Aircraft Anti-ingestion Means (e.g., Aircraft Debris Guard) Patents (Class 55/306)
  • Patent number: 11181044
    Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Grant
    Filed: September 14, 2020
    Date of Patent: November 23, 2021
    Inventor: Michael J. Kline
  • Patent number: 11162462
    Abstract: An air intake system for a vehicle has a conduit having an internal wall forming an air passage. A deflector is disposed within the air passage. A restricting structure is disposed within the air passage between the deflector and a conduit outlet. The restricting structure defines at least in part an opening substantially laterally aligned with the deflector. The restricting structure has a lateral wall disposed downstream of the deflector and extending within the air passage. The lateral wall has a front surface generally facing a conduit inlet, and a plurality of surface-increasing features provided on the front surface. Each of the surface-increasing features has a length of at least 1 mm measured from the front surface in a direction normal thereto. An air intake system having a collector connected to the deflector and positioned to collect at least some moisture from air flowing past the deflector is also described.
    Type: Grant
    Filed: September 9, 2019
    Date of Patent: November 2, 2021
    Assignee: BOMBARDIER RECREATIONAL PRODUCTS INC.
    Inventor: Thomas Driant
  • Patent number: 11125192
    Abstract: A centrifugal air filter for an automotive system includes a plurality of single separators for setting an air flow passing therethrough in a turbulent motion and a separation area surrounding the plurality of single separators. The separation area receives particles from the air flow due to the centrifugal forces. A filter housing portion is located below a predefined or operation position for receiving particles from the air flow due to gravity, and an intake pipe is connected by an extraction line to a connecting pipe emerging on a filter housing and opening into the filter housing portion.
    Type: Grant
    Filed: April 21, 2020
    Date of Patent: September 21, 2021
    Assignee: DEERE & COMPANY
    Inventors: Ming Parker Yuen, Phouphadeth Sananikone, Dierk Esau, Alexander Berg
  • Patent number: 11047305
    Abstract: A debris deflector for a jet engine. The debris deflector includes a housing having a base and a nose, wherein the housing tapers radially inwardly from the base towards the nose, such that the nose can deflect debris away from the housing. The housing includes a flexible shroud that extends between the base and the nose, such that the housing can selectively move between a collapsed position and an extended position, such that a linear distance between the nose and the base is less when in the collapsed position. A fastener is disposed on the base to removably secure the housing to a jet engine cowling. The debris deflector is useful for deflecting debris, such as wildlife or small aircraft, away from the jet engine during flight.
    Type: Grant
    Filed: April 10, 2019
    Date of Patent: June 29, 2021
    Inventor: Stephanie Fraser-Beekman
  • Patent number: 10946975
    Abstract: A turbomachine of the «open rotor» type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.
    Type: Grant
    Filed: November 25, 2016
    Date of Patent: March 16, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Romain Jean-Claude Ferrier, Romeo Brogna, Jackie Raymond Julien Prouteau, Nicolas Joseph Sirvin
  • Patent number: 10906660
    Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: February 2, 2021
    Assignee: Bell Textron Inc.
    Inventor: Eric Albert Sinusas
  • Patent number: 10889384
    Abstract: The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: January 12, 2021
    Assignee: Textron Innovations Inc.
    Inventor: Thomas Dewey Parsons
  • Patent number: 10858995
    Abstract: A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: December 8, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Roger J. Aubert
  • Patent number: 10836504
    Abstract: One embodiment is a passive particle separation system including a plenum; an inlet for feeding outside air into the plenum, wherein the outside air has particles entrained therewith; a housing for enclosing the plenum; and a standpipe installed on the housing. The outside air enters the plenum via the inlet and plenum, housing, and standpipe interact to impact the outside air entering the plenum to cause the particles to be released from the outside air.
    Type: Grant
    Filed: April 26, 2018
    Date of Patent: November 17, 2020
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Joshua Allan Edler, Brent Scannell, Thomas Mast, Sarah R. Villanueva, David Michael Tiedeman, Keith C. Pedersen
  • Patent number: 10823063
    Abstract: Foreign object damage (FOD) screen assemblies and gas turbine engine compartments having FOD screen assemblies are provided. FOD screen assemblies provided herein are formed of materials that reduce the overall weight of the assembly such that easier handling and repair of the FOD screen assembly may be achieved. Further, the FOD screen assemblies provided herein include features that provide for a secure attachment of one or more mesh members to frame members of the assembly. The one or more mesh members are secured to the frame members in such a way that minimal stress is placed on the mesh member at the attachment points.
    Type: Grant
    Filed: February 13, 2018
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: John Joseph Wunsch, Randy Ray Johnson, Justin Sanjay Rao, Adam Patrick Young
  • Patent number: 10774744
    Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: September 15, 2020
    Inventor: Michael J. Kline
  • Patent number: 10765980
    Abstract: An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: September 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Francois Bisson, Mark Cunningham
  • Patent number: 10556701
    Abstract: An energy absorbing arrangement may comprise an inner barrel comprising a centerline axis, an outer barrel, a webbing extending between the outer barrel and the inner barrel and configured to be offset from a nose lip by a distance, the webbing being folded together to form a plurality of folds, the plurality of folds being stitched together via a plurality of stitches, wherein the webbing is configured to absorb energy from an object in response to the object passing through the nose lip and applying a force to the webbing.
