Working Fluid On At Least One Side Of Heat Exchange Wall Patents (Class 415/178)
  • Patent number: 10408082
    Abstract: An airfoil includes an airfoil body that has a retention pocket and an airfoil piece disposed in the retention pocket. The retention pocket secures the airfoil piece in place. The airfoil piece defines a portion of an airfoil profile of an airfoil section of the airfoil body.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: September 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10393123
    Abstract: A fan unit comprises at least one radial fan comprising: an impeller rotationally driven about a rotation axis; and a fan housing in which the impeller is arranged, the fan housing including a guide wall spirally extending around the fan housing in a circumferential direction of the impeller, the guide wall transitioning into air outlet openings, wherein the guide wall has spirally shaped guide wall segments in the circumferential direction, each of which transitions into one of the air outlet openings, such that the air outlet openings are distributed in the circumferential direction of the impeller.
    Type: Grant
    Filed: December 21, 2016
    Date of Patent: August 27, 2019
    Assignee: Nicotra Gebhardt GmbH
    Inventors: Klaus Gundel, Thomas Heigold, Walter Müller
  • Patent number: 10337405
    Abstract: An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: July 2, 2019
    Assignee: General Electric Company
    Inventors: Tod Robert Steen, Amid Ansari, Anthony Paul Greenwood
  • Patent number: 10273828
    Abstract: The internal combustion engine is provided which may include a cylinder head, a turbine, and a turbine housing. The turbine housing may include an exhaust gas passage, at least one coolant fluid passage, and a wall between the passages. The wall may have a first area (Aexhaust) disposed to absorb heat from an exhaust flow passing through the exhaust gas passage, and a second area (Acoolant) disposed to transfer heat from the wall to be absorbed by a coolant fluid flow passing through the at least one coolant fluid passage, wherein the following applies: Acoolant/Aexhaust?1.2.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: April 30, 2019
    Assignee: Ford Global Technologies, LLC
    Inventors: Kai Sebastian Kuhlbach, Joachim Hansen, Ludwig Stump, Stefan Quiring, Jan Mehring, Carsten Weber
  • Patent number: 10208669
    Abstract: A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70° C. and 90° C., preferably equal to about 80° C.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: February 19, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sebastien Gameiro, Brice Andre, Guillaume Mathon Margueritte, Nicolas Potel
  • Patent number: 10082081
    Abstract: A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: September 25, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael Joseph Murphy, Sean P. Zamora
  • Patent number: 10054312
    Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing.
    Type: Grant
    Filed: February 25, 2015
    Date of Patent: August 21, 2018
    Assignee: United Technologies Corporation
    Inventors: Zhongtao Dai, Kristin Kopp-Vaughan
  • Patent number: 10024170
    Abstract: An integrally bladed rotor with an axial bore having either an inward dishing shape or an axial straight shape with an annular inward projection in which radial cooling holes having an elliptical cross sectional shape are formed, where the radial cooling holes have an elliptical cross sectional shape with a major axis perpendicular to the axial bore in order to reduce stress near an inlet opening of the radial holes in order to increase the LCF life of the IBR. The radial cooling holes discharge into a circumferential channel that is connected to cooling holes extending in the rotor blades.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: July 17, 2018
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Robert L Memmen, Wesley D Brown
  • Patent number: 9988943
    Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James P. Chasse, Jr., Ryan K. Snyder, William K. Ackermann, Pellegrino J. Pisacreta, Judith F. Brooks, Stephanie Ernst
  • Patent number: 9988924
    Abstract: A gas turbine engine comprising first and second axially spaced turbine rotor stages (46, 48) and a turbine casing (56) radially outside the rotor stages. A first seal segment arrangement (58) forms a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56). A first air source (82) is coupled to the first seal segment arrangement (58). A second seal segment arrangement (70) forms a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56). A heating chamber (84) is provided radially between the second seal segment arrangement (70) and the turbine casing (56). A duct (86) is coupled between the first air source (82) and the heating chamber (84).
