Ice Preventer Or De-icer Patents (Class 60/39.093)
  • Patent number: 10030536
    Abstract: A combination of a gas turbine pressure sensing assembly and an engine electronics unit. The pressure sensing assembly includes a pressure manifold having an air inlet and one or more air outlets. The pressure sensing assembly further includes one or more pressure sensors connected to the air outlets to sense the pressure of air entering through the air inlet. The engine electronics unit in operation produces waste heat. The pressure sensing assembly further includes a heat conduction path which thermally connects the engine electronics unit to the manifold such that the manifold acts as a sink for the waste heat. The temperature rise of the manifold produced by the waste heat preventing icing of the manifold.
    Type: Grant
    Filed: November 27, 2015
    Date of Patent: July 24, 2018
    Assignee: ROLLS-ROYCE PLC
    Inventor: David Brookes
  • Patent number: 9915164
    Abstract: A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.
    Type: Grant
    Filed: April 16, 2015
    Date of Patent: March 13, 2018
    Assignee: United Technologies Corporation
    Inventor: Gary D. Roberge
  • Patent number: 9879599
    Abstract: A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The anti-ice valve is opened at startup of the gas turbine engine to assist compressor stability.
    Type: Grant
    Filed: December 31, 2012
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Claude Mercier, Gary Collopy
  • Patent number: 9512580
    Abstract: A deicing method includes the steps of determining a necessary quantity of heat to substantially vaporize an interfacial layer between a solid surface and a layer of ice and applying pulsed heating at the interfacial layer. The pulsed heating is applied with the determined necessary quantity of heat to substantially vaporize the interfacial layer.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: December 6, 2016
    Assignee: Elwha LLC
    Inventors: William D. Duncan, Peter L. Hagelstein, Roderick A. Hyde, Muriel Y. Ishikawa, Jordin T. Kare, David B. Tuckerman, Lowell L. Wood, Jr., Thomas A. Weaver
  • Patent number: 9102411
    Abstract: The present invention relates to a method for commanding and controlling at least one resistive heating element (1) belonging to an aircraft turbojet engine nacelle deicing set, characterized in that it involves the steps aimed at: obtaining, from a central control unit (6) of the aircraft, parameters representative of the exterior flight conditions; determining a thermal model corresponding to the flight conditions obtained; as a function of the thermal model, delivering the appropriate corresponding electrical power (4) to the resistive heating element.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: August 11, 2015
    Assignee: AIRCELLE
    Inventors: David Pereira, Laurence Lemains
  • Patent number: 9038363
    Abstract: The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.
    Type: Grant
    Filed: January 20, 2010
    Date of Patent: May 26, 2015
    Assignee: AIRCELLE
    Inventors: David Pereira, Laurence Lemains
  • Patent number: 9027353
    Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: May 12, 2015
    Assignee: United Technologies Corporation
    Inventors: Jorn A. Glahn, Clifton J. Crawley, Jr., Philip S. Stripinis, William K. Ackermann
  • Patent number: 9016633
    Abstract: A de-icing system and method. An electromechanical actuator heat sink is operable to receive heat from an electromechanical actuator, and a heat distribution element is operable to distribute heat to a surface. A heat transportation device is operable to transport heat from the electromechanical actuator heat sink to the heat distribution element.
    Type: Grant
    Filed: June 13, 2011
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventors: Julie Fatemeh Asfia, David Blanding, Jeffrey Coffman
  • Patent number: 9016065
    Abstract: An air intake system for a gas turbine includes one or more coils in airflow communication with an inlet arrangement. Each coil is constructed and arranged to have a respective upstream face velocity that is intended to be within 20% of the other coils. Each coil utilizes a working fluid of a predetermined temperature range conveyed there through and a plurality of spaced fins. The fins are spaced apart to permit air to flow between adjacent fins as air flows through the coil. At least one of the coils has a number of fins per inch that is different from the number of fins per inch of the other coils. Alternatively, each individual coil has at least one section with fewer or greater numbers of fins per inch that the other sections of that coil.
    Type: Grant
    Filed: February 14, 2011
    Date of Patent: April 28, 2015
    Assignee: Donaldson Company, Inc.