    Type: Grant
    Filed: April 14, 2017
    Date of Patent: February 11, 2020
    Assignee: Rohr, Inc.
    Inventor: Johann Steven Schrell
  • Patent number: 10513980
    Abstract: A gas turbine engine arrangement comprising a gas turbine engine and an inlet screen. The gas turbine engine comprises an engine core comprising an inlet having a radial extent extending from an engine longitudinal axis to a first radial position, and a fan duct comprising an inlet having a radial extent extending from the first radial position to a fan casing, the inlet screen comprising an at least part annular porous grid radially extending across at least part of the radial extent of the fan duct inlet, and not extending across any substantial part of the radial extent of the core inlet.
    Type: Grant
    Filed: January 23, 2018
    Date of Patent: December 24, 2019
    Assignee: ROLLS-ROYCE PLC
    Inventor: Vasileios Kyritsis
  • Patent number: 10480413
    Abstract: An intertial particle seperator (IPS) including an intake air duct, a scavenge duct that shares an interior common wall with the intake air duct, a clean air duct, and a splitter. The splitter is configured to split a flow of intake air into a flow of scavenge air to pass through the scavenge duct and a flow of clean air to pass through the clean air duct. The IPS also includes a plurality of valleys on the intake air duct. The plurality of valleys includes a plurality of troughs and peaks along the interior common wall. In addition, each trough of the plurality of valleys extends along a direction of the flow of intake air.
    Type: Grant
    Filed: March 9, 2016
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Philip H. Snyder
  • Patent number: 10393023
    Abstract: A tangential on-board injector for a gas turbine engine is provided. The tangential on-board injector includes a body having an entrance and an exit, the body having a curved shape and defining an air passageway between the entrance and the exit and an inlet extension connected to the entrance of the body, the inlet extension extending from the body and having an inlet configured to force air to change direction when entering the inlet of the inlet extension.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: August 27, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Mark F. Zelesky
  • Patent number: 10265707
    Abstract: A ram circuit for an aircraft includes a ram inlet housing, a ram outlet housing, a heat exchanger, a ram air fan, and a particle separator. The ram inlet housing includes a chamber and an inlet configured to receive air. The ram outlet housing is fluidly connected to the ram inlet housing. The heat exchanger is disposed between and fluidly connected to the inlet housing and the outlet housing. The ram air fan is disposed in the outlet housing and includes a motor with a cooling inlet. The particle separator includes an outer inlet and a clean air outlet. The outer inlet is configured to receive ram air from the chamber of the ram inlet housing and faces into a flow of air passing through the chamber. Clean air is discharged through the clean air outlet which is fluidly connected to the cooling inlet of the motor.
    Type: Grant
    Filed: December 21, 2016
    Date of Patent: April 23, 2019
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Richard A. Himmelmann
  • Patent number: 10184399
    Abstract: An inertial inlet particle separator system for a vehicle engine is provided. A separator assembly and collector assembly are coupled to the scavenge flow path and configured to receive the scavenge air. The collector inlet has a throat defining a cumulative throat area at each position along the throat length from the first throat end to the second throat end. The collector body defines a cross-sectional area associated with each position along the throat length between the first throat end and the second throat end. The collector outlet is coupled to the collector body such that scavenge air flows into the collector inlet, through the collector body, and out through the collector outlet. At a first position between the first throat end and the second throat end, the respective cross-sectional area of the collector body is greater than or equal to the respective cumulative throat area.
