Working Fluid On At Least One Side Of Heat Exchange Wall Patents (Class 415/178)
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Patent number: 8926272Abstract: A rotor blade for an aircraft includes an airfoil skin, an active element, and an actuator configured to operate the active element. A heat pipe is configured to promote heat transfer from the actuator to the airfoil skin. The heat pipe has a slope gradient such that a centrifugal force generated during rotation of the rotor blade promotes travel of a condensed working fluid within the heat pipe to move from a condenser end of the heat pipe toward an evaporator end of the heat pipe.Type: GrantFiled: September 7, 2011Date of Patent: January 6, 2015Assignee: Textron Innovations Inc.Inventors: Troy C. Schank, Monte A. McGlaun
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Publication number: 20150003975Abstract: The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.Type: ApplicationFiled: September 19, 2014Publication date: January 1, 2015Inventors: Sergey SHCHUKIN, Robert MARMILIC
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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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Patent number: 8893499Abstract: An expander-generator is disclosed having an expansion device and a generator disposed within a hermetically-sealed housing. The expansion device may be overhung and supported on or otherwise rotate a hollow expansion rotor having a thrust balance seal being arranged at least partially within a chamber defined in the expansion rotor. Partially-expanded working fluid is extracted from an intermediate expansion stage and a first portion of the extracted working fluid is used cool the generator and accompanying radial bearings. A second portion of the extracted working fluid may be introduced into the chamber defined within the expander rotor via a conduit defined in the thrust balance seal chamber. The second portion of extracted working fluid minimizes unequal axial thrust loads on the expander rotor due to the overhung arrangement.Type: GrantFiled: October 9, 2012Date of Patent: November 25, 2014Assignee: Dresser-Rand CompanyInventor: William C. Maier
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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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Publication number: 20140321971Abstract: An internally-cooled centrifugal compressor having a shaped casing and a diaphragm disposed within the shaped casing having a gas side and a coolant side so that heat from a gas flowing through the gas side is extracted via the coolant side. An impeller disposed within the diaphragm has a stage inlet on one side and a stage outlet for delivering a pressurized gas to a downstream connection. The coolant side of the diaphragm includes at least one passageway for directing a coolant in a substantially counter-flow direction from the flow of gas through the gas side.Type: ApplicationFiled: July 8, 2014Publication date: October 30, 2014Applicant: DRESSER-RAND COMPANYInventors: James Jeffrey Moore, Andrew Hampton Lerche, Brian Scott Moreland
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Patent number: 8858158Abstract: A steam turbine 10 is comprised of a double-structured casing configured of an outer casing 21 and an inner casing 20, a turbine rotor 23 disposed through the inner casing and having a plurality of stages of moving blades 22 implanted, and a plurality of stages of stationary blades 25 disposed alternately with the moving blades 22 in the axial direction of the turbine rotor 23 in the inner casing 20. The steam turbine 10 is further provided with a discharge passage 30 which externally guides steam, which has flown in the inner casing and passed the final stage moving blades while performing expansion work, directly from the inner casing interior.Type: GrantFiled: August 6, 2009Date of Patent: October 14, 2014Assignee: Kabushiki Kaisha ToshibaInventors: Kazutaka Ikeda, Katsuya Yamashita, Takao Inukai, Kazuhiro Saito, Kouichi Kitaguchi, Shogo Iwai, Shigekazu Miyashita
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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: 20140286763Abstract: A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.Type: ApplicationFiled: January 22, 2013Publication date: September 25, 2014Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
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Publication number: 20140271154Abstract: A turbine inner shell for a turbine engine includes one or more mounting grooves, each of which receives a fluid conduit. A temperature controlling fluid is circulated through fluid conduit to selectively heat or cool surrounding portions of the turbine inner shell, to thereby control the thermal growth of those portions of the turbine inner shell. This makes it possible to selectively control a clearance between the tips of rotating turbine blades and the surrounding shrouds of the turbine.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Donald Earl FLOYD, Kenneth Black