    Inventor: Theodore Philip Bezat
  • Patent number: 9003760
    Abstract: An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: April 14, 2015
    Assignee: Airbus Operations SAS
    Inventors: Frédéric Chelin, Thierry Surply, Dominique Haro, Fabrice Gantie, David Lambert
  • Patent number: 8997451
    Abstract: An engine and pod assembly for an aircraft includes a pod receiving an engine having an air intake. A rotating nose cone extends on the nose cone, as well as a device for limiting the formation of ice. The device includes means for creating a circumferential heterogeneity of ice on the nose cone.
    Type: Grant
    Filed: March 12, 2010
    Date of Patent: April 7, 2015
    Assignee: Sagem Defense Securite
    Inventors: François Dufresne de Virel, Michel Pealat, Patrick Joyez, Bruce Pontoizeau, Jean-François Lacuisse, Sylvie Wintenberger
  • Patent number: 8984855
    Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: March 24, 2015
    Assignee: SNECMA
    Inventors: Mickael Delapierre, Herve Gignoux, Gael Loro, Sylvie Wintenberger
  • Patent number: 8973650
    Abstract: A system, including a superconductive heat transfer assembly, including, a first superconductive heat transfer pipe, a second superconductive heat transfer pipe, and a superconductive heat transfer contact switch configured to open and close a gap between the first superconductive heat transfer pipe and the second superconductive heat transfer pipe.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: March 10, 2015
    Assignee: General Electric Company
    Inventors: Harish Chandra Dhingra, Donald Gordon Laing
  • Publication number: 20150040577
    Abstract: A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.
    Type: Application
    Filed: August 30, 2013
    Publication date: February 12, 2015
    Inventors: Dave Dischinger, Ronald Goodwin, Harry Lester Kington
  • Publication number: 20150033698
    Abstract: A system includes a gas turbine system that has a turbine, a combustor, and a compressor having an air intake. The air intake is configured to supply an air flow to the compressor. The system also includes a fluid injection system that has a fluid wash system configured to inject a wash fluid into the gas turbine system via the air intake. The fluid wash system includes an injector configured to inject the wash fluid into the gas turbine system and an anti-icing system configured to inject an anti-icing fluid into the gas turbine system via the air intake. The anti-icing system is configured to inject the anti-icing fluid into the gas turbine system via the injector.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Jose Antonio Cuevas, Tho Nguyen, Horacio Solis
  • Patent number: 8931252
    Abstract: A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled ? relative to the radial line; the angles ? and ? are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: January 13, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Giles Anthony Richardson, David MacManus, Christopher Thomas John Sheaf
  • Patent number: 8915058
    Abstract: A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between. The arrangement includes a heat transfer member extending from the first end at least part way along the body towards the second end. A heat source is arranged in use to heat the heat transfer member in the vicinity of the first end of the body. A plurality of thermal control layers are provided on the heat transfer member, each of the layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member. The arrangement may be used for prevention of icing of an aerofoil body such as a blade, vane or the like.
    Type: Grant
    Filed: June 3, 2011
    Date of Patent: December 23, 2014
    Assignee: Rolls-Royce PLC
    Inventors: David S Knott, Alexis Lambourne, Andrew M Rolt, Cosimo Buffone
  • Publication number: 20140366552
    Abstract: The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present invention is to provide a method and a device for suppressing the formation of ice on said structures, which avoid the disadvantages of known solutions, such as a reduction of the performance of the gas turbine, and have a simple and broad applicability. According to the present invention the mechanical vibratory energy of said structures during operation is converted into electrical energy by a piezoelectric element, firmly applied to said structure, and in a connected electrical circuit the generated electrical energy is then converted into thermal energy by an ohmic resistor and this thermal energy is conducted to at least a portion of the structure for suppressing ice formation. Excess energy may be transmitted by a transmitter to other circuits in adjacent structures.
    Type: Application
    Filed: June 17, 2014
    Publication date: December 18, 2014
    Inventors: Jaroslaw Leszek SZWEDOWICZ, Andreas BAUER, Marcus NEUBAUER, Sebastian Marc SCHWARZENDAHL
  • Patent number: 8904747
    Abstract: A gas turbine inlet heating system is disclosed. In one embodiment, the system includes: a compressor having: an inlet bellmouth adjacent to a set of inlet guide vanes (IGVs); and an outlet fluidly connected to the inlet bellmouth; and a conduit coupled to an outlet of the compressor, the conduit including a control valve, the conduit for diverting a first portion of compressed air from the outlet of the compressor to the inlet bellmouth.
