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1712results about "De-icing equipments" patented technology
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Surface topographies for non-toxic bioadhesion control
Owner:UNIV OF FLORIDA RES FOUNDATION INC
Surface topographies for non-toxic bioadhesion control
An article has a surface topography for resisting bioadhesion of organisms and includes a base article having a surface. A composition of the surface includes a polymer. The surface has a topography comprising a pattern defined by a plurality of spaced apart features attached to or projected into the base article. The plurality of features each have at least one microscale dimension and at least one neighboring feature having a substantially different geometry. An average feature spacing between adjacent ones of the features is between 10 μm and 100 μm in at least a portion of the surface. The surface topography can be numerically represented using at least one sinusoidal function. In one embodiment, the surface can comprise a coating layer disposed on the base article.
Owner:UNIV OF FLORIDA RES FOUNDATION INC
Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein
An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.
Owner:THE BF GOODRICH CO +1
Liquid-Impregnated Surfaces, Methods of Making, and Devices Incorporating the Same
InactiveUS20130032316A1Improve skidReduce resistanceFouling preventionDe-icing equipmentsNon wettingFrost
The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.
Owner:MASSACHUSETTS INST OF TECH
Cnt-based resistive heating for deicing composite structures
ActiveUS20110024409A1Prevent freezingInhibition formationMaterial nanotechnologyLayered productsFiberCarbon nanotube
A composite structure includes a matrix material and a carbon nanotube (CNT)-infused fiber material that includes a plurality of carbon nanotubes (CNTs) infused to a fiber material. The CNT-infused fiber material is disposed throughout a portion of the matrix material. The composite structure is adapted for application of a current through the CNT-infused fiber material to provide heating of the composite structure. A heating element includes a CNT-infused fiber material includes a plurality of CNTs infused to a fiber material. The CNT-infused fiber material is of sufficient proportions to provide heating to a structure in need thereof.
Owner:APPL NANOSTRUCTURED SOLUTIONS LLC
Device for heating an aerofoil
InactiveUS6031214AImprove the immunityLimit heating deficitHeater elementsDe-icing equipmentsFiberLeading edge
The heating device comprises electrically conducting longitudinal fibers extending substantially parallel to a leading edge of the aerofoil close to said leading edge, and means for electrically connecting the ends of the longitudinal conducting fibers to an electric power supply. The conducting fibers are grouped together in conducting rovings forming part of a hybrid fabric which furthermore includes a weft of electrically insulating fibers woven together and woven with the conducting rovings.
Owner:EUROCOPTER
Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip
InactiveUS20050006529A1Avoid temperatureCost penaltyDe-icing equipmentsFuselage insulationNacelleAcoustic noise reduction
An aircraft engine nacelle comprises: (a) an inlet lip and a skin having internal and external surfaces; (b) a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; and (c) an electrically powered de-icing system located on the external surface of the nacelle skin and in electrical connection to a power source. A method for de-icing and abating noise from an aircraft nacelle comprises: (a) providing a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; (b) providing an electrically powered de-icing system on the external surface of the nacelle skin; and (c) applying an electric current to the electrically powered de-icing system. The nacelle skin may be a perforated skin, and the de-icing system comprises a wire mesh bonded to the external surface of the perforated skin. The method and nacelle permit the use of noise abatement structures such as acoustic panels for noise reduction while advantageously avoiding detrimental high temperatures associated with conventional de-icing systems.
Owner:ROHR INC
Liquid-impregnated surfaces, methods of making, and devices incorporating the same
ActiveUS8574704B2Reduce viscous dragMinimizes accumulationLayered productsDe-icing equipmentsNon wettingFrost
The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.
Owner:MASSACHUSETTS INST OF TECH
Anti-icing system for wind turbines
InactiveUS20050242233A1Lower Level RequirementsAvoid and reduce accretionPump componentsEngine fuctionsNacelleEngineering
A de-icing and anti-icing arrangement for a Wind Energy Converting System (WECS), a WECS comprising a de-icing and anti-icing arrangement and a method for preventing and eliminating ice accretion on the rotor blades of a WECS are provided. The WECS comprises a tower, a rotor having a plurality of blades that rotate due to wind force, a nacelle including a first means for transforming the rotor's rotational movement to electric power, and a second means for permitting the flow of fluid from volumes defined by the rotor blades, the rotor blades comprising an external surface having openings in fluid connection with the volumes inside the blades for permitting the flow of fluid to the outside of the blades to fluid-thermodynamically interact with the wind hitting the part of the blade surface, and thereby prevent or eliminate the accretion of ice on the external surface of the blade.
