| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390092 | Debris anti-ingestion preventer | 41 |
| 20080236133 | TURBOMACHINE FRONT PORTION COMPRISING A DEFLECTOR SYSTEM FOR DEFLECTING FOREIGN BODIES, SUCH AS HAILSTONES - The present invention relates to a turbomachine front portion ( | 10-02-2008 |
| 20090044512 | DIRT SEPARATOR FOR COMPRESSOR DIFFUSER IN GAS TURBINE ENGINE - A compressor diffuser for a gas turbine engine is provided with a dirt separator. The dirt separator ensures the air having moved downstream of the compressor section, and moving toward the combustion section, is separated into a dirtier air flow path directly radially outwardly, and a cleaner airflow path directed radially inwardly. In this manner, the air reaching a combustion section, and the air being utilized for radially inner cooling air is relatively cleaner air. Further, the dirt separator provides a convenient surface for mounting a pressure sensor. In one embodiment, the dirt separator is mounted within the diffuser housing, and in a second embodiment, it is mounted immediately downstream. | 02-19-2009 |
| 20090126337 | RETROFIT DIRT SEPARATOR FOR GAS TURBINE ENGINE - A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine. | 05-21-2009 |
| 20090139200 | TURBOENGINE AIR INTAKE PROVIDED WITH A CONTROLLED FILTER SYSTEM - An air intake ( | 06-04-2009 |
| 20090145101 | PARTICLE SEPARATOR FOR TIP TURBINE ENGINE - A particle separator ( | 06-11-2009 |
| 20090255230 | GAS TURBINE - A gas turbine having air cooling is provided with an effective measure for cleaning cooling air which is used in the turbine, which measure is particularly efficient. In order to allow comparatively pure, that is to say particle-free, compressed cooling air to flow into the cooling-channel system of the turbine, it is proposed that a protective element is provided for particle separation in a manner which is adjacent radially further to the outside to the removal opening, which protective element impedes particles which floating the compressor final air from flowing into the removal opening. As a result the clogging of cooling—air holes in impact-cooled turbine components which are loaded by hot gas can be avoided. | 10-15-2009 |
| 20090266048 | Turbine Air-Intake Filter - A turbine air-intake filter for removal of particles from an air stream entering a gas turbine comprises a composite filter media ( | 10-29-2009 |
| 20090320441 | INFLATABLE SEAL ASSEMBLY BETWEEN AN ENGINE INLET AND A VEHICLE - An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine. | 12-31-2009 |
| 20100180566 | BIRD AND DEBRIS DEFLECTOR FOR AIRCRAFT JET ENGINES - A retractable deflector serves to deflect birds and debris from an air intake duct of an aircraft jet engine. The intake duct has a central longitudinal axis and a forward opening for the receipt of air. The deflector includes a plurality of elongate first support members disposed on the air intake duct in spaced relation to each other and having leading ends which extend from a perimeter of said forward opening. These members are mounted for movement to extend and retract the leading ends. A second support member is coupled to the leading ends of these first support members to retain said leading ends in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause said first support members to deflect at least one of a bird and debris, when in a first, deployed position, and to allow the leading ends of the first support members to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the air duct when in a second, retracted position. | 07-22-2010 |
| 20100287908 | Jet engine shield and debris deflector - A jet engine bird and debris shield device is disclosed that is designed as a deflector to deflect large birds, such as geese weighing in excess of eight pounds, and keep from entering the turbine blades of a jet engine. The shield device is aerodynamically shaped in the form of a frustro-conical cylinder aligned to the direction of flight and attaches to the air intake portion of the jet engine. The shield is formed with a series of openings or slots that allow sufficient air to be entrained into the jet engine intake. The orientation and shape of the slots direct the air directly to the turbine blades of the engine. | 11-18-2010 |
| 20100313542 | JET ENGINE SCREEN - The present invention relates to a jet screen designed to protect a jet engine comprising: a conical shaped perimeter; a concaved metal grid within the perimeter; and a plurality of bolts, said bolts provide a mechanism to secure the screen to an intake opening of a jet engine. The metal grid may be manufactured by using a light metal alloy. The perimeter of the screen extends around the circumference of the intake opening and the jet screen completely covers the intake opening. The metal grid according to the present invention provides sufficient spacing to avoid interference with air intake into the intake opening and to prevent entry of foreign objects into the intake opening. | 12-16-2010 |