    Type: Grant
    Filed: July 1, 2011
    Date of Patent: December 9, 2014
    Assignee: General Electric Company
    Inventors: Malath Ibrahim Arar, Anna Valeria Anllo
  • Patent number: 8899008
    Abstract: A system includes an anti-icing heat recovery system, which includes a first heat exchanger, a second heat exchanger, and a variable speed fan. The first heat exchanger is configured to receive a working fluid from an exhaust section of a gas turbine engine and to transfer heat from the working fluid to a cooled intermediate heat transfer medium to generate a heated intermediate heat transfer medium. The second heat exchanger is configured to receive the heated intermediate heat transfer medium from the first heat exchanger and to transfer heat from the heated intermediate heat transfer medium to air entering the gas turbine engine. The variable speed fan is configured to urge the working fluid from the exhaust section of the gas turbine engine through the first heat exchanger.
    Type: Grant
    Filed: May 15, 2012
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Douglas Alan Jones, Gerardo Plata Contreras, Robert Allen Baten, Victor Gerardo Cabal Velarde, Jingmei Zhang, Jesus Elios Almendarez Mendez, Richard Michael Watkins
  • Patent number: 8899917
    Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.
    Type: Grant
    Filed: March 26, 2012
    Date of Patent: December 2, 2014
    Assignee: Techspace Aero S.A.
    Inventors: Denis Bajusz, Nicholas Raimarckers, Antoine Stephany, Georges Broers, Yves Culot, Marc Strengnart, Albert Cornet, David Depaepe
  • Publication number: 20140345292
    Abstract: In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.
    Type: Application
    Filed: May 22, 2013
    Publication date: November 27, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Carlos Enrique Diaz, Jorge Alejandro Carretero Benignos
  • Patent number: 8869537
    Abstract: A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavorable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: October 28, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Torsten Geis, Edward Brook
  • Patent number: 8844293
    Abstract: A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated with a generator power conditioning unit as a sole means for providing anti-icing heating to fuel supplied for engine combustion. The method and apparatus permits the heat exchanger to heat the fuel sufficiently so that other dedicated heating means may be unnecessary.
    Type: Grant
    Filed: March 22, 2011
    Date of Patent: September 30, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Ian A. MacFarlane
  • Patent number: 8844258
    Abstract: A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated.
    Type: Grant
    Filed: August 27, 2013
    Date of Patent: September 30, 2014
    Assignee: General Electric Company
    Inventors: Sanji Ekanayake, Alston Ilford Scipio, Dale J. Davis, Ryan Margate Pastrana
  • Publication number: 20140245749
    Abstract: A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The anti-ice valve is opened at startup of the gas turbine engine to assist compressor stability.
    Type: Application
    Filed: December 31, 2012
    Publication date: September 4, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Patent number: 8800258
    Abstract: An air intake structure is mounted upstream of a mid-structure of a nacelle for an aircraft engine. The air intake structure includes an external wall incorporating a lip, a partition defining a deicing compartment in the lip, a deicing manifold extending in the compartment, and a duct for supplying hot air to the deicing manifold. In particular, the external wall is mounted movably with respect to the mid-structure between a rear position and a front position, and the duct is connected in a fixed manner to the mid-structure. The partition is fixed in a sealed manner inside the lip, and the duct is connected to the manifold by a disconnectable seal which is situated in an immediate vicinity of the partition.
    Type: Grant
    Filed: August 28, 2008
    Date of Patent: August 12, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Stephane Beilliard, Jean-Philippe Dauguet
  • Patent number: 8793970
    Abstract: A lip assembly for an air inlet of a turbojet engine nacelle includes an inner surface, an external surface. A portion of the external surface is covered by an ice-repellent coating. In particular, the ice-repellent coating includes a piezoelectric actuator which vibrates the external surface and is combined into a matrix of the ice-repellent coating.