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: June 5, 2018
    Assignee: ROLLS-ROYCE PLC
    Inventors: Marko Bacic, Leo Vivian Lewis, Robert John Irving
  • Patent number: 9976435
    Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: May 22, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark Borja, Paul W. Palmer
  • Patent number: 9909441
    Abstract: A method of operating a clearance control system for a gas turbine engine, includes estimating, in a control module, thermal expansion values of engine components based at least partially on an exhaust gas temperature of the gas turbine engine, determining an estimated clearance value based on the thermal expansion values and ducting airflow for cooling the engine components.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: March 6, 2018
    Assignee: General Electric Company
    Inventor: Timothy Leo Schelfaut
  • Patent number: 9835033
    Abstract: A hybrid airfoil according to an exemplary aspect of the present disclosure includes, among other things, a leading edge portion made of a first material, a trailing edge portion made of a second material, and an intermediate portion between the leading edge portion and the trailing edge portion made of a non-metallic material. A rib is disposed between the leading edge portion and the intermediate portion. A protrusion of one of the rib and the intermediate portion is received within a pocket of the other of the rib and the intermediate portion.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: December 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Edward F. Pietraszkiewicz, Alexander Staroselsky, Mark F. Zelesky
  • Patent number: 9835173
    Abstract: An electric submersible well pump assembly includes a pump and an electrical motor filled with a dielectric lubricant. A capsule extends around a portion of the motor, defining a chamber between the capsule and the motor. A port through a side wall of the motor communicates the lubricant within the motor to the chamber. Thermoelectric devices are located within the chamber. Voltage supplied to the thermoelectric devices cools the lubricant.
    Type: Grant
    Filed: September 4, 2014
    Date of Patent: December 5, 2017
    Assignee: Baker Hughes, a GE Company, LLC
    Inventors: Anil K. Sadana, Carlos A. Prieto, Sayantan Roy
  • Patent number: 9828915
    Abstract: A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.
    Type: Grant
    Filed: June 15, 2015
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: Carlos Miguel Miranda, Srikanth Chandrudu Kottilingam, Benjamin Paul Lacy
  • Patent number: 9822653
    Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: November 21, 2017
    Assignee: General Electric Company
    Inventors: Christopher Donald Porter, Christopher Lee Golden
  • Patent number: 9758252
    Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventors: Sridhar Adibhatla, Steven Edward Nolte, Gerhard Walter Moeller, Christopher Timothy Gallagher, John William Hanify, Grant Alan Ingram
  • Patent number: 9657587
    Abstract: A method of controlling a rotor tip clearance arrangement of a gas turbine engine and a control system configured to control rotor tip clearance. Steps include measuring at least one engine parameter; determining engine power demand from the at least one engine parameter; and calculating rotor tip clearance given the determined engine power demand. The rotor tip clearance arrangement is controlled to increase or decrease the rotor tip clearance based on the difference between the calculated clearance and a predefined target clearance.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: May 23, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, James Tooke
  • Patent number: 9498820
    Abstract: This invention relates to an apparatus (high shear device) and method for treating liquid metals by intensive melt shearing. The apparatus comprises a stator and a rotor with a small gap between them to provide intensive melt shearing for dispersing efficiently and distributing uniformly gas, liquid and solid phases in liquid metals without severe turbulence at the melt surface. The device can be extended to a multistage high shear pump by arranging individual rotor/stator assemblies either concentrically (one in another) or vertically. The device and high shear pump can be readily integrated into existing casting processes. The device is suitable for use in casting processes including high pressure die casting, low pressure die casting, gravity die casting, sand casting, investment casting, direct chill casting, twin roll casting, and any other casting process which requires liquid metal as a feedstock.