| 20100326040 | Bird and debris guand for a jet engine - This guard can be built of this wire material and put in frame so that it fits In the air intake of the jet engine to stop any bird or a piece of debris being sucked in. This would include not only commercial or any jet aircraft that has a frontal air intake including military or any other manufacture of aircraft that uses jet engines for power. | 12-30-2010 |
| 20110000184 | Method to protect jet engines from bird strikes - The method of preventing the dangers of birds entering the jet engines of an airplane during take-off and landing by rotating a portion of the jet engines cowling to a blocking position in front of the jet engine during take-off and landing and the rotating the same portion of the jet engine cowling back away from the front of the jet engine during high speed cruising at altitudes. | 01-06-2011 |
| 20110011055 | Jet engine air intake guard - A jet engine air intake guard takes the circumstance into consideration to protect a jet-engine air intake structure from being damaged by birds or any other foreign objects, including meteoritic debris and bullets during flight operations, said structure comprising a deflector, a steep dome-shaped device with sharply pointed forepart, a secondary device which is carefully designed to insert into the base component, in order to deflect birds or any foreign objects out of the air stream and to provide an adequate air intake to the jet-engine during use. According to the invention, the protective device also comprises a base component put over the air intake cowl being provided with stiffening means completely cover the air intake cowl to hold the protective device firmly while operating is being disclosed in the present application. | 01-20-2011 |
| 20110016845 | AIRCRAFT ENGINE PROTECTION DEVICE - A jet engine intake guard includes an engine sleeve located within the nacelle of the engine; a primary deflection screen located at a front portion of the sleeve and having a first circular frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the diameter of the primary frame and attached to one another in a tri-axle weave pattern. The guard also includes a secondary deflection screen located behind the primary deflection screen in the direction of air flow through the engine and having a second circular frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the secondary frame and attached to one another in a tri-axle weave pattern. The guard further includes a capture basket located between the primary and secondary deflection screens. The capture basket has a first wall located toward the primary deflection screen, a center portion and a second wall located toward the secondary deflection screen. In a preferred embodiment the entire guard is made of woven carbon fiber. | 01-27-2011 |
| 20110030333 | JET ENGINE PROTECTION SYSTEM - A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat has passed, the devices are stowed/retracted or safely jettisoned. | 02-10-2011 |
| 20110047959 | AIR PARTICLE SEPARATOR FOR A GAS TURBINE ENGINE - An assembly for separating debris from a pressurization air flow adjacent to a bearing compartment seal includes a baffle and a capture annulus. The baffle is disposed in the pressurization air flow upstream of the compartment seal. The capture annulus is positioned adjacent the baffle and has a cavity to collect the debris. | 03-03-2011 |
| 20110138770 | ANTI-ICING SYSTEM USING RADIANT INFRARED ENERGY FROM TURBINE EXHAUST FLUES - An exhaust flue is provided for use with a gas turbine engine. The exhaust flue is oriented to channel exhaust gases from a core engine of the gas turbine engine. The exhaust flue includes a radiating portion positioned within an air inlet of the gas turbine engine. The radiating portion is oriented to emit infrared radiation towards an air filter assembly within the air inlet. | 06-16-2011 |
| 20110179763 | Particle separator and debris control system - A gas turbine engine system includes an air inlet, an inlet particle separator located at the air inlet and having a blower selectively driven by a variable output motor, and a controller for dynamically controlling the variable output motor that selectively drives the blower of the inlet particle separator. | 07-28-2011 |
