguez, Evan C. Landrum, Jiping Zhang
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Publication number: 20140301827Abstract: Exemplary embodiments of the present disclosure are directed to a 2-stage supercharging unit having a housing unit which integrates within it a high-pressure charger and a low-pressure charger. The rotor axes of the two chargers are vertical with respect to the housing unit, which can be screwed directly via the housing base to the side of an internal combustion engine. As a result, increased flexibility is made possible with regard to the connection of the supercharging unit to the cooler and to the internal combustion engine, whereby the structural volume of the supercharging assembly can be additionally reduced.Type: ApplicationFiled: April 9, 2014Publication date: October 9, 2014Applicant: ABB TURBO SYSTEMS AGInventors: Christoph MATHEY, Joel Schlienger, Olaf Baudisch, Patrick Aberle
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Publication number: 20140294560Abstract: Embodiments of the present disclosure include a gas turbine shroud assembly. The shroud assembly may include a shroud structure that defines a first cooling chamber and a second cooling chamber. The shroud assembly may also include a first impingement plate disposed within the first cooling chamber and a second impingement plate disposed within the second cooling chamber. Further, the shroud assembly may include one or more cooling channels formed within the shroud structure. The cooling channels may be configured to connect the first cooling chamber with the second cooling chamber. The shroud assembly may also include a flow of cooling air in communication with the first cooling chamber. In this manner, the flow of cooling air may flow from the first cooling chamber to the second cooling chamber by way of the one or more cooling channels.Type: ApplicationFiled: April 2, 2013Publication date: October 2, 2014Applicant: General Electric CompanyInventor: Niraj K. Mishra
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Patent number: 8845273Abstract: A fluid transfer arrangement comprising a duct having a first end and a second end, a pulse generation mechanism located at the first end of the duct to direct fluid pulses towards the second end of the duct in use, and a baffle located at the second end of the duct that defines an aperture having sharp edges. The sharp edges generate ring vortex fluid flow from the aperture in use. Applications include impingement heating and cooling.Type: GrantFiled: May 17, 2011Date of Patent: September 30, 2014Assignee: Rolls-Royce PLCInventors: Zahid M. Hussain, Christopher T. J. Sheaf, Brian A. Handley
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Publication number: 20140286762Abstract: A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area.Type: ApplicationFiled: March 20, 2013Publication date: September 25, 2014Applicant: General Electric CompanyInventors: Onika Misasha Kerber, Gary Michael Itzel, James William Vehr, Evan Andrew Sewall
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Publication number: 20140271115Abstract: A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane.Type: ApplicationFiled: December 4, 2013Publication date: September 18, 2014Inventors: Robert T. Duge, Andrew J. Eifert
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Publication number: 20140271151Abstract: Lubrication system for a device (13) located between an internal shaft (12a) and an external shaft (12b) of an aircraft turbine (10), that are free to rotate, concentric and arranged at least partially one (12b) around the other (12b), comprising an annular element (30) provided with an external groove (31) and being configured so that it can be mounted integral with the external shaft (12b), the external groove (31) being designed to be supplied with lubricant from a fixed part of the turbine (10), a grooved element (25) configured to be mounted integral with the internal shaft (12a), the grooved element (25) having relief (70) designed to direct a lubricant in contact with its external surface along a longitudinal direction (A) when the internal shaft (12a) is rotating, the external groove (31) being in fluid communication with an external surface (70) of the grooved element (25) through at least two conduits (22) arranged through the external shaft (12b).Type: ApplicationFiled: March 13, 2014Publication date: September 18, 2014Applicant: SNECMAInventors: Olivier BELMONTE, Serge Louis Antunes, Mathieu Perrier
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Patent number: 8834108Abstract: A running-gap control system of an aircraft gas turbine with a core engine including a turbine whose blade rows have a running gap 13 to the turbine casing 12, with the turbine casing 12 being surrounded by a core-engine ventilation compartment 15 enclosed by a fairing 2 of the core engine, with the fairing 2 forming an inner wall of a bypass duct 1. Air from the bypass duct 1 can be introduced via at least one inlet nozzle 5 into a cooling-air distributor 7 by a control system 6, 10, 11 and the air is subsequently returned to the bypass flow 3.Type: GrantFiled: February 24, 2010Date of Patent: September 16, 2014Assignee: Rolls-Royce Deutschland Ltd & Co KGInventors: Dimitrie Negulescu, Stephan Lisiewicz
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Publication number: 20140255171Abstract: A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a pressure restricting valve mounted downstream of displacement pump and in parallel to the equipment, such that oil flows through the equipment when the same is active, and through the valve when the equipment is inactive.Type: ApplicationFiled: March 6, 2014Publication date: September 11, 2014Inventors: Antoine Laigle, Jean-Louis Muller