    Type: Grant
    Filed: September 16, 2011
    Date of Patent: November 22, 2016
    Assignee: Brunel University
    Inventors: Zhongyun Fan, Bo Jiang, Yubo Zuo
  • Patent number: 9341412
    Abstract: The present disclosure relates to methods and systems for reducing silica recession of silicon-containing ceramics or silicon-containing ceramic composites, particularly those exposed to a combustion gas or to combustion gas environments, including those exposed to high temperature combustion gas environments. The methods and systems involve silicon-doping of compressed air and/or removal of moisture from compressed air prior to co-mingling the treated compressed air with the combustion gas to which the silicon-containing ceramics or silicon-containing ceramic composites are exposed.
    Type: Grant
    Filed: December 18, 2012
    Date of Patent: May 17, 2016
    Assignee: General Electric Company
    Inventor: Krishan Lal Luthra
  • Patent number: 9334867
    Abstract: The described embodiments relate generally to improving performance characteristics of a low profile fan. More specifically configurations having sloped fan blade edges are disclosed. By applying a gradual slope to each of the fan blades, performance of the fan can be increased without risking contact or rubbing between the fan blades and a fan housing. In some embodiments, the sloped fan blades can be configured to prevent contact when bearings of the fan include a certain amount of tilt play.
    Type: Grant
    Filed: May 3, 2013
    Date of Patent: May 10, 2016
    Assignee: Apple Inc.
    Inventors: Anthony Joseph Aiello, Jesse T. Dybenko, Richard A. Herms
  • Patent number: 9216491
    Abstract: A manufacturing method is provided. The manufacturing method includes forming one or more grooves in a component comprising a substrate. Each groove extends at least partially along the substrate and has a base, a top and at least one discharge end. The manufacturing method further includes forming a crater, such that the crater is in fluid connection with the respective discharge end for each groove, and disposing a coating over at least a portion of an outer surface of the substrate. The groove(s) and the coating together define one or more channels for cooling the component. The coating does not completely bridge each of the one or more craters, such that each crater defines a film exit. A component with cratered film exits is also provided.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: December 22, 2015
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 9133855
    Abstract: The invention relates to a rotor (10) for a turbo machine, in particular for an aircraft turbine, with rotating blades (12) that are joined to a basic rotor body (16), whereby at least one channel (22) extending between the high-pressure side (HD) and the low-pressure side (ND) of rotor (10) radially underneath a blade platform (18) of at least one rotating blade (12) is provided, whereby a slope of a principal axis of extension (H) of channel (22) relative to an axis of rotation (D) of rotor (10) has the same sign as a slope of a principal axis of extension (R) of a radially inner boundary of the flow channel of rotor 10. In addition, the invention relates to a turbo machine having a rotor (10) as well as to a method for manufacturing a rotor (10) for a turbo machine.
    Type: Grant
    Filed: November 11, 2011
    Date of Patent: September 15, 2015
    Assignee: MTU AERO ENGINES GMBH
    Inventors: Hans Peter Borufka, Frank Stiehler
  • Patent number: 9028207
    Abstract: A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
    Type: Grant
    Filed: September 23, 2010
    Date of Patent: May 12, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Humberto A. Zuniga, Ching-Pang Lee, Michael E. Crawford
  • Publication number: 20150110612
    Abstract: The invention relates to a cooled wall segment in the hot gas path of a gas turbine, particularly to a cooled stator heat shield. Such components have to be properly cooled in order to avoid thermal damages of these components and to ensure a sufficient lifetime. The wall segment according to the invention includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting said first and said second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet for the cooling medium and an outlet for the cooling medium.
    Type: Application
    Filed: October 3, 2014
    Publication date: April 23, 2015
    Inventors: Herbert BRANDL, Andrey Anatolievich SEDLOV, Artem IVANOV
  • Publication number: 20150110611
    Abstract: An airfoil cooling circuit for a gas turbine engine having at least one internal cavity with a lobed cross-sectional shape.