Owner:BATTISTI LORENZO
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 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.
Owner:GENERAL ELECTRIC CO
Surface topographies for non-toxic bioadhesion control
Owner:UNIV OF FLORIDA RES FOUNDATION INC
Independent power generation in aircraft
Systems and methods of independent power generation are disclosed. A particular system includes an aircraft having at least one engine and a plurality of independent power units. Each power unit of the plurality of independent power units generates electricity independently of the at least one engine. The plurality of independent power units include at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity. The first set of electrical characteristics is different than the second set of electrical characteristics.
Owner:THE BOEING CO
Anti-icing, de-icing, and heating configuration, integration, and power methods for aircraft, aerodynamic, and complex surfaces
ActiveUS20140070054A1Reduce weightEfficiency advantageMaterial nanotechnologyDe-icing equipmentsElectricityElectrical resistance and conductance
Anti-icing methods and aerodynamic structures having laminated resistive heaters for de-icing are described. Several of the inventive aspects utilize laminated resistive heaters comprising a carbon nanotube layer and / or capacitors to store and supply electricity. The invention also includes methods of making aerodynamic structures having de-icing or anti-icing functionality.
Owner:BATTELLE MEMORIAL INST
Turbojet pod with laminar flow
InactiveUS6179249B1Good aerodynamic shapeKeep shapeAircraft power plant componentsDe-icing equipmentsEngineeringTurbojet
The bay (12) of a turbofan engine (10) comprises a front structural element (30), whose external surface is continuous and extends over at least 50% of the geometrical chord of the bay. Said element (30) is installed on maintaining and guiding members (44), such as slides, which prevent a significant deformation in flight and allow a sliding to the front of the element (30) for maintenance purposes. A laminar air flow around the front half of the bay (12) is consequently ensured.
Owner:SOC NATIONALE INDUSTRIELLE AEROSPATIALE SA
System and method to identify regions of airspace having ice crystals using an onboard weather radar system
ActiveUS20130234884A1Clear air turbulence detection/forecastingDe-icing equipmentsWeather radarAtmospheric sciences
Owner:HONEYWELL INT INC
Nacelle inlet lip anti-icing with engine oil
InactiveUS7131612B2Inhibition formationPrevent freezingTurbine/propulsion engine coolingDe-icing equipmentsLeading edgeNacelle
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.
Owner:PRATT & WHITNEY CANADA CORP
Pressure control system for a pressure-expandable displacement element
An elastically expandable hollow displacement element is secured to the rear surface of an aircraft wing slat. When the displacement element is contracted, the slat may be retracted onto the wing's leading edge. When the slat is extended, the displacement element is expanded to protrude convexly from the slat, thereby preventing vortex formation in the slat air gap and reducing aero-acoustic noise. A pressure control system for inflating and deflating the displacement element includes a bleed air line connected from the aircraft engine bleed air system to the displacement element, a shut-off valve and a pressure control valve interposed in series in the bleed air line, and a slat contour controller connected by respective signal lines to the valves, which control the quantity and the pressure of the bleed air supplied into the displacement element, for properly inflating the same.
Owner:AIRBUS OPERATIONS GMBH
Thickness measurement device for ice, or ice mixed with water or other liquid
InactiveUS6239601B1Resistance/reactance/impedenceDe-icing equipmentsMeasurement deviceMeasuring output
A device and method are provided for determining the thickness of a layer of solid ice, a mixture of ice and water, or a mixture of ice and other liquid, accumulated on the outer surface of an object. First and second total impedance sensors are operated at first and second frequencies. Corresponding first and second AC total impedance measuring circuits are coupled to the first and second sensors to produce output voltages based on the total impedance changes sensed by the sensors. A processor is coupled to the first and second measuring circuits to generate an output value using the measured output voltages. The output value is indicative of the thickness of the ice or ice and water mixture, or ice and other liquid.
Owner:NAT AERONAUTICAS & SPACE ADMINISTATION
Prescented and custom scented card insert
InactiveUS6575383B2Better friendlinessThicken fragranceSpraying apparatusDe-icing equipmentsPaper towelEngineering
A pre-scented or custom scented card insert designed to fit into any existing toilet paper or paper towel holder. The insert allows consumers to choose a scent additive to freshen their bathroom, kitchens or any other place where these products are used, as well as to scent the toilet paper or paper towel rolls. The insert can be replaced easily to refresh the roll, or additional inserts can be added to create a stronger fragrance impact.
Owner:ORLANDI INC
Surface topographies for non-toxic bioadhesion control
An article has a surface topography for resisting bioadhesion of organisms and includes a base article having a surface. A composition of the surface includes a polymer. The surface has a topography comprising a pattern defined by a plurality of spaced apart features attached to or projected into the base article. The plurality of features each have at least one microscale dimension and at least one neighboring feature having a substantially different geometry. An average feature spacing between adjacent ones of the features is between 10 μm and 100 μm in at least a portion of the surface. The surface topography can be numerically represented using at least one sinusoidal function. In one embodiment, the surface can comprise a coating layer disposed on the base article.
Owner:UNIV OF FLORIDA RES FOUNDATION INC
Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip
InactiveUS7588212B2Increases amount of acoustic treatmentReduce weightDe-icing equipmentsFuselage insulationNacelleAcoustic noise reduction
Owner:ROHR INC
Aeroengine intake having a heat exchanger within an annular closed chamber
InactiveUS7398641B2Prevent freezingIncrease surface areaTurbine/propulsion engine coolingDe-icing equipmentsAviationNacelle
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.
Owner:ROLLS ROYCE PLC
Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein
An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.
Owner:THE BF GOODRICH CO +1
Thermal management system for a gas turbine engine
In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
Owner:RTX CORP
Inflight ice detection system
InactiveUS7370525B1Efficient discriminationSimple systemDe-icing equipmentsInstrumentsElectrical conductorSurface mounting
A dual channel inflight ice detection system to detect ice accretion on an aircraft surface by illuminating an ice collecting surface mounted on an aircraft with linear polarized light. The backscattered light is acquired in two light conductors one with polarization sensitivity aligned to the transmitted light and the second with polarization sensitivity orthogonal to the first. The presence of ice is determined by the change in the ratio of light intensities in the two light conductors.
Owner:SWAN INT SENSORS
Electrical power generation apparatus for contra-rotating open-rotor aircraft propulsion system
An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.
Owner:ROLLS ROYCE NORTH AMERICAN TECH
Uniform Heat Distribution in Resistive Heaters For Anti-Icing and De-Icing
ActiveUS20160221680A1Prevent freezingImprove protectionWindingsDe-icing equipmentsElectrical resistance and conductanceAdhesive
The concept of the present invention describes configurations to provide uniform heat distribution of resistive heaters. This configuration allows successful anti-icing and deicing with relatively low applied power. One aspect involves the use of a thin film heater applied just underneath the topcoat to efficiently direct all heat to the surface, allowing anti-icing and de-icing with minimal power. This can be accomplished by employing a hybrid electrode interface, using a metal foil or metal braid that is attached to the aircraft surface with a structural adhesive that has been smoothed along the edges with metal-filled adhesive. Another aspect of the present invention uses an array of heater cells created as a single sheet and a heat spreading material, provided underneath or overtop of the heater cells.
Owner:BATTELLE MEMORIAL INST
Modular anti-icing/de-icing device for an aerodynamic surface
InactiveUS20050184193A1Overcome limitationsPropellersCoolant flow controlJet aeroplaneFlight vehicle
A anti-icing / de-icing device for an aircraft wing includes at least one aerodynamic surface, e.g. a rotorcraft blade or an airplane wing, the aerodynamic surface possessing at least two anti-icing / de-icing modules 17, with each module 17 being provided with a respective heater element 54. In addition, the heater elements 54 of the modules 17 are powered electrically by a common electrical power supply member 1, each anti-icing / de-icing module acting against icing in its own zone independently of the other module(s).
Owner:EUROCOPTER
Airfoil anti-icing assembly and method
InactiveUS6702233B1De-icing equipmentsHot gas positive displacement engine plantsJet engineEngineering
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. The system of this invention comprises a source of hot gases, typically jet engine bleed air, and the airfoil assembly of this invention.
Owner:ROHR INC
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