| 20110185700 | Jet engine bird diverters - This invention is a series of Jet engine bird diverters designed to attach to the side(s) of the jet engines and the leading edge of the jet engine housing or become an integral part of the leading edge of the jet engine housing. The designs embody aerodynamic structural titanium support systems that extend forward and terminate directly in front of the centerline of the jet engine terminating at a circular titanium forward spoke connecter that receives a sharply angled series of identical bird deflection spokes that trail back and attach to the perimeter of the jet engine intake housing or nacelle. All of the support elements and deflection members shall be aeronautically designed to direct a maximum amount of air into the jet engine. | 08-04-2011 |
| 20110277441 | METHOD AND APPARATUS FOR AN AIR FILTER CARTRIDGE REPLACEMENT ASSEMBLY - A method of assembling a filter replacement assembly for use with a gas turbine engine. The method includes coupling a first container to a filter wall that is included in an inlet air treatment system. The first container defines a first cavity that is sized to receive at least one filter. A second container is coupled to the first container. The second container defines a second cavity that is sized to receive the at least one filter therein. | 11-17-2011 |
| 20110277442 | Seal for Gas Turbine Filter - A turbine filter seal assembly may include a first mounting flange with a channel extending about a first air opening, a seal with an enlarged portion compressed into the channel, and a second mounting flange with a protrusion extending about a second air opening. The first and second mounting flanges are configured to couple to one another about the seal, and the protrusion is configured to bias the seal. | 11-17-2011 |
| 20120000176 | FOG AND MIST CATCHING APPARATUS - 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. | 01-05-2012 |
| 20120023895 | APPARATUS AND FILTERING SYSTEMS RELATING TO COMBUSTORS IN COMBUSTION TURBINE ENGINES - A combustor for a combustion turbine engine, the combustor that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; a screen; and a standoff comprising a raised area on an outer surface of the outer wall near the periphery of the windows; wherein the screen extends over the windows and is supported by the standoff in a raised position in relation to the outer surface of the outer wall and the windows. | 02-02-2012 |
| 20120124961 | Filter Cartridge Assembly For Use With Turbine Engine Systems - A filter cartridge assembly includes a first filter including a first cavity defined therein and a second filter coupled to the first filter. The second filter includes a second cavity defined therein in flow communication with first cavity. The filter cartridge assembly also includes at least one pre-filter extending about the first filter and the second filter such that a third cavity is defined between the at least one pre-filter and at least one of the first filter and the second filter. | 05-24-2012 |
| 20120131900 | INLET PARTICLE SEPARATOR SYSTEM - An inlet particle separator system is provided. The system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The system also includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Finally, the system includes a fluidic device disposed in flow communication with the first flow of substantially contaminated air for inducting air through the scavenge subsystem and the engine inlet. | 05-31-2012 |
| 20120216505 | AIRCRAFT - A bird knocking-off rod of a bird knocking-off device is disposed outside a jet engine, in front of an air inlet of the jet engine and capable of rotating with a rotation area that is larger than an opening area of the air inlet of the jet engine. The rotary drive unit contains a rotary drive source and is capable of rotationally driving the bird knocking-off rod independently of rotation of the jet engine. Thus, bird strike against aircraft can be prevented. | 08-30-2012 |
| 20130000271 | ENGINE SHIELD - One example embodiment includes an engine shield for protecting a jet engine intake. The engine shield includes a base, a first support and a second support. The first and second supports include a first end and a second end opposite the first end and are attached to the base at a first end. The engine shield also includes an apex attached the second end of the first support and the second end of the second support. The base, first support, second support and apex define an inner volume with an inner surface and an outer volume with an outer surface. The engine shield further includes a ring. The ring is attached to the first support between the base and the apex and the second support between the base and the apex. The engine shield additionally includes a mesh, where the mesh covers the outer surface. | 01-03-2013 |
| 20130104518 | Bird deflector and air replacement system | 05-02-2013 |