    Type: Application
    Filed: May 28, 2013
    Publication date: April 23, 2015
    Inventor: Robert Frederick Bergholz
  • Patent number: 9003793
    Abstract: A turbocharger assembly includes a compressor assembly, a turbine wheel, a shaft, a bearing assembly, and a cooling gas conduit. The compressor assembly includes a compressor impeller. The compressor impeller includes an outermost impeller edge and has a maximum cross-sectional dimension at the outermost impeller edge. The shaft interconnects the compressor impeller and the turbine wheel. The bearing assembly surrounds at least a portion of the shaft. The cooling gas conduit is disposed in fluid communication with the compressor assembly and the bearing assembly. At least a portion of the cooling gas conduit is disposed adjacent the outermost impeller edge such that the cooling gas conduit is configured to receive a portion of intake gases flowing along the outermost impeller edge and guide the portion of the intake gases toward the bearing assembly to cool the bearing assembly.
    Type: Grant
    Filed: May 31, 2013
    Date of Patent: April 14, 2015
    Assignee: GM Global Technology Operations LLC
    Inventors: Louis Begin, Brian J. Edwards, Carnell E. Williams
  • Patent number: 8998563
    Abstract: An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: Philip Robert Rioux
  • Patent number: 8992171
    Abstract: An energy efficient climate control system for an offshore wind turbine that is integrated with the component cooling system is disclosed. The climate control system includes a cooling circuit adapted to carry heat generated by a component of the nacelle to outside the nacelle. The climate control system also includes an airflow system adapted to receive a warm outflow of coolant from the cooling circuit, across a variable flow control valve, the airflow system supplying clean ambient air to the nacelle at a predetermined relative humidity. The variable flow control valve regulates a flow rate of the coolant through the airflow system to adjust the relative humidity of the air entering the nacelle.
    Type: Grant
    Filed: September 1, 2011
    Date of Patent: March 31, 2015
    Assignee: Gamesa Innovation & Technology, S.L.
    Inventor: Peri Sabhapathy
  • Patent number: 8973375
    Abstract: One embodiment of the present application includes a hot section component of a gas turbine engine having a covering. The covering includes a protrusion and is attached to the hot section component though a flexible retainer. In one form the covering is made from ceramic matrix composite. The flexible retainer has a closed position and an open position. The retainer secures the protrusion to the hot section component when it engages part of the protrusion when in the closed position.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: March 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Mark O'Leary
  • Patent number: 8967958
    Abstract: A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.
    Type: Grant
    Filed: December 17, 2010
    Date of Patent: March 3, 2015
    Assignee: Techspace Aero S.A.
    Inventors: Denis Bajusz, David Depaepe, Jacques Charlier, Nicolas Raimarckers
  • Patent number: 8961114
    Abstract: One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: February 24, 2015
    Assignee: General Electric Company
    Inventor: Michael Anthony Ruthemeyer
  • Publication number: 20150033696
    Abstract: A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Brian David Moran, Kyle Eric Benson, Jeffery Craig Moree, Chandresh R. Shah, Xiaoqiang Zeng
  • Patent number: 8932007
    Abstract: An axial flow gas turbine (20) includes a rotor (13) and a stator, and a hot gas path through which hot gas passes. The rotor (13) includes a rotor shaft (15) with axial slots for receiving a plurality of blades (B1-B3) arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows. The rotor shaft (15) is configured to axially conduct a main flow of cooling air along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and the rotor shaft (15) supplies the interior of the blades (B1-B3) with cooling air (18). Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: January 13, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Alexander Anatolievich Khanin, Valery Kostege, Anton Sumin
  • Patent number: 8932010
    Abstract: A centrifugal fan module, a heat dissipation device having the same and an electric device having the heat dissipation device are provided, in which the heat dissipation device includes a fin module and a centrifugal fan module including a volute-shaped frame and a centrifugal fan pivoted in the volute-shaped frame. The volute-shaped frame includes an air inlet, a larger air outlet and a smaller air outlet. The air inlet and the smaller air outlet are both on the same surface of the volute-shaped frame. The larger air outlet is coupled to the fin module. The smaller air outlet is arranged correspondingly to a maximum wind-speed flowing path of the centrifugal fan.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: January 13, 2015
    Assignee: Quanta Computer Inc.
