Ice Preventer Or De-icer Patents (Class 60/39.093)
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Patent number: 7581378Abstract: An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).Type: GrantFiled: July 28, 2006Date of Patent: September 1, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Joseph Horace Brand, Michael John Dowhan
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Publication number: 20090199535Abstract: An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).Type: ApplicationFiled: April 24, 2009Publication date: August 13, 2009Inventors: Joseph Horace Brand, Michael John Dowhan
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Publication number: 20090120099Abstract: An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).Type: ApplicationFiled: July 28, 2006Publication date: May 14, 2009Inventors: Joseph Horace Brand, Michael John Dowhan
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Publication number: 20090060707Abstract: A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice on gas turbine engine compressor inlet guide vanes after the ice has been removed. A determination is made as to whether actual inlet guide vane position differs from the commanded inlet guide vane position by a predetermined amount. If so, then the inlet guide vanes are repeatedly commanded to move in at least two predetermined directions to remove ice that may have formed on the inlet guide vanes.Type: ApplicationFiled: July 25, 2007Publication date: March 5, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventor: Darrell R. Williams
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Publication number: 20090020647Abstract: According to the invention, a scaled articulation device (27) is mounted on at least one (14) of the branches (14; 18, 9) of said hot-air circulation circuit in the form of a bracket so as to provide said bracket with capabilities of deforming about said articulation device (27).Type: ApplicationFiled: March 22, 2007Publication date: January 22, 2009Applicant: AIRBUS FRANCEInventor: Alain Porte
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Publication number: 20080307769Abstract: An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured to selectively receive a flow of compressed air that is discharged from the compressor. Because the compressed air is relatively hot, the anti-ice formation device temperature increases to a temperature sufficient to prevent ice accumulation and formation in the engine inlet duct. The anti-ice formation device is also configured such that heat is not transferred to the compressor inlet housing. As a result, the anti-ice formation device does not cause impeller clearance variations, which would adversely affect engine performance.Type: ApplicationFiled: June 18, 2007Publication date: December 18, 2008Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Tina H. Chaney, Dave G. Dischinger, Alan G. Tiltman, Dwight D. Vettel
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Patent number: 7465150Abstract: Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthemore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade.Type: GrantFiled: June 30, 2006Date of Patent: December 16, 2008Assignee: Siemens AktiengesellachaftInventor: Fathi Ahmad
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Publication number: 20080302081Abstract: A method of detecting an ice shedding event in a gas turbine engine, the engine having a rotor comprising a compressor drivingly connected via a shaft to a turbine; the method for detecting an ice shedding event comprising the steps of measuring the temperature at regular intervals and where a temperature drop of at least 20 degrees per second is recorded, producing a signal indicative of an ice shedding event and sending the signal to an indicator device. Advantageously, the engine may then be inspected for damage associated to an ice impact rather than other foreign object ingestion event or fuel flow irregularity. Alternatively, instead of temperature, pressure may be measured and a pressure drop of at least 20 kPa per second is indicative of an ice shedding event.Type: ApplicationFiled: February 11, 2008Publication date: December 11, 2008Applicant: ROLLS-ROYCE PLCInventors: Robert J. Snell, Steven M. Anthony, Stefania Mandirola, Arthur L. Rowe
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Publication number: 20080279688Abstract: A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.Type: ApplicationFiled: August 13, 2007Publication date: November 13, 2008Inventors: JOSEPH M. JENSEN, James D. Bolla, Joseph T. Humphrey, Steve H. Nguyen
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Publication number: 20080190093Abstract: The turbojet has a bearing which supports, in rotation and in thrust, a low-pressure compressor shaft of axis Z-Z of the engine. The bearing is lubricated with oil by means of two nozzles. A feed tube is fastened to the nose cone of the engine. This tube connects the low-pressure compressor shaft to the engine nose cone. A skin lines the wall of the engine nose cone, leaving a passage for the circulation of oil. A plurality of radial oil return tubes are placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing. The return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.Type: ApplicationFiled: February 11, 2008Publication date: August 14, 2008Applicant: SNECMAInventors: Gerard Philippe GAUTHIER, Laurent Gille, Serge Rene Morreal, Jean-Yves Picart