    Type: Grant
    Filed: September 29, 2008
    Date of Patent: August 5, 2014
    Assignee: Aircelle
    Inventor: Thierry Le Docte
  • Patent number: 8783619
    Abstract: An air inlet of an aircraft nacelle includes a pipe, extending over the circumference of the air inlet and defined in the back by a front frame, and an element for the localized injection of hot air into the pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. The inlet includes at least one vortex generator (38) in the pipe (22), the generator being plate-shaped or shaped in a manner projecting from the wall of the pipe (22), in order to disrupt the hot air flow so as to compensate the effect of the centrifugal force and reduce the temperature gradient between the inside and outside of the pipe (22).
    Type: Grant
    Filed: December 14, 2010
    Date of Patent: July 22, 2014
    Assignee: Airbus Operations SAS
    Inventors: Arnaud Hormiere, Alain Dega, Stephane Gaillot
  • Publication number: 20140165531
    Abstract: A rigid electrical raft has electrical conductors embedded in a rigid material. The electrical conductors transmit electrical signals through the rigid electrical raft, which may form part of an electrical system of a gas turbine engine. The rigid electrical raft also has electrical heating elements embedded therein. The electrical heating elements provide heat which may be used, for example, to prevent condensation and/or ice build-up and/or to raise the temperature of electrical components to be within a desired range.
    Type: Application
    Filed: December 9, 2013
    Publication date: June 19, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Paul BROUGHTON, Michael Christopher WILLMOT, Justin Sean DALTON
  • Publication number: 20140144124
    Abstract: Embodiments of the present disclosure are directed towards a system that includes a recirculation system. The recirculation system includes a compressor discharge air line extending from a compressor to an air intake. The compressor discharge air line is configured to flow a compressor discharge air flow, and the air intake is configured to supply an air flow to the compressor. An ejector is disposed along the compressor discharge air line between the compressor and the air intake. The ejector is configured to receive and mix the compressor discharge air flow and a turbine exhaust flow to form a first mixture.
    Type: Application
    Filed: November 26, 2012
    Publication date: May 29, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Indrajit Mazumder, Rajarshi Saha, Seyfettin Can Gulen, Sabarinath Devarajan, Prashant Kumar
  • Patent number: 8721755
    Abstract: An apparatus is provided and includes an inlet, including a peripheral wall formed to define a pathway along which gaseous, fluidic and particulate matter flow and two or more nets sequentially disposed in the pathway, the two or more nets being suspended on the peripheral wall with substantially no clearance between each of the two or more nets and the peripheral wall and held sufficiently loosely to permit relative movement of each of the two or more nets such that an effective pore size of the two or more nets is variable over time to encourage fluidic condensation at the two or more nets and to permit a relatively substantial portion of the gaseous and particulate matter to continue to flow.
    Type: Grant
    Filed: July 2, 2010
    Date of Patent: May 13, 2014
    Assignee: BHA Altair, LLC
    Inventors: Paul Sherwood Bryant, Alan Edwin Baigent, Paul Christopher James Bissett, John Carl Davies, Evdokia Ivanovna Huddlestone, Etienne Rene Jarrier, Ian Hugh Sutherland
  • Publication number: 20140102113
    Abstract: A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into exhaust gases. The anti-icing system is configured to use heat from the exhaust gases to heat a heat transfer fluid (HTF) and to selectively heat the fuel and the air via the HTF.
    Type: Application
    Filed: June 15, 2012
    Publication date: April 17, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jose Antonio Cuevas, James Knox Prochaska
  • Publication number: 20140096503
    Abstract: An apparatus has a first member having an exposed peripheral surface and an electrically and thermally conductive portion. A circumferential array of magnets of alternating polarity are mounted for rotation about an axis relative to the first member inboard of the peripheral surface, the magnets being in sufficient proximity to the electrically and thermally conductive portions so that the rotation of the magnets about the axis is effective to generate eddy currents, in turn, is effective to heat the electrically and thermally conductive portion and, thereby, heat the exposed peripheral surface.
    Type: Application
    Filed: October 5, 2012
    Publication date: April 10, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Lubomir A. Ribarov, Jacek F. Gieras
  • Patent number: 8677764
    Abstract: An aircraft propulsion unit includes a nacelle in which a power plant is arranged. The nacelle includes an inside wall that delimits a pipe with an air intake at the front. The propulsion unit includes a frost treatment system having at least one first pipe equipped with elements for regulating the passing air, for directing the hot air from the power plant to the air intake, and, an exhaust system having at least one second pipe equipped with elements for regulating the passing air, for directing air from the power plant to a delivery zone. The at least one second pipe is connected to the at least one first pipe, and the elements for regulating the air that passes into the at least one first pipe are separate from the elements for regulating the air that passes into the at least one second pipe.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: March 25, 2014
    Assignee: Airbus Operations S.A.S.
    Inventor: Alain Porte
  • Publication number: 20140077039
    Abstract: An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater.
    Type: Application
    Filed: December 28, 2012
    Publication date: March 20, 2014
    Applicant: Aerospace Filtration Systems, Inc.
    Inventor: Aerospace Filtration Systems, Inc.
  • Patent number: 8661783
    Abstract: A heat exchanger is provided for warming fuel prior to introduction of the fuel to an engine, the heat exchanger including: a fuel inlet and a fuel outlet; a heat exchange matrix having heat transfer components past which the fuel flows between said inlet and said outlet and which are arranged to be heated; and swirl inducing means arranged between said inlet and said matrix arranged to cause fuel from said inlet to swirl prior to entering said matrix. By causing the fuel to swirl prior to entering the heat exchange matrix, entrained ice in the fuel can be caused to concentrate at an outer region of the heat exchanger thereby allowing fuel to continue to flow through the heat exchanger to the engine even when ice is present in the fuel.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: March 4, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Peter F W Foster
  • Publication number: 20140041393
    Abstract: An air processing assembly is provided. The assembly includes at least one filter element that includes a filter media having a first end and a second end spaced a predefined distance from the first end. A channel is defined within the filter media, wherein the channel extends from the filter media first end to the filter media second end. The channel defines a flow path for a solid desiccant, wherein air being channeled through the assembly is filtered via the filter media and moisture is substantially removed from the air via the solid desiccant.
    Type: Application
    Filed: August 8, 2012
    Publication date: February 13, 2014
    Inventors: Bhalchandra Arun Desai, Julio Enrique Mestroni, Huong Van Vu
  • Publication number: 20140008497
    Abstract: A system for reducing moisture in a gas turbine engine with one or more air ducts includes one or more one or more covers, each with an outer face and an inner face, with the inner face connectable to the air duct, wherein the cover is shaped to engage and close the air duct and a desiccant that is attachable to the cover.
    Type: Application
    Filed: July 9, 2012
    Publication date: January 9, 2014
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Eric J. Alexander, Anthony C. Jones
  • Publication number: 20130340439
    Abstract: A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated.
    Type: Application
    Filed: August 27, 2013
    Publication date: December 26, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Sanji Ekanayake, Alston Ilford Scipio, Dale J. Davis, Ryan Margate Pastrana
  • Publication number: 20130327012
    Abstract: Embodiments of the present disclosure are directed towards a system having a compressor bleed air recirculation system. The compressor bleed air recirculation system includes a compressor bleed air line extending from a compressor to an air intake, wherein the compressor bleed air line is configured to flow a compressor bleed air flow, and the air intake is configured to supply an air flow to the compressor. The compressor bleed air recirculation system further includes an eductor disposed along the compressor bleed air line between the compressor and the air intake, wherein the eductor is configured to receive and mix the compressor bleed air flow and a first ambient air flow to form a first air mixture.
    Type: Application
    Filed: June 11, 2012
    Publication date: December 12, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Mohammad Mahabub, Imran A. Khan, Tho Vankhanh Nguyen
  • Patent number: 8590309
    Abstract: According to one aspect of the invention, an ice separating apparatus for a gas turbine engine includes a can having a first end and a tangential inlet proximate the first end of the can to receive a fluid flow within the can, wherein the fluid flow includes fuel and ice. The apparatus also includes a first conduit within the can to receive a separated fuel flow proximate a second end of the can, wherein the fluid flow separates ice from fuel to form the separated fuel flow.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: November 26, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Bruce Paradise
  • Publication number: 20130305737
    Abstract: A system includes an anti-icing heat recovery system, which includes a first heat exchanger, a second heat exchanger, and a variable speed fan. The first heat exchanger is configured to receive a working fluid from an exhaust section of a gas turbine engine and to transfer heat from the working fluid to a cooled intermediate heat transfer medium to generate a heated intermediate heat transfer medium. The second heat exchanger is configured to receive the heated intermediate heat transfer medium from the first heat exchanger and to transfer heat from the heated intermediate heat transfer medium to air entering the gas turbine engine. The variable speed fan is configured to urge the working fluid from the exhaust section of the gas turbine engine through the first heat exchanger.