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Publication number: 20140271129Abstract: A method is provided for making a mold for casting advanced turbine airfoils (e.g. gas turbine blade and vane castings) which can include complex internal and external air cooling features to improve efficiency of airfoil cooling during operation in the gas turbine hot gas stream. The method steps involve incorporating at least one fugitive insert in a ceramic material in a manner to form a core and at least a portion of an integral, cooperating mold wall wherein the core defines an internal cooling feature to be imparted to the cast airfoil and the at least portion of the mold wall has an inner surface that defines an external cooling feature to be imparted to the cast airfoil, selectively removing the fugitive insert, and incorporating the core and the at least portion of the integral, cooperating mold wall in a mold for receiving molten metal or alloy cast in the mold.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: Howmet CorporationInventors: Boyd A. Mueller, Michael A. Pepper, Daren K. Rogers, Gail R. Cole
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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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Connection assembly for joining a turbine housing and a bearing housing and exhaust gas turbocharger
Patent number: 8827638Abstract: In a connection assembly of a turbine housing to a bearing housing of an exhaust gas turbocharger and to an exhaust gas turbocharger, wherein the turbine housing and the bearing housing are centered relative to each other and connected to each other in the region of a connection joint including a sealing assembly with a heat shield disposed between the turbine housing and the bearing housing, at least one cutout is provided in the heat shield for accommodating a centering means by way of which the turbine housing and the bearing housing are directly centered relative to one another.Type: GrantFiled: July 15, 2011Date of Patent: September 9, 2014Assignee: iHi Charging Systems International GmbHInventor: Joachim Delitz -
Patent number: 8826668Abstract: A system for cooling a wall (24) of a component having an outer surface with raised ribs (12) defining a structural pocket (10), including: an inner wall (26) within the structural pocket and separating the wall outer surface within the pocket into a first region (28) outside of the inner wall and a second region (40) enclosed by the inner wall; a plate (14) disposed atop the raised ribs and enclosing the structural pocket, the plate having a plate impingement hole (16) to direct cooling air onto an impingement cooled area (38) of the first region; a cap having a skirt (50) in contact with the inner wall, the cap having a cap impingement hole (20) configured to direct the cooling air onto an impingement cooled area (44) of the second region, and; a film cooling hole (22) formed through the wall in the second region.Type: GrantFiled: August 2, 2011Date of Patent: September 9, 2014Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Jay A. Morrison
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Patent number: 8820092Abstract: Fuel (12) is supplied to a rotatable portion (118) of a gas turbine engine (10) comprising a rotor (24) and at least one blade (26, 26.1) operatively coupled thereto, so as to provide for cooling at least one of the rotor (24) or the at least one blade (26, 26.1) by transforming the fuel (12) to a vapor or gaseous state. The fuel (12) is discharged in a vapor or gaseous state from the rotatable portion (118) directly into a combustion chamber (16) of the gas turbine engine (10).Type: GrantFiled: April 9, 2009Date of Patent: September 2, 2014Assignee: Williams International Co., L.L.C.Inventors: Robert S. Thompson, Jr., Gregg Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky
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Publication number: 20140216056Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.Type: ApplicationFiled: September 28, 2012Publication date: August 7, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Frederick M. Schwarz, John T. Schmitz
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Publication number: 20140208768Abstract: A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section. The ducting (32) bypasses the combustor (16). A heat exchanger (34) may be arranged in the flow path to extract heat from the flow between the compressor and the component. One or more valves (36;64;66) in the flow path are actuated under the control of a controller (48;60) at a predetermined frequency of actuation so as to pulse the flow between the heat exchanger and the component, typically to improve the aerodynamic efficiency of turbine blades in use.Type: ApplicationFiled: December 19, 2012Publication date: July 31, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Patent number: 8790073Abstract: A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side.Type: GrantFiled: January 21, 2010Date of Patent: July 29, 2014Assignee: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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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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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: 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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Patent number: 8756910Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique cooling system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooling one or more objects of cooling. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.Type: GrantFiled: December 27, 2010Date of Patent: June 24, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Eric Sean Donovan, William Daniel Feltz, Steven Wesley Tomlinson
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Publication number: 20140169934Abstract: Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes.Type: ApplicationFiled: December 14, 2012Publication date: June 19, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: United Technologies Corporation
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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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Publication number: 20140147259Abstract: An impingement cover (460) for fusing to a gas turbine engine turbine nozzle (451) with a nozzle rail (455) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail (455). The body has a plate like shape and includes a plurality of impingement holes (464), a first edge, a second edge, and a first airfoil cooling hole (470). The plurality of tabs includes a first tab (461) extending from the first edge, and a second tab (462) extending from the second edge. The second tab (462) is located in a different quadrant of the body than the first tab (461).Type: ApplicationFiled: November 29, 2012Publication date: May 29, 2014Applicant: SOLAR TURBINES INCORPORATEDInventors: William Landon Reilly, David Jeorling, Adrian Nazareno Reyes
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Patent number: 8727704Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.Type: GrantFiled: August 19, 2011Date of Patent: May 20, 2014Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Eric C. Berrong
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Patent number: 8727714Abstract: A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer surface of the component (12). An intermediate panel (22) is provided and preferably preformed to a general outer contour of the component (12), and is positioned over the inner panel (16). An external pressure force is applied across a surface area of the intermediate panel (22) against the outer surface of the component (12) to contour the intermediate panel (22) according to a geometric configuration formed by the ribs (38) thereby forming cooling chambers (24) between the outer surface and ribs (38) of the component (12) and the intermediate panel (22).Type: GrantFiled: April 27, 2011Date of Patent: May 20, 2014Assignee: Siemens Energy, Inc.Inventors: Raymond G. Snider, Jay A. Morrison
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Patent number: 8721271Abstract: An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by: (I) diverting air flow from the inner side of the oil cooler towards the outer side of the oil cooler, (ii) enhancing heat exchange performance at the leading edge of the cooler, and/or (iii) suppressing airflow wake at the trailing edge of the cooler.Type: GrantFiled: November 30, 2010Date of Patent: May 13, 2014Assignee: Rolls-Royce PLCInventors: Yi Wang, Miles T Trumper, Mark J Wilson, Peter Ireland, Robert C Chambers
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Publication number: 20140112767Abstract: A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall (2) that delimits the flow channel and an outer wall (1) that is closed off vis-Ã -vis the environment. A heat-protection plate (3) is arranged on the radial outside of the inner wall, and insulation (4) is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel (6) is formed between the insulation and the radial inside of the outer wall, the cooling-air channel (6) having at least one air-guiding element (5) resting against the insulation.Type: ApplicationFiled: October 22, 2013Publication date: April 24, 2014Inventors: Manfred Feldmann, Norbert Schinko, Christian Eichler, Sebastian Kaltenbach
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Patent number: 8702383Abstract: A switchgear cabinet for a wind turbine has a cabinet housing with a ventilation hole defined therein. A fan is disposed in the cabinet housing and supported on the cabinet housing so as to be disposed in front of or in the ventilation hole. A circumferential coaming is disposed on the outer side of the cabinet housing surrounding the ventilation hole. A pan-shaped cover has a closed front and a rim. The cover is disposed over the coaming with the rim extending around the coaming. The cover is spaced from the coaming so as to define at least one air-permeable connection between the fan and the surroundings of the cabinet.Type: GrantFiled: August 19, 2008Date of Patent: April 22, 2014Inventors: Hermann Kestermann, Cathrin Zwartjes