    Inventors: Yu-Nien Huang, Ching-Chin Chen, Chun-Fa Tseng, Chun-Che Chiu, Hsin-Yu Wang, Sung-Fong Yang
  • Patent number: 8926272
    Abstract: 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: Grant
    Filed: September 7, 2011
    Date of Patent: January 6, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Troy C. Schank, Monte A. McGlaun
  • Publication number: 20150003975
    Abstract: 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: Application
    Filed: September 19, 2014
    Publication date: January 1, 2015
    Inventors: Sergey SHCHUKIN, Robert MARMILIC
  • Patent number: 8894359
    Abstract: 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: Grant
    Filed: December 8, 2011
    Date of Patent: November 25, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Mrinal Munshi, John Finneran, Ching-Pang Lee, Yevgeniy Shteyman, Daryl Graber, Matthew R. Porter, Jonathan M. Leagon
  • Patent number: 8894363
    Abstract: 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: Grant
    Filed: February 9, 2011
    Date of Patent: November 25, 2014
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, Humberto A. Zuniga, Jay A. Morrison, Brede J. Kolsrud, John J. Marra
  • Patent number: 8893499
    Abstract: 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: Grant
    Filed: October 9, 2012
    Date of Patent: November 25, 2014
    Assignee: Dresser-Rand Company
    Inventor: William C. Maier
  • Publication number: 20140321971
    Abstract: 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: Application
    Filed: July 8, 2014
    Publication date: October 30, 2014
    Applicant: DRESSER-RAND COMPANY
    Inventors: James Jeffrey Moore, Andrew Hampton Lerche, Brian Scott Moreland
  • Patent number: 8858158
    Abstract: 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: Grant
    Filed: August 6, 2009
    Date of Patent: October 14, 2014
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Kazutaka Ikeda, Katsuya Yamashita, Takao Inukai, Kazuhiro Saito, Kouichi Kitaguchi, Shogo Iwai, Shigekazu Miyashita
  • Patent number: 8845273
    Abstract: 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: Grant
    Filed: May 17, 2011
    Date of Patent: September 30, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Zahid M. Hussain, Christopher T. J. Sheaf, Brian A. Handley
  • Publication number: 20140286763
    Abstract: 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: Application
    Filed: January 22, 2013
    Publication date: September 25, 2014
    Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
  • Publication number: 20140271154
    Abstract: 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: Application
    Filed: March 14, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Donald Earl FLOYD, Kenneth Black
  • Publication number: 20140271129
    Abstract: 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: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: Howmet Corporation
    Inventors: Boyd A. Mueller, Michael A. Pepper, Daren K. Rogers, Gail R. Cole
  • Patent number: 8834108
    Abstract: 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: Grant
    Filed: February 24, 2010
    Date of Patent: September 16, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Dimitrie Negulescu, Stephan Lisiewicz
  • Patent number: 8826668
    Abstract: 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: Grant
    Filed: August 2, 2011
    Date of Patent: September 9, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Jay A. Morrison
  • Patent number: 8827638
    Abstract: 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: Grant
    Filed: July 15, 2011
    Date of Patent: September 9, 2014
    Assignee: iHi Charging Systems International GmbH
    Inventor: Joachim Delitz
  • Patent number: 8820092
    Abstract: 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: Grant
    Filed: April 9, 2009
    Date of Patent: September 2, 2014
    Assignee: Williams International Co., L.L.C.
    Inventors: Robert S. Thompson, Jr., Gregg Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky