| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390093 | Ice preventer or de-icer | 39 |
| 20080302081 | Method for detecting ice ingestion in a gas turbine engine - 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. | 12-11-2008 |
| 20080307769 | 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 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. | 12-18-2008 |
| 20090199535 | ANTI-ICING APPARATUS AND METHOD FOR AERO-ENGINE NOSE CONE - An aero-engine nose cone anti-icing system ( | 08-13-2009 |
| 20090241509 | TURBINE ENGINE INLET STRUT DEICING - A gas turbine engine is disclosed that includes an inlet case having circumferentially spaced, radially extending inlet struts. Each inlet strut has a leading and trailing end. Spaced apart sidewalls adjoin the leading and trailing ends. A first heating element is arranged on the leading end. A second heating element is arranged on at least one of the sidewalls. The first heating element is configured to provide a different amount of energy per unit of time than the second heating element. | 10-01-2009 |
| 20090260341 | Distributed zoning for engine inlet ice protection - An engine inlet ice protection system and method for ice protection includes a plurality of grouped structural elements having electrical components that provide ice protection where power is cycled to the groups of structural elements so that at a given time the ice protection elements receiving power are generally distributed throughout the engine inlet. | 10-22-2009 |
| 20090272095 | ICE SHED REDUCTION FOR LEADING EDGE STRUCTURES - A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface. | 11-05-2009 |
| 20100101206 | DEVICE FOR DE-ICING THE AIR INTAKE OF A GAS TURBINE - 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. | 04-29-2010 |
| 20100107594 | TURBINE INTEGRATED BLEED SYSTEM AND METHOD FOR A GAS TURBINE ENGINE - A bleed system for a gas turbine engine includes: (a) a bleed air turbine having a turbine inlet adapted to be coupled to a source of compressor bleed air at a first pressure; (b) a bleed air compressor mechanically coupled to the bleed air turbine, and having a compressor inlet adapted to be coupled to a source of fan discharge air at a second pressure substantially lower than the first pressure; and (c) a mixing duct coupled to a turbine exit of the bleed air turbine and to a compressor exit of the bleed air compressor. | 05-06-2010 |
| 20100199629 | SYSTEME D'ANTI GIVRAGE ET DE DEGIVRAGE DE NACELLE DE MOTEUR D'AERONEF A TAPIS RESISTIF - A deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip. | 08-12-2010 |
| 20100236215 | 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 casing with an array of generally radially-extending strut members disposed therein. The heat transfer system includes at least one primary heat pipe disposed at least partially inside a selected one of the strut members; at least one secondary heat pipe disposed outside the fan casing and thermally coupled to the at least one primary heat pipe and to a heat source. Heat from the heat source can be transferred through the secondary heat pipe to the primary heat pipe and to the selected strut member. | 09-23-2010 |
| 20100242428 | AIR INTAKE STRUCTURE TO BE MOUNTED UPSTREAM OF A NACELLE MIDDLE STRUCTURE FOR AIRCRAFT ENGINE, AND NACELLE EQUIPPED WITH SUCH AIR INTAKE STRUCTURE - The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall ( | 09-30-2010 |
| 20100326041 | HEATED GUIDE VANE - A heated guide vane for turbomachinery includes a guide vane having two major surfaces joined about their periphery by edges and an electric heater element, wherein the electric heater element is secured to at least one major surface of the guide vane. | 12-30-2010 |
| 20110005188 | AIR INTAKE LIP FOR TURBOJET NACELLE - The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device ( | 01-13-2011 |
| 20110011056 | PIEZOELECTRIC DE-ICING OF AN AIR INLET - The invention relates to a lip assembly ( | 01-20-2011 |
| 20110099970 | SYSTEM FOR ICE AND/OR FROST PREVENTION USING GUIDED WAVE ENERGY - 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. | 05-05-2011 |
| 20110120076 | STRUCTURE FOR AN AIR INLET LIP OF AN ELECTRIC DE-ICING POD COMPRISING AN ACOUSTIC ATTENUATION ZONE - The present invention relates to a structure ( | 05-26-2011 |
| 20110131945 | ASSEMBLY OF COMPONENTS CONNECTED BY A DEVICE THAT MAINTAINS THE INTEGRITY OF THE SURFACE OF ONE OF THE COMPONENTS - This assembly comprises a first component ( | 06-09-2011 |
| 20110162340 | METHOD FOR MAKING A NACELLE DE-ICING ELEMENT - The invention relates to a method for making a nacelle element ( | 07-07-2011 |
| 20110167781 | TURBOMACHINE NACELLE AND ANTI-ICING SYSTEM AND METHOD THEREFOR - 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. | 07-14-2011 |