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Publication number: 20140099193Abstract: A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.Type: ApplicationFiled: October 5, 2012Publication date: April 10, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Xiuzhang James Zhang, Adebukola Benson, Zhirui Dong
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Publication number: 20140093361Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.Type: ApplicationFiled: September 28, 2012Publication date: April 3, 2014Applicant: United Technologies CorporationInventors: Sarah Riley, Mark A. Boeke, Jeffrey J. DeGray, Shawn J. Gregg
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Patent number: 8684667Abstract: A low-pressure steam turbine includes an inner casing, an outer casing arranged outside the inner casing so as to cover the inner casing, a heat carrier heating channel between the inner casing and the outer casing so that a heat carrier flows therethrough, a heat carrier inlet passage for introducing the heat carrier into the heat carrier heating channel, and a heat carrier chamber in the inside of at least one of stationary blades to receive the heat carrier that has passed through the heat carrier heating channel. The at least one of stationary blades is heated by the heat carrier which has been heated by passing through the heat carrier heating channel.Type: GrantFiled: March 29, 2012Date of Patent: April 1, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Takashi Maruyama
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Patent number: 8684682Abstract: A power generating apparatus of renewable energy type includes a tower, a nacelle which is supported rotatably by a tip portion of the tower; a main shaft rotatable with a blade; a hydraulic pump which is housed in the nacelle and is driven by rotation of the main shaft; a hydraulic motor which is driven by operating oil supplied from the hydraulic pump; a generator which is coupled to the hydraulic motor; an operating-oil line which is provided between the hydraulic pump and the hydraulic motor and through which the operating oil circulates; a cooling-medium line through which cooling medium for cooling the operating oil circulates via an intermediate heat exchanger; and a main heat exchanger which cools the cooling medium by heat exchange with cool water source around a base portion of the tower, and one of the operating-oil line.Type: GrantFiled: January 31, 2012Date of Patent: April 1, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Yu Akashi, Takeshi Matsuo, Shinsuke Sato, Takuro Kameda, Yoshiyuki Morii, Fumio Hamano
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Patent number: 8678750Abstract: A specialty pump and heat exchange system having a fluid pump driven by a gear assembly. The fluid pump has a pump casing and an inboard head that form a fluid passageway when connected together. The gear assembly uses lubricant in the transmission and that lubricant is cooled by being pumped from the gear assembly through a lubricant passageway in the inboard head and then recycled back to the gear assembly for further use. In addition to cooling the lubricant, the system warms the fluid pump and/or fluid passing through the fluid pump.Type: GrantFiled: April 18, 2011Date of Patent: March 25, 2014Assignee: W. S. Darley + Co.Inventor: Douglas W. Seitz
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Patent number: 8680672Abstract: A semiconductor package is provided for carrying a sleeve member and a fan wheel axially coupled to the sleeve member so as to provide a heat dissipating function. The semiconductor package includes: a substrate; a coil module and at least an electronic component disposed on the substrate; and an encapsulant formed on the substrate for encapsulating the coil module and the electronic component so as to prevent the coil module and the electronic component from disturbing air flow generated by the fan wheel during operation, thereby avoiding generation of noises or vibrations.Type: GrantFiled: March 23, 2012Date of Patent: March 25, 2014Assignee: Amtek Semiconductors Co., Ltd.Inventor: Hsiang-Wei Tseng
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Publication number: 20140079540Abstract: In accordance with an exemplary embodiment, a method of manufacturing a stator airfoil assembly includes forming an interior wall of a stator airfoil using an additive manufacturing technique, forming an exterior wall of the stator airfoil using the additive manufacturing technique, and forming a plurality of internal ribs between the interior wall and the exterior wall using the additive manufacturing technique. A cooling air circuit is formed in a space between the interior wall and the exterior wall. Further, the interior wall, the exterior wall, and the internal ribs are formed simultaneously as an integral structure by using the additive manufacturing technique.Type: ApplicationFiled: September 17, 2012Publication date: March 20, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark C. Morris, Donald G. Godfrey, Harry Lester Kington