| 20130213003 | RETRACTABLE BIRD AND DEBRIS DEFLECTOR FOR AN AIRCRAFT JET ENGINE - A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a forward opening for air receipt. The deflector includes a plurality of elongate members disposed on the duct in spaced relation to each other, each member having two end segments and a central segment disposed between the two end segments; and a plurality of guiding members, each mounted for movement along the perimeter of the duct and coupled to one end segment of an elongate member. The central segment of each elongate member extends between a pair of guiding members such that the elongate member is movable by a respective pair of guiding members between a retracted position and a deployed position in front of the duct. When in the deployed position, the central segments are situated to impede the ingress of debris into the duct. | 08-22-2013 |
| 20130305684 | DEBRIS DISCOURAGER - A debris discourager for a gas turbine engine is rotatable about an engine axis and extends between a fore end and an aft end. A portion of the debris discourager includes a non-uniform surface that generates a wind flow to prevent debris from entering a sealed interface. | 11-21-2013 |
| 20140123621 | ACTUATED BYPASS HOOD FOR GAS TURBINE AIR INLET SYSTEM AND METHODS - An inlet hood for use with a gas turbine or compressor air inlet system includes a frame and at least one pre-filter pivotably held by the frame in an operating position. The pre-filter is pivotable to a bypass position angled relative to the operating position. Methods of assembly and use are provided. | 05-08-2014 |
| 20140144123 | INLET PARTICLE SEPARATOR SYSTEM WITH AIR INJECTION - An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter section, and an injection opening. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The injection opening is formed in and extends through the hub section, and is disposed downstream of the air inlet. | 05-29-2014 |
| 20150040535 | INLET PARTICLE SEPARATOR SYSTEM WITH HUB AND/OR SHROUD SUCTION - An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path. | 02-12-2015 |
| 20150113938 | WEATHER HOOD WATER REMOVAL SYSTEM AND METHOD FOR ASSEMBLY - An air intake system for use with a gas turbine is provided. The air intake system includes a weather hood coupled to a filter house. The air intake system also includes a prefilter assembly configured within said weather hood, wherein said prefilter assembly includes at least three air filtration units, including at least one moisture separator and at least one coalescing filter. | 04-30-2015 |
| 20150322859 | GAS TURBINE AIR INLET ARRANGEMENT AND METHODS - A tube sheet for the air intake for a gas turbine includes a non-planar frame arrangement with openings to receive filter elements. There can be inlet hoods that are pivotable relative to the tube sheet. | 11-12-2015 |
| 20150345391 | Environmental Defense Shield - An environmental defense shield includes symmetric airfoil-shaped vanes contributing to and positioned around a plenum space and positioned in front of a turbine engine. An annular band stiffener is set into the vanes, which projects forward in a diminishing size, the vanes merging together to create or attaching to a solid nose. The environmental defense shield serves to protect the engine from debris while also smoothing airflow into the engine. | 12-03-2015 |
| 20150377074 | DEBRIS REMOVAL SYSTEM - A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism. | 12-31-2015 |
| 20160017804 | APPARATUS FOR PROTECTING AIRCRAFT COMPONENTS AGAINST FOREIGN OBJECT DAMAGE - A device for protecting aircraft equipment against contact by a foreign object including an interference arrangement disposed in an air inlet upstream from the aircraft equipment where the interference arrangement is configured to physically obstruct passage of the foreign object within the air inlet. | 01-21-2016 |
| 20160032835 | AIR-DRIVEN PARTICLE PULVERIZER FOR GAS TURBINE ENGINE COOLING FLUID SYSTEM - A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway. The aperture is configured to provide a fluid in a flow direction. Fingers are arranged in the fluid passageway facing into flow direction. The fluid passageway includes a cooling cavity immediately downstream from the fingers and it is configured to receive fluid having passed over or through the fingers. | 02-04-2016 |
| 20160097324 | FILTRATION SYSTEM FOR USE IN A GAS TURBINE ENGINE ASSEMBLY AND METHOD OF ASSEMBLING THEREOF - A filtration system and methods of assembly and operation are provided. The filtration system includes an array of perforated tubes in flow communication with a flow of intake air. Each perforated tube comprises a solids inlet and a solids outlet. The system also includes a solids feed system comprising a feed line coupled in flow communication with said solids inlet and configured to channel sorbent material through each perforated tube in said array. The filtration system also includes a monitoring arrangement for monitoring a parameter associated with the intake air, and varying the operation of the system based upon said parameter. | 04-07-2016 |