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Patent number: 7398641Abstract: A gas turbine engine comprising a nacelle having an intake, the intake defining a generally annular chamber, an engine accessory and a heat exchanger for cooling a fluid of the accessory. The chamber is closed and the heat exchanger is disposed within the chamber operable to provide heat to prevent ice forming on the intake during engine operation.Type: GrantFiled: May 4, 2004Date of Patent: July 15, 2008Assignee: Rolls-Royce plcInventors: Richard G Stretton, Peter Beardsley
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Publication number: 20080092516Abstract: An engine arrangement for a component subject to icing. The arrangement comprising a manifold as part of a flow path incident upon a heated component. The manifold including holes to create jets having an exit angle toward the component subject to icing. The jets of hot gas are entrained in a core flow passing through the main flow path before washing over a desired incident area of the component. The exit angle and spacing between the jet and the component are determined to reduce disruption of the core flow and/or provide the desired incident area on the component and/or use the minimum amount of hot air.Type: ApplicationFiled: October 10, 2007Publication date: April 24, 2008Applicant: ROLLS-ROYCE PLCInventor: CLIVE LOCKWOOD
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Publication number: 20080022682Abstract: A energy recovery system for an internal combustion engine which dynamically allocates heat energy to multiple vehicle accessory systemsType: ApplicationFiled: September 7, 2007Publication date: January 31, 2008Inventor: Triantafyllos Tafas
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Publication number: 20070234704Abstract: A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method includes coupling a manifold to the gas turbine engine such that the manifold is coupled in thermal communication with a heat source, coupling a first heat pipe to the manifold such that the first heat pipe partially circumscribes the gas turbine engine in a clockwise orientation, and coupling a second heat pipe to the manifold such that the second heat pipe partially circumscribes the gas turbine engine in a counter-clockwise orientation.Type: ApplicationFiled: September 1, 2005Publication date: October 11, 2007Inventors: Thomas Moniz, Kattlaicheri Venkataramani, Justin Stephenson, Erich Krammer, William Gerstler
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Publication number: 20070220899Abstract: The invention relates to a system (2) for deicing an aircraft turbine engine inlet cone (4) comprising air-diffusing means (18) intended to equip the inlet cone of the turbine engine so as to deliver hot air thereto. According to the invention, it also comprises a circuit (20) for removing pressurizing air from at least one bearing enclosure of the turbine engine, this circuit communicating with the air-diffusing means in order to be able to supply the latter with hot air.Type: ApplicationFiled: March 21, 2007Publication date: September 27, 2007Applicant: SNECMAInventors: Julien Roland EARITH THOMAS, Picart Jean-Yves
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Patent number: 7246480Abstract: A heating system for a turbine engine air intake region for preventing the formation of ice on the air intake region, which may be formed from the bell-mouth, one or more vanes, such as inlet guide vanes, a turbine blade assembly formed from one or more blades, such as the first row of rotating blades, and related components. A heat source may be attached to the inlet manifold and positioned to emit thermal radiation toward the air intake region to prevent the formation of ice thereon.Type: GrantFiled: November 4, 2004Date of Patent: July 24, 2007Assignee: Siemens Power Generation, Inc.Inventor: Paul David Ritland
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Patent number: 7188464Abstract: A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine. The method comprises coupling a semi-permeable membrane to the engine adjacent an outer surface of the engine, coupling a fluid reservoir to the aircraft engine in flow communication with the semi-permeable membrane, and supplying fluid from the fluid reservoir to the semi-permeable membrane to facilitate preventing ice accumulation on the aircraft engine outer surface.Type: GrantFiled: March 4, 2005Date of Patent: March 13, 2007Assignee: General Electric CompanyInventors: John Frederick Ackerman, William Kent Wagner
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Patent number: 7137240Abstract: An auxiliary power unit (APU) inlet muff anti-icing system that uses high pressure, high temperature APU compressor delivery air to melt any accumulation of ice and snow near the bottom of the muff with a tracer line coupled to a perforated gull wing fairing mounted within the inlet muff and that uses the compressor delivery air as the primary stream for an ejector to suck ice and snow melt accumulating near the fairing overboard.Type: GrantFiled: August 18, 2004Date of Patent: November 21, 2006Assignee: Hamilton Sundstrand CorporationInventor: Robert G. Thompson
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Patent number: 7131612Abstract: A nacelle for housing a gas turbine engine having a pressurized oil system for lubricating components thereof comprises an inlet lip defining a leading edge of the nacelle, the inlet lip having a conduit therein in fluid flow communication with the pressurized oil system of the gas turbine engine and defining an oil passage for circulation of pressurized engine oil therethrough. The conduit is in heat transfer communication with an outer surface of the inlet lip.Type: GrantFiled: July 29, 2003Date of Patent: November 7, 2006Assignee: Pratt & Whitney Canada Corp.Inventors: Praba Kharan Baptist, Keppel Nyron Bharath
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Patent number: 7131815Abstract: A vane provided with at least one spindle, the at least one spindle configured to engage in operation with a support such that in operation the vane pivots about the at least one spindle. The vane is further provided with an electrically operable heater which is communicable with an electrical supply via an electrical connection node located in the at least one spindle. The electrical connection node comprises a female portion and a corresponding male portion. The support is defined by a casing.Type: GrantFiled: June 28, 2004Date of Patent: November 7, 2006Assignee: Rolls-Royce PLCInventors: Peter Allford, Gary Olds
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Patent number: 7055304Abstract: The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16). The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device. The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.Type: GrantFiled: July 6, 2004Date of Patent: June 6, 2006Assignee: SNECMA MoteursInventors: Yannick Jean Roger Courtot, Francois Marie Paul Marlin, Jean Armand Francois Danielo
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Publication number: 20060101802Abstract: The invention relates to an air intake appliance for an aircraft engine. At least one channel wall (1) of the air intake appliance (20) is provided on at least a part of its inner surface with several essentially parallel ducts (2) arranged side by side for conducting hot gas along said inner surface of the channel wall in order to transfer heat from the hot gas to the channel wall and thereby prevent formation of ice on the outer surface (1a) thereof. Said ducts comprise alternately arranged inflow ducts (2a) and outflow ducts (2b). Distribution means (10, 24) are provided for distributing hot gas to the inflow ducts (2a), and the inflow ducts (2a) are so connected to the outflow ducts (2b) that the hot gas from the distribution means (10, 24) will first flow through an inflow duct (2a) and thereafter through an outflow duct (2b). The invention also relates to an aircraft engine provided with such an air intake appliance.Type: ApplicationFiled: November 7, 2005Publication date: May 18, 2006Applicant: SAAB ABInventors: Ellstrom Hans, Mats Bergman
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Publication number: 20060090472Abstract: A heating system for a turbine engine air intake region for preventing the formation of ice on the air intake region, which may be formed from the bell-mouth, one or more vanes, such as inlet guide vanes, a turbine blade assembly formed from one or more blades, such as the first row of rotating blades, and related components. A heat source may be attached to the inlet manifold and positioned to emit thermal radiation toward the air intake region to prevent the formation of ice thereon.Type: ApplicationFiled: November 4, 2004Publication date: May 4, 2006Inventor: Paul Ritland
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Publication number: 20060037303Abstract: An auxiliary power unit (APU) inlet muff anti-icing system that uses high pressure, high temperature APU compressor delivery air to melt any accumulation of ice and snow near the bottom of the muff with a tracer line coupled to a perforated gull wing fairing mounted within the inlet muff and that uses the compressor delivery air as the primary stream for an ejector to suck ice and snow melt accumulating near the fairing overboard.Type: ApplicationFiled: August 18, 2004Publication date: February 23, 2006Inventor: Robert Thompson
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Patent number: 6990797Abstract: A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.Type: GrantFiled: September 5, 2003Date of Patent: January 31, 2006Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee
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Patent number: 6920748Abstract: A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine. The method comprises coupling a semi-permeable membrane to the engine adjacent an outer surface of the engine, coupling a fluid reservoir to the aircraft engine in flow communication with the semi-permeable membrane, and supplying fluid from the fluid reservoir to the semi-permeable membrane to facilitate preventing ice accumulation on the aircraft engine outer surface.Type: GrantFiled: July 3, 2002Date of Patent: July 26, 2005Assignee: General Electric CompanyInventors: John Frederick Ackerman, William Kent Wagner
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Publication number: 20050109011Abstract: The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16). The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device. The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.Type: ApplicationFiled: July 6, 2004Publication date: May 26, 2005Applicant: SNECMA MOTEURSInventors: Yannick Courtot, Francois Marlin, Jean Danielo
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Publication number: 20050050877Abstract: A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.Type: ApplicationFiled: September 5, 2003Publication date: March 10, 2005Inventors: Kattalaicheri Venkataramani, Lawrence Butler, Ching-Pang Lee
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Publication number: 20050039435Abstract: A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine.Type: ApplicationFiled: July 3, 2002Publication date: February 24, 2005Inventors: John Ackerman, William Wagner