    Type: Application
    Filed: May 15, 2012
    Publication date: November 21, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Douglas Alan Jones, Gerardo Plata Contreras, Robert Allen Baten, Victor Gerardo Cabal Velarde, Jingmei Zhang, Jesus Elios Almendarez Mendez, Richard Michael Watkins
  • Patent number: 8549832
    Abstract: An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.
    Type: Grant
    Filed: December 30, 2009
    Date of Patent: October 8, 2013
    Assignee: MRA Systems Inc.
    Inventor: Mahendra Maheshwari
  • Publication number: 20130247541
    Abstract: The gas turbine intake anti-icing device is used for a gas turbine electric power generation system (1) having a gas turbine (2) and a power generator (20) coupled to the gas turbine (2) and rotationally driven to generate electrical power. The gas turbine intake anti-icing device includes a power generator cooling mechanism (21, 22, 23, 25), which takes air from the outside and introduces air into the power generator (20) to cool the power generator (20), and exhaust air supply path (31) that connects intake path (9) of the gas turbine (2) to exhaust path (30) for air that is discharged from power generator cooling mechanism (21, 22, 23, 25) after the power generator (20) is cooled. The air discharged from the power generator cooling mechanism (21, 22, 23, 25) is supplied to the intake path (9) of the gas turbine (2) through the exhaust air supply path (31).
    Type: Application
    Filed: December 10, 2012
    Publication date: September 26, 2013
    Applicant: MITSUI ENGINEERING & SHIPBUILDING CO., LTD.
    Inventor: MITSUI ENGINEERING & SHIPBUILDING CO., LTD.
  • Publication number: 20130239542
    Abstract: A turbine engine has a fan comprising a duct and supporting struts, a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. A cooling circuit is located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, and includes at least intercooler configured to transfer heat from inlet air to a secondary fluid heat sink.
    Type: Application
    Filed: March 16, 2012
    Publication date: September 19, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Arindam Dasgupta, Om P. Sharma
  • Patent number: 8522522
    Abstract: A power generator, such as a permanent magnet alternator (“PMA”) or a permanent magnet generator (“PMG”), may be used to provide electric power to a deicing system, for example. The power generator is embedded within a spinner, and may be in communication with a locally mounted electronic control unit (“ECU”).
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: September 3, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Richard A. Poisson
  • Publication number: 20130219916
    Abstract: According to one aspect of the invention, a method for conditioning air received by a power generation system includes flowing ventilation air through a turbine system to control a temperature of the turbine system and receiving the ventilation air from the turbine system and mixing the ventilation with an ambient air to form an intake air to be directed to a compressor, wherein a temperature of the ventilation air is greater than the ambient air.
    Type: Application
    Filed: February 24, 2012
    Publication date: August 29, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Bhachandra Arun Desai, Huong Van Vu
  • Patent number: 8505273
    Abstract: An ice and/or frost preventing system for positioning in an airflow tunnel having an air inlet includes a plurality of waveguide passages positioned in the airflow tunnel; an air filter positioned in each waveguide passage; a microwave energy source coupled to each waveguide passage; a first screen positioned in the airflow tunnel upstream of the plurality of waveguide passages; and a second screen positioned in the airflow tunnel downstream of the plurality of waveguide passages. The microwave energy sources and the first and second screens create a guided, standing wave, microwave energy that substantially prevents at least one of ice and frost from forming on the air filters. A turbine system including the ice and/or frost preventing system is also described.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: August 13, 2013
    Assignee: General Electric Company
    Inventors: Hua Zhang, Jianmin Zhang
  • Patent number: 8499540
    Abstract: A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.
    Type: Grant
    Filed: March 19, 2008
    Date of Patent: August 6, 2013
    Assignee: Turbomeca
    Inventors: Edgar Haehner, Eric Royer