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Publication number: 20140248166Abstract: A vacuum pump has at least one side passage pump stage which comprises a side passage bounded by at least one stator element and having a coolant circuit for cooling the vacuum pump with a coolant, wherein the coolant circuit has at least one coolant passage for the side passage pump stage which is bounded at least regionally by the stator element.Type: ApplicationFiled: February 27, 2014Publication date: September 4, 2014Applicant: Pfeiffer Vacuum GmbHInventors: Aleksandr Shirinov, Wolfgang Soehngen, Torsten Gogol, Sebastian Oberbeck
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Publication number: 20140238336Abstract: A power system, comprising a turbocharger, an oil sump, a supply passage, a return passage, and a turbocharger bypass passage. The supply passage is positioned fluidly between the turbocharger and the oil sump and is configured to supply oil to the turbocharger. The return passage is positioned fluidly between the turbocharger and the oil sump and is configured to return oil from the turbocharger to the oil sump. The turbocharger bypass passage is positioned fluidly between the supply passage and the return passage. The turbocharger bypass passage comprises a valve that is configured to be in a closed positioned when the turbocharger is in a normal operating mode, and in an open position when the turbocharger is in a failure mode.Type: ApplicationFiled: February 27, 2013Publication date: August 28, 2014Applicant: DEERE & COMPANYInventor: ROBERT J. MCMULLEN
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Publication number: 20140241853Abstract: A vacuum pump, in particular to a turbomolecular pump, has a pump inlet, a pump outlet and a pump space for a gas to be pumped arranged between the pump inlet and the pump outlet, and at least one cooling gas inlet for a cooling gas for cooling the vacuum pump, the pump further having one or more hollow regions for the cooling gas connected in a gas conducting manner to the cooling gas inlet and arranged outside the pump space, wherein the or each hollow region is bounded by at least one component of the vacuum pump to be cooled.Type: ApplicationFiled: February 27, 2014Publication date: August 28, 2014Applicant: Pfeiffer Vacuum GmbHInventor: Michael SCHILL
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Publication number: 20140230452Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.Type: ApplicationFiled: May 1, 2014Publication date: August 21, 2014Applicant: United Technologies CorporationInventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
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Publication number: 20140219788Abstract: The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity, and at least a first impingement device arrangeable within the cavity. The at least first impingement device is self-locking, resilient and preloadable and has at least one locking element to lock the at least first impingement device in place in the cavity via a force fit between the at least one locking element and the inner wall of the cavity wherein the locking element of the at least first impingement device is embodied as a protrusion extending in an assembled state of the at least first impingement device in the cavity basically perpendicular to a surface of a side wall of the at least first impingement device in a direction towards the inner wall.Type: ApplicationFiled: September 3, 2012Publication date: August 7, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventor: Ulf Nilsson
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Patent number: 8789369Abstract: A turbocharger of a supercharging apparatus includes a turbine impeller, which is rotatable by exhaust gas discharged from an internal combustion engine of a vehicle. An electric heater is placed in an exhaust passage, which extends from an exhaust outlet of the internal combustion engine to the turbine impeller. The electric heater generates a heat when the electric heater is energized.Type: GrantFiled: July 11, 2012Date of Patent: July 29, 2014Assignee: Denso CorporationInventor: Osamu Sato
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Publication number: 20140205427Abstract: A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction.Type: ApplicationFiled: December 11, 2013Publication date: July 24, 2014Inventors: Hélène Mazet, Morgan Balland, Jean-Yves Picart
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Publication number: 20140205446Abstract: The invention relates to an oil cooling system of a turbine engine installed in an aircraft comprising a circuit suitable for circulating the oil between the engine and at least one external heat exchanger placing the oil in thermal communication with a part of the lip of the nacelle, wherein it also comprises at least one air/oil heat exchanger placing the oil in thermal communication with the air circulating in the cold zone of the turbine engine, equipped with a device suitable for varying its oil cooling capacity, and with a control means for said cooling capacity variation device.Type: ApplicationFiled: January 22, 2014Publication date: July 24, 2014Applicant: SNECMAInventors: Emmanuel PATSOURIS, Lambert Demoulin
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Patent number: 8784047Abstract: A heat exchanger for a gas turbine engine includes first and second opposing sides enclosing a cavity. A first set of fins is supported on the first side and arranged outside the cavity. The fins have leading and trailing edges respectively including first and second heights. The first height is less than the second height. In one application, the heat exchanger is arranged in a gas turbine engine. A core is supported relative to a fan case. The core includes a core nacelle and a fan case. A fan duct is provided between the core nacelle and the fan case. A heat exchanger includes fins arranged in a fan duct. The fins are oriented such that the shorter leading edge faces into the airflow.Type: GrantFiled: November 4, 2010Date of Patent: July 22, 2014Assignee: Hamilton Sundstrand CorporationInventor: James S. Elder
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Patent number: 8784061Abstract: Method and system are provided for controlling a thermal differential within a turbine rotor for use with a turbine system. A thermal barrier coating is applied to a surface of the turbine rotor. The surface is proximate to a wheel rim of the turbine rotor.Type: GrantFiled: January 31, 2011Date of Patent: July 22, 2014Assignee: General Electric CompanyInventors: Narendra Are, Roger Clayton Walker, Matthew Ryan Ferslew, Matthew Paul Forcier
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Patent number: 8777559Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.Type: GrantFiled: August 23, 2010Date of Patent: July 15, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Hidemichi Koyabu, Satoshi Hada
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Publication number: 20140193246Abstract: A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.Type: ApplicationFiled: March 11, 2014Publication date: July 10, 2014Applicant: United Technologies CorporationInventors: Glenn Levasseur, Edward F. Pietraszkiewicz
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Publication number: 20140186164Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.Type: ApplicationFiled: December 28, 2012Publication date: July 3, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: James M. Koonankeil, Edward F. Pietraszkiewicz, Karl A. Schachtner, Kevin J. Klinefelter, Markus W. Fritch, Jason Daley
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Patent number: 8747060Abstract: A system to cool the air inside a nacelle of a wind turbine. The system has an upper cooling circuit, with a reservoir disposed below the nacelle. The reservoir has at least one pair of annular chambers and a lid that freely rotates about its axis and about the nacelle yaw axis. Coolant flows from a first annular chamber to a second annular chamber through a heat exchanger in the nacelle, thereby carrying heat from the nacelle to the second annular chamber. The system also has a lower cooling circuit, having a coil that connects the first annular chamber to the second annular chamber and being exposed to the outside of the wind turbine. Coolant flows from the second annular chamber to the first annular chamber through the coil, thereby dissipating the heat to ambient air.Type: GrantFiled: September 21, 2011Date of Patent: June 10, 2014Assignee: Gamesa Innovation & Technology, S.L.Inventor: Peri Sabhapathy
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Patent number: 8740555Abstract: A turbomachine comprising a rotor, an inner housing, and an outer housing is proposed. The inner housing is arranged around the rotor and the outer housing is arranged around the inner housing, An encapsulation is arranged around the inner housing. An annular channel and holes into a chamber are provided between the encapsulation and the inner-housing outer surface, and steam flows out again via holes which are situated in the encapsulation.Type: GrantFiled: February 27, 2009Date of Patent: June 3, 2014Assignee: Siemens AktiengesellschaftInventor: Andreas Ulma
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Patent number: 8740549Abstract: A lubrication system for turbocharger(s) ensures continuous lubrication of bearings and shaft of the turbocharger with lubricant retention during start and shut down of turbocharger-associated systems thereby enhancing the performance and turbocharger life. A shaft and bearings are lubricated by introducing pressurized lubricating oil through an oil inlet passage in the bearing housing and after lubricating, the lubricant returns to the engine oil sump located below the turbocharger through the oil outlet passage. A valve in the oil inlet pipe line permits lubricant flow to the bearings during engine running, and when the engine stops and oil pressure falls below the valve opening pressure, the valve shuts and traps the lubricant in oil inlet pipe that is above the valve. The oil outlet pipe retains sufficient lubricant in the bearing housing which lubricates the shaft and bearings post engine shutdown.Type: GrantFiled: July 18, 2012Date of Patent: June 3, 2014Assignee: Mahindra & Mahindra LtdInventors: Kishor Raut Shashank, Sharad Shete Manoj
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Publication number: 20140147249Abstract: An assembly for a gas turbine engine includes a rotor formed by a drum and a hub. The drum has a generally conically shaped inner surface that defines a flow path along a first cavity. The hub is connected to the drum and has a conically shaped inner surface that defines a flow path along a second cavity.Type: ApplicationFiled: October 24, 2012Publication date: May 29, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: UNITED TECHNOLOGIES CORPORATION
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Publication number: 20140144155Abstract: A turbine has a first and second inner wall, an inner casing and a shield element. The first and second inner walls are mounted to the inner casing such that an inner volume for working fluid is separated from an outer volume for cooling fluid. The first and second inner walls and inner casing are arranged to form a cavity in outer volume. The shield element is arranged inside cavity to separate cavity in an inner and outer region in a radially outer position to the inner region. A gap is formed between the first and second inner walls for working fluid between the inner volume and inner region. The shield element is arranged in cavity to form a fluid inlet for injecting cooling fluid from outer region to inner region for generating a predefined recirculation of working fluid and cooling fluid inside inner region.Type: ApplicationFiled: March 23, 2012Publication date: May 29, 2014Inventor: Andrew Down