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Patent number: 6848656Abstract: An aircraft engine nacelle nose cowl has a supply duct to deliver pressurised hot gas into an internal compartment of the nose cowl. A slot is provided in the nose cowl to enable pressurised hot gas to pass out of the compartment through the slot. As the pressurised hot gas passes out of the compartment through the slot, this causes a film of water on an outer surface of the nose cowl to detach from the nose cowl. The slot is of restricted dimensions which causes localised heating of the nose cowl around the slot as the pressurised hot gas pass out of the compartment through the slot. In this manner ice is prevented from accumulating on the outer surface of the nose cowl and/or ice is removed from the outer surface of the nose cowl.Type: GrantFiled: May 20, 2003Date of Patent: February 1, 2005Assignee: Short Brothers PLCInventor: Alan Linton
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Publication number: 20040065092Abstract: A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region, associated with a booster compressor of the turbofan engine, is identified. The splitter region has surfaces internal to the turbofan engine subject to inlet icing conditions. A resin is molded along a leading edge of the splitter region, and electric coils are installed within the resin to prevent ice build-up on the splitter region or to remove ice from the splitter region during icing conditions.Type: ApplicationFiled: October 3, 2002Publication date: April 8, 2004Applicant: General Electric CompanyInventors: Aspi R. Wadia, Raymond G. Holm
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Patent number: 6702233Abstract: An anti-icing assembly for an airfoil such as an aircraft wing or slat comprises: (a) an airfoil having an exterior surface and interior wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity; (b) an inlet plenum integral to the airfoil, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the airfoil interior cavity and (ii) a throat section interfacing the inlet plenum and airfoil interior cavity; and (c) an outlet plenum integral to the airfoil, wherein the outlet plenum comprises an outlet baffle capable of directing hot gases from the airfoil interior cavity. The airfoil anti-icing method of this invention comprises providing hot gases such as jet engine bleed air to the airfoil assembly of this invention, swirling the hot gases within the airfoil interior cavity, and discharging the hot gases from the airfoil interior cavity through the airfoil outlet end.Type: GrantFiled: February 7, 2001Date of Patent: March 9, 2004Assignee: Rohr, Inc.Inventor: Henry Morgan DuPont
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Patent number: 6688558Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes a tapered acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: May 29, 2002Date of Patent: February 10, 2004Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
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Publication number: 20040006966Abstract: Air intake temperature in a gas turbine is regulated by a heat exchange fluid having a low viscosity at low temperatures. The circulated heat transfer fluid preferably comprises an alkali metal formate, most preferably potassium formate. The potassium formate may be blended with other alkali metal formate(s), with alcohol, glycols, salt brines, or any combination of glycols, alcohols, Sodium Nitrite, Sodium Nitrates, Potassium Chloride, Sodium Chloride, water and/or or other salt brines.Type: ApplicationFiled: April 16, 2003Publication date: January 15, 2004Applicant: Clearwater InternationalInventors: John Henry Hallman, William J. Hyland, Ray Veldman, Jeff Diaz, William Larry Lewis
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Patent number: 6666026Abstract: The present invention proposes a process and a device which permit to improve the efficiency of energetic gas turbines operating in user regions with outside temperatures from −5° C. to +5° C. Unlike in the state of the art, no heat is withdrawn in this connection from the gas compressor (3) when the heat requirement rises in the overall intake system, but successively by using first the off-air heated by the generator (2) for heating the intake air in the intake duct (12, 12′) and subsequently withdrawing additional heat in the form of the heat of an off-heat system (8) generated at the end of the heat circulation. When additional heat is required, heat can be withdrawn from the compressor (3) via a bypass conduit (20).Type: GrantFiled: January 26, 1999Date of Patent: December 23, 2003Assignee: Energieversorgung Halle GmbHInventors: Wolfgang Jungsch, Ralf Weber
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Patent number: 6584777Abstract: A fuel system (10) comprises a tank (12), a pump (14), heat exchangers (16 & 18) and a filter (20) in series fluid flow relationship. A fuel metering unit (24) returns a proportion of the filtered fuel to the tank (12) and is controlled by the engine electronic control (30). The system (10) operates so that fluid is not returned to the tank (12) when a pressure differential of the order of 5 psi is detected across the fluid filter (20) and the temperature of the fluid is below 0° C. The fluid is not returned to the tank (12) for a period of time to reduce the flow of fluid passing through the heat exchangers (16 & 18). The reduced flow of fluid passing through the heat exchangers (16 & 18) is heated to a temperature sufficient to melt any solidified impurities blocking the fluid filter (20).Type: GrantFiled: June 13, 2000Date of Patent: July 1, 2003Assignee: Rolls-Royce PLCInventor: Andrew Clarke
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Patent number: 6561760Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.Type: GrantFiled: August 17, 2001Date of Patent: May 13, 2003Assignee: General Electric CompanyInventors: Aspi Rustom Wadia, Kenneth Edward Seitzer, Harjit Singh Hura, Frank Worthoff, Raymond Gust Holm, Eric Pierre Masse, Jason Corey Slagle
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Patent number: 6457676Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes an acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: October 2, 2001Date of Patent: October 1, 2002Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
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Patent number: 6442944Abstract: An apparatus for supplying hot bleed air for anti-icing of a jet engine and cooled bleed air to an environmental control system includes a first duct (17), a second duct (5) and a front frame (10) coupled to the front of a jet engine (23). The first duct (17) is positioned to route hot bleed air from the jet engine (23) to the front frame (10). The second duct (5) is positioned to receive cooled bleed air from the front frame (10) for routing to an environment control system of an aircraft. Regulating/shutoff valves (15) are connected in the first duct (17) to control the flow of the bleed air in accordance with conventional control techniques. The apparatus further includes an aerodynamic vane (3) to support the second duct (5).Type: GrantFiled: October 26, 2000Date of Patent: September 3, 2002Assignee: Lockheet Martin CorporationInventor: Anthony I. Skur, III
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Patent number: 6443395Abstract: Air inlet cowl for a jet engine equipped with deicing means. According to the invention, the hollow leading edge (16) of said cowl (9) comprises a mixer (19) for forming, at each moment, a mixture of the stream of hot air (20) being injected and some, previously injected, of the stream of air that is recirculating. This evens out the temperature inside said leading edge (16), eliminating hot spots and optimizing the de-icing.Type: GrantFiled: August 9, 2001Date of Patent: September 3, 2002Assignee: Airbus FranceInventors: Alain Porte, Stéphane Viala, Olivier Barbara
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Patent number: 6427434Abstract: A device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. The air inlet cowl for a jet engine, the leading edge of which is hollow and swept with a flow of deicing hot air, includes orifices for discharging the hot air flow to the outside of the leading edge, which form an arrangement such that at least two pressurized hot air jets passing through two adjacent orifices have, downstream of a calibration piece in which the orifices are made, different inclinations with respect to the calibration piece.Type: GrantFiled: December 20, 2000Date of Patent: August 6, 2002Assignee: Aerospatiale Matra AirbusInventors: Alain Porte, Stéphane Viala
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Patent number: 6371411Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes an acoustic liner positioned forward of the inlet throat and has a perforated face sheet a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: November 23, 1999Date of Patent: April 16, 2002Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
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Patent number: 6354538Abstract: An improved anti-icing system for a nose cowl of an aircraft jet engine. An improved injection nozzle is provided to passively enhance the injection of hot, pressure gas from the engine into the ambient air within the nose cowl to entrain such air and cause the entrained mass to rotate within the nose cowl in swirling rotational motion and thereby cause the temperature of the skin of the nose cowl to rise sufficiently to preclude the formation of ice thereon during flight. A plurality of spaced circumferentially arranged tab members, that are preferably triangularly shaped, are canted inwardly slightly to create large scale longitudinal vortices and transverse stirring during the introduction of hot gas and thereby enhance its mixture with the ambient air within the nose cowl and thereby preclude any tendency for the formation of an area of elevated temperature in the skin of the nose cowl downstream of the position of the injection nozzle under certain severe design conditions.Type: GrantFiled: October 25, 1999Date of Patent: March 12, 2002Assignee: Rohr, Inc.Inventor: Radhakrishna Chilukuri
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Publication number: 20010003897Abstract: Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit.Type: ApplicationFiled: December 20, 2000Publication date: June 21, 2001Inventors: Alain Porte, Stephane Viala
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Patent number: 6233917Abstract: A method of controlling the temperature of intake air provided from outside air passing through an air-feed system only utilizes an especially low heating of the intake air while at the same time safely avoiding the formation of ice in the intake air, in order to avoid efficiency losses. A temperature setpoint formed by the sum of the dew point of the outside air and an additive margin of safety is preselected for the intake air. A temperature setpoint of not more than the sum of 0° C. and the margin of safety is advantageously preselected. A temperature-control device for carrying out the method and a gas turbine having the temperature-control device are also provided.Type: GrantFiled: April 8, 1999Date of Patent: May 22, 2001Assignee: Siemens AktiengesellschaftInventors: Siegfried Bähr, Thomas Pfuff