Did You Know...
...that it was melting ice cream that inspired the invention of the outboard motor? It was a lovely August day and Ole Evinrude was rowing his boat to his favorite island picnic spot. As he rowed, he watched his ice cream melt and wished he had a faster way to get to the island. At that moment the idea for the outboard motor was born!
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| Number | Title | Issue Date |
| 8141335 | Intake air heating control device for gas turbine Extremely cold (e.g., −20° C.) air A is heated by a heat exchanger 30, which is supplied with steam S via a control valve 32, and heated air A′ is taken into a gas turbine 10. The valve opening degree of the control valve 32 is feedb... | 03/27/2012 |
| 8015789 | Anti-icing apparatus and method for aero-engine nose cone 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 engin... | 09/13/2011 |
| 8015788 | Heat transfer system for turbine engine using heat pipes A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling. The heat transfer system includes at least one heat pipe disposed in contact with an interior of the casing. The heat pipe is thermally coupled to a heat source, ... | 09/13/2011 |
| 8011172 | Engine arrangement 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... | 09/06/2011 |
| 7941993 | Engine cooling Cavities 4 are defined within an engine nacelle 1 with an inner surface 2 and an outer surface 3. Within these cavities 4, an evaporatable liquid 5 is arranged such that a proportion of the liquid 5 is in a gaseous ph... | 05/17/2011 |
| 7921632 | Device for protection against icing for aircraft engines and related de-icing method A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined thre... | 04/12/2011 |
| 7874137 | Gas turbine engine anti-ice formation device and system 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 fr... | 01/25/2011 |
| 7823374 | Heat transfer system and method for turbine engine using heat pipes A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling. The heat transfer system includes at least one heat pipe disposed in contact with an interior of the casing. The heat pipe is thermally coupled to a heat source, ... | 11/02/2010 |
| 7762054 | Thermally powered turbine inlet air chiller heater An addition to the air compressor of a combustion turbine system is disclosed, which chills the inlet air on warm days. The same equipment with minimal modification is used to prevent inlet air icing conditions on cold days. Referring to FIG. 1, inlet air con... | 07/27/2010 |
| 7581378 | Anti-icing apparatus and method for aero-engine nose cone 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 engin... | 09/01/2009 |
| 7398641 | Aeroengine intake having a heat exchanger within an annular closed chamber 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 op... | 07/15/2008 |
| 7334411 | Gas turbine heat exchanger assembly and method for fabricating same A method for assembling a gas turbine engine includes fabricating a heat exchanger that includes a first manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the manifold inlet, a second quantity o... | 02/26/2008 |
| 7331421 | Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods Flow restrictors for aircraft inlet acoustic cores, and associated systems and methods are disclosed. A system in accordance with one embodiment of the invention includes an inlet flow surface having multiple openings, and an acoustic treatment positioned adjacent t... | 02/19/2008 |
| 7328623 | Temperature and/or pressure sensor assembly A sensor assembly includes a housing and a tube. The housing has a first leading edge portion which is capable of being located in a compressor/fan inlet flow path and which includes an interior wall section. The tube has a proximal portion including an air inlet wh... | 02/12/2008 |
| 7246480 | System for heating an air intake of turbine engine 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... | 07/24/2007 |
| 7188464 | Methods for operating gas turbine engines 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... | 03/13/2007 |
| 7137240 | Inlet muff anti-icing system for an auxiliary power unit 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... | 11/21/2006 |
| 7131612 | Nacelle inlet lip anti-icing with engine oil 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 s... | 11/07/2006 |
| 7131815 | Inlet guide vane 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 com... | 11/07/2006 |
| 7055304 | De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes 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 fixe... | 06/06/2006 |
| 6990797 | Methods and apparatus for operating gas turbine engines 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 couple... | 01/31/2006 |
| 6920748 | Methods and apparatus for operating gas turbine engines 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... | 07/26/2005 |
| 6921244 | Bleed valve system Disclosed is a system for operating gas turbine engine bleed valves in response to pressure values within the engine, wherein the engine pressure values are sensed electronically and routed to a programmable logic device, and wherein the programmable logic device co... | 07/26/2005 |
| 6848656 | Ice protection system 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... | 02/01/2005 |
| 6702233 | Airfoil anti-icing assembly and method 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 inl... | 03/09/2004 |
| 6688558 | Method and apparatus for aircraft inlet ice protection 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... | 02/10/2004 |
| 6666026 | Process for preheating suction air by waste heat in power engines 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... | 12/23/2003 |
| 6584777 | Apparatus for and method of filtering a fluid 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 elec... | 07/01/2003 |
| 6561760 | Booster compressor deicer 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... | 05/13/2003 |
| 6457676 | Method and apparatus for aircraft inlet ice protection 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 acoust... | 10/01/2002 |
| 6442944 | Bleed air heat exchanger integral to a jet engine 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 ... | 09/03/2002 |
| 6443395 | Air inlet cowl for a jet engine equipped with de-icing means 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, previous... | 09/03/2002 |
| 6427434 | Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit 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... | 08/06/2002 |
| 6371411 | Method and apparatus for aircraft inlet ice protection 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 acousti... | 04/16/2002 |
| 6354538 | Passive control of hot air injection for swirling rotational type anti-icing system 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 cau... | 03/12/2002 |
| 6233917 | Method of controlling the temperature of intake air, temperature-control device for carrying out the method and gas turbine having the temperature-control device 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 ... | 05/22/2001 |
| 6134874 | Integral inertial particle separator for radial inlet gas turbine engine An integral inertial particle separator with a de-icing feature in the form of a bifurcated radial intake for a gas turbine engine with an outside wall of the radial intake disposed in contact with heated oil from the engine lubrication system. To dischar... | 10/24/2000 |
| 6079670 | Hot air diffuser for a jet engine air inlet cowl with de-icing circuit The present invention relates to an air inlet cowl (9) for a jet engine, especially for an aircraft. According to the invention, the diffuser (12) of hot air for de-icing, arranged in the hollow leading edge (16) of the cowl (9) is in the form of a polygo... | 06/27/2000 |
| 5944287 | Ice protection for porous structure A nacelle having a porous structure is provided with laminar flow control and contamination protection. In region B suction through a composite layer is achieved by evacuating a chamber adjacent the inner surface of the nacelle to provide laminar flow con... | 08/31/1999 |
| 5930990 | Method and apparatus for achieving power augmentation in gas turbines via wet compression A wet compression power augmentation apparatus and method for effectively adding a mass flow of nebulized water to a gas turbine by use of a spray rack group assembly having at least one spray rack water pipe and at least one spray rack water nozzle. Nebu... | 08/03/1999 |