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Patent number: 8668438Abstract: A turbine assembly having a bladed turbine wheel and a turbine casing (1000), extending axially of the turbine assembly, radially outwardly surrounding the tips of the blades of the turbine wheel, the casing having at least one radially outwardly extending dummy flange (2100, 2200) off which, in axial direction, one or more cooling manifolds (1100, 1200, 1300), wrapping radially outwardly around the casing, are mounted, the or each cooling manifold being adapted to receive cooling air and to discharge the cooling air radially inwardly towards the casing, for cooling the casing.Type: GrantFiled: March 16, 2010Date of Patent: March 11, 2014Assignee: Rolls-Royce PLCInventor: Rajinder Saroi
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Publication number: 20140064942Abstract: A cooling arrangement in a platform in a rotor blade or a sidewall in a stator blade in a turbine of a combustion turbine engine is described. The cooling arrangement may include: a cooling chamber configured to pass coolant from an inlet to an outlet; and a rib positioned within the cooling chamber. The rib may partially divide the cooling chamber so to form a switchback. The rib may be canted with respect to the cooling chamber such that the switchback has an ever narrowing channel.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Inventors: Christopher Donald Porter, Gary Michael Itzel
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Patent number: 8651805Abstract: A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.Type: GrantFiled: April 22, 2010Date of Patent: February 18, 2014Assignee: General Electric CompanyInventors: Benjamin Paul Lacy, Ronald Scott Bunker, Gary Michael Itzel
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Publication number: 20140044530Abstract: A portable electronic device includes a main body and a heat dissipation module with a tiltedly installed centrifugal fan inside thereof. The main body includes an upper housing wall and a lower housing wall. The heat dissipation module includes a centrifugal fan, a heat dissipation fin array and a heat pipe. The centrifugal fan includes an impeller, a radial air outlet, an upper axial air inlet and a lower axial air inlet, wherein the centrifugal fan has a first side that is in contact with the upper housing wall and an opposite second side that is in contact with the lower housing wall. The heat dissipation fin array is located at the radial air outlet of the centrifugal fan. The heat pipe has a first end connected with the heat dissipation fin array and a second opposite end connected with a heat source.Type: ApplicationFiled: August 8, 2012Publication date: February 13, 2014Applicant: Quanta Computer Inc.Inventors: Ming-Hsien LIN, Yun-Jeng Lin, Yu-Hsun Lin
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Publication number: 20140037436Abstract: A turbine housing (3) applied to a turbine (2) incorporated in a turbocharger (1) includes a main body (10) in which a wheel housing chamber (13) housing a turbine wheel (4) and an exhaust passage (15) are provided. The exhaust passage (15) has one end communicating with an outlet of the wheel housing chamber (13) and the other end providing an exhaust port (15a). The main body (10) is provided with an upstream-side inner pipe (20) and a downstream-side inner pipe (21) therein. The upstream-side inner pipe has a shroud portion (20) which is located in the wheel housing chamber (13) and extends along edges of turbine blades (5) of the turbine wheel (4). The downstream-side inner pipe (21) is arranged in the exhaust passage (15) so as to be located on a downstream side of the upstream-side inner pipe (20). A thickness (t2) of the downstream-side inner pipe (21) is thinner than a thickness (t1) of the upstream-side inner pipe (20).Type: ApplicationFiled: April 26, 2011Publication date: February 6, 2014Applicant: TOYOTA JIDOSHA KABUSHIKI KAISHAInventor: Masakazu Tabata
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Publication number: 20140033736Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.Type: ApplicationFiled: August 3, 2012Publication date: February 6, 2014Inventors: Tracy A. Propheter-Hinckley, Steven Bruce Gautschi, San Quach
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Patent number: 8636463Abstract: Cooling channels through the interior of a machine component that include: a first set of cooling channels, the first set of cooling channels including a plurality of parallel channels that reside in a first plane; a second set of cooling channels, the second set of cooling channels including a plurality of parallel channels that reside in a second plane. Along a longitudinal axis, the cooling channels of the first and second set of cooling channels may include an alternating diverging-converging configuration, the alternating diverging-converging configuration creating a series of broader chamber sections connected by a series of narrower throat sections. The first set of cooling channels and the second set of cooling channels may be configured such that, when viewed from the side, a crisscrossing pattern with a plurality of intersections is formed.Type: GrantFiled: March 31, 2010Date of Patent: January 28, 2014Assignee: General Electric CompanyInventor: James William Vehr