| 20110179764 | TURBO-ENGINE COMPRESSOR TIP COMPRISING DE-ICING MEANS - The de-icing system comprises a flexible bladder ( | 07-28-2011 |
| 20110179765 | Jet engine shield and deicer - A shield or protective grille assembly constructed of non-corrosive and heat conductive metal members ( | 07-28-2011 |
| 20110247313 | SYSTEM FOR HEATING AN AIRSTREAM BY RECIRCULATING WASTE HEAT OF A TURBOMACHINE - An embodiment of the present invention takes the form of an application and process that incorporates a waste heat source to increase the temperature of the airstream entering an inlet section of a combustion turbine. An embodiment of the present invention may perform an anti-icing operation that reduces the need to operate the IBH system. | 10-13-2011 |
| 20110277443 | ELECTRIC DE-ICING DEVICE AND RELATED MONITORING SYSTEM - 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 ( | 11-17-2011 |
| 20110296811 | Heat transfer arrangement for fluid-washed surfaces - 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. | 12-08-2011 |
| 20120017564 | SUPERCONDUCTIVE HEAT TRANSFER SYSTEM - 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. | 01-26-2012 |
| 20120036826 | ENGINE AND POD ASSEMBLY FOR AN AIRCRAFT, EQUIPPED WITH AN ANTI-ICING DEVICE - 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. | 02-16-2012 |
| 20120036827 | ROTATING INLET COWL FOR A TURBINE ENGINE, COMPRISING AN ECCENTRIC FORWARD END - 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. | 02-16-2012 |
| 20120137650 | FLUID IMPINGEMENT ARRANGEMENT - A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit. | 06-07-2012 |
| 20120255274 | FLOW DEVICE AND METHOD AND SYSTEM USING THE FLOW DEVICE - A flow device adapted to operate as a restrictor as well as provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device. The flow device includes an expandable orifice that has an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter, and an opening surrounded and defined by the tabs. The tabs project from the outer perimeter toward the opening, which restricts flow of the bleed air through the expandable orifice at a pressure below a predetermined pressure level, but then expands to relieve an over-pressure condition of the bleed air at a pressure above the predetermined pressure level as a result of the cantilevered tabs being deflected by the over-pressure condition. The device is adaptable for use in aircraft applications, including the regulation of bleed air used in anti-icing/de-icing systems. | 10-11-2012 |
| 20130180227 | Fastening element and de-icing device of an aircraft gas-turbine engine - The present invention relates to a fastening element, in particular to its use in a de-icing device of an aircraft gas-turbine engine, for connecting two components, with the fastening element ensuring a connection of the components with a predetermined relative movability to each other, with the fastening element including two struts arranged at an angle to each other, where two first end areas, spacedly arranged to each other, can be fastened to one of the components, and the two other second end areas can be connected to each other and fastened to the other component. | 07-18-2013 |
| 20130239542 | STRUCTURES AND METHODS FOR INTERCOOLING AIRCRAFT GAS TURBINE ENGINES - 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. | 09-19-2013 |
| 20130247541 | GAS TURBINE INTAKE ANTI-ICING DEVICE - The gas turbine intake anti-icing device is used for a gas turbine electric power generation system ( | 09-26-2013 |
| 20130327012 | GAS TURBINE ANTI-ICING SYSTEM - 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. | 12-12-2013 |
| 20140096503 | Magnetic De-Icing - 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. | 04-10-2014 |
| 20140144124 | Gas Turbine Anti-Icing System - 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. | 05-29-2014 |
| 20140165531 | HEATED RIGID ELECTRICAL SYSTEM - 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. | 06-19-2014 |
| 20150033698 | ANTI-ICING SYSTEM FOR A GAS TURBINE - 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. | 02-05-2015 |
| 20150377129 | De-Icing by Integral Electric Heat Generation - Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil. | 12-31-2015 |
| 20160003147 | System for preventing icing on an aircraft surface operationally exposed to air - A system for preventing icing on an aircraft surface includes a plasma actuator which is applied onto an aircraft surface operationally exposed to air and which is arranged for generating at least one plasma discharge (D) for inducing a flow (F) of ionized hot-air particles towards the surface. | 01-07-2016 |