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Patent number: 8632303Abstract: A wind turbine generator includes a tower, at least one blade, a hub supporting the blade, a nacelle supported by the tower and having a duct part with an intake port and an exhaust port, and a heat exchanger provided in the duct part and cooling a cooling medium for a heat-producing component inside the tower or nacelle. The wall of the nacelle has a double wall structure constituted of an inner wall and an outer wall in an area where the duct part is provided. The inner wall forms a bottom surface of the duct part and has a curved portion which curves inward toward a center line of the nacelle with increasing distance from the hub. The duct part increases in cross-section from a side of the intake port to a side of the exhaust port at least in an area where the curved portion is formed.Type: GrantFiled: November 8, 2011Date of Patent: January 21, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Yu Akashi, Takeshi Matsuo, Shinsuke Sato, Takuro Kameda
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Publication number: 20140010640Abstract: A pump assembly having improved cooling for use in a selective catalytic reduction system is disclosed. The pump assembly comprises a pump housing having a body portion and a nozzle portion extending from the body portion, a jacket including a cavity for receiving the pump housing, first and second ports for cooling fluid, and a flow guide disposed between the jacket and the pump housing. The cavity includes a first compartment for cooling fluid defined in part by the flow guide and in part by the pump housing and being in fluid communication with the first port; and a second compartment for cooling fluid defined in part by the flow guide and in part by the jacket. The first compartment is in fluid communication with the second port by way of the second compartment.Type: ApplicationFiled: March 22, 2012Publication date: January 9, 2014Applicant: DELPHI TECHNOLOGIES HOLDING, S.A.R.L.Inventors: Keith E. Wright, Michael Peter Cooke, David W. Needham, Martin Paul Hardy
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Publication number: 20140000285Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.Type: ApplicationFiled: July 2, 2012Publication date: January 2, 2014Inventors: Russell J. Bergman, Leonard A. Bach, Brandon W. Spangler
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Patent number: 8616834Abstract: A heat exchanger apparatus includes: (a) an airfoil having opposed pressure and suction sides, a root, a tip, and spaced-apart leading and trailing edges; and (b) a plenum integrally formed within the airfoil which is configured to receive a flow of circulating working fluid; and (c) inlet and outlet ports communicating with the plenum and an exterior of the airfoil.Type: GrantFiled: April 30, 2010Date of Patent: December 31, 2013Assignee: General Electric CompanyInventors: Glenn Knight, III, Bojan Lukovic, Daniel Laborie, Kenneth S. Scheffel
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Publication number: 20130343882Abstract: An impeller radial pump includes a pump chamber with a central suction and with a pump chamber outlet, wherein an impeller is provided in the pump chamber. Radially outside of the impeller, a circular ring shaped and circumferential pump chamber ring section is provided as a part of the pump chamber, wherein the pump chamber ring section essentially has an extension along the axial direction of the pump from the impeller against the suction direction. The pump chamber ring section has a varying width and is configured to be narrower in a compression region in the circulation direction.Type: ApplicationFiled: June 21, 2013Publication date: December 26, 2013Inventors: Tobias Albert, Uwe Koegel
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Patent number: 8613589Abstract: To provide a thermal insulation structure for a structural member and a scroll structure which can be easily used even in integrally constructed structural members and which can ensure reliability and thermal insulation properties. Provided are securing portions (52 and 53) extending outward from an outer wall of the structural member; a press plate (55) attached to the securing portions (52 and 53), with a gap between the press plate and the outer wall; and a thermal insulation member (56) disposed between the outer wall and the press plate (55).Type: GrantFiled: March 27, 2009Date of Patent: December 24, 2013Assignees: Pebble Bed Modular Reactor (Pty) Limited, Mitsubishi Heavy Industries, Ltd.Inventors: Shoki Yamashita, Toshihiro Inoue