    Type: Grant
    Filed: April 7, 2016
    Date of Patent: January 22, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Zedic Daniel Judd, Yogendra Yogi Sheoran, Jennifer Ann Reich, Todd A. Kincheloe, Yates Wong, Cristopher Frost
  • Patent number: 10086321
    Abstract: A liquid separation device for the separation of liquid or liquid mist from a gas, with at least one pair of basic carriers being a first and a second plate-shaped basic carrier, where in each of the first and the second basic carrier, at least two separator elements are formed. The separator elements each have a passage pipe with a gas inlet and a gas outlet, which are arranged at opposite sides of the respective plate-shaped basic carrier in such a way that the passage pipe extends through the respective plate-shaped basic carrier. The first and the second basic carrier being arranged one next to the other in flow direction of the gas. Each of the two separator elements in both basic carriers in which the separator elements are arranged adjacent to each other, with their passage pipes form continuous flow paths for the gas.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: October 2, 2018
    Assignee: Reinz-Dichtungs-GmbH
    Inventors: Philipp Zedelmair, Christoph Erdmann, Francesco Zitarosa
  • Patent number: 10046861
    Abstract: An aircraft system comprising a deflector assembly including, a base having mounting apertures; an inner ring concentrically positioned within an outer ring, the inner ring and the outer ring have an annulus defined therebetween via a base plate, a plurality of rods attached within the annulus and culminating at an apex creating a conical profile; and a forward-mounted cone-shaped deflecting member. The base plate comprises a through hole allowing airflow through the deflector assembly to supply an airplane engine. The aircraft safety device system further comprises at least one locking latch for removably securing the deflector assembly to a housing of the airplane engine. The aircraft safety device is mountable inside a lip of the housing of the airplane engine. Further, the aircraft safety device provides protection for airplane engines from air born animate and inanimate objects.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: August 14, 2018
    Inventors: Richard Jones, Terrell Jones
  • Patent number: 9810079
    Abstract: A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: November 7, 2017
    Assignee: General Electric Company
    Inventors: Robert Francis Manning, Victor Hugo Silva Correia
  • Patent number: 9709275
    Abstract: 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.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: July 18, 2017
    Assignee: General Electric Company
    Inventors: Peter de Diego, Herbert Chidsey Roberts, III, Frederic Woodrow Roberts, Jr.
  • Patent number: 9550140
    Abstract: A separator method and apparatus that includes a rotatable drum defining an annular passageway therein, a plurality of blades coupled to the rotatable drum and located in the annular passageway, each of the plurality of blades including a leading section, a trailing section, a concave surface, and a convex surface, the concave and convex surfaces extending from the leading section to the trailing section, each of the plurality of blades disposed circumferentially adjacent to at least another one of the plurality of blades so as to define blade flowpaths therebetween, and a housing at least partially surrounding the rotatable drum and defining a fluid collection chamber fluidly communicating with the annular passageway.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: January 24, 2017
    Assignee: Dresser-Rand Company
    Inventors: William C. Maier, Gocha G. Chochua
  • Patent number: 9517842
    Abstract: Some examples of an aircraft engine barrier filtration system include an engine barrier filter layer positioned near an aircraft engine intake. The filter layer filters aircraft engine intake air. The system includes a check valve assembly positioned adjacent to the engine barrier filter layer. The check valve assembly permits the engine intake air to flow into the engine through the filter layer during a first aircraft operation mode and to prevent air flow away from the engine through the filter layer during a second aircraft operation mode that is different from the first aircraft operation mode.
    Type: Grant
    Filed: May 30, 2014
    Date of Patent: December 13, 2016
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Albert G. Brand
  • Patent number: 9403601
    Abstract: An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the guard body, at least three, vertical, peripherally extending walls located between the base and the dome section, with successive ones of the peripheral walls having different peripheral dimensions, peripherally cylindrical, with the dimension increasing from the base toward the dome section. A plurality of air intake openings are defined in and between the peripheral walls with at least one dimensional size which is small enough to prevent having birds from being able to pass through the guard into the aircraft engine.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: August 2, 2016
    Inventor: William Bekoe Boateng
  • Patent number: 9316183
    Abstract: An engine system including an air intake duct positioned upstream of an engine cylinder may include an ice ingestion feature for retaining condensation. An ice ingestion feature may include indents formed in the bottom of an air intake duct wall. As such, the ice ingestion feature may include compartments and/or grooves of varying depths, widths, and/or angles such that the ice retention rate may be based on the surface area of the compartment or grooves.
    Type: Grant
    Filed: August 15, 2013
    Date of Patent: April 19, 2016
    Assignee: Ford Global Technologies, LLC
    Inventors: Scott M. Rollins, Christopher B. Bishop
  • Patent number: 9272293
    Abstract: A particle separator comprises a vessel, a fluid inlet, a fluid swirl passage, a scupper cavity, a first fluid outlet, and a second fluid outlet. The vessel includes a vessel sidewall extending between a vessel top side and a vessel bottom side. The fluid swirl passage includes a first passage end in communication with a fluid inlet disposed on the vessel top side. A second passage end is in communication with a vessel swirl cavity defined at least in part by an inner surface of the vessel sidewall. The scupper cavity includes a scupper entrance disposed along the inner surface of the vessel sidewall, and is spaced circumferentially apart from the second passage end. The first fluid outlet is in communication with the scupper cavity and disposed on the vessel bottom side. The second fluid outlet is disposed above the first fluid outlet in communication with the vessel swirl cavity.
    Type: Grant
    Filed: April 29, 2013
    Date of Patent: March 1, 2016
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Peter Bizzarro, Charles J. McColgan, Thomas E. Vatter
  • Patent number: 9249727
    Abstract: 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.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: February 2, 2016
    Inventor: Jeffrey A. Matos
  • Patent number: 9234461
    Abstract: 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.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: January 12, 2016
    Assignee: Shield Aerodynamics LLC
    Inventor: Dennis Snyder
  • Patent number: 9212606
    Abstract: A bird strike prevention device for covering an air intake of a jet engine of an airplane includes a plurality of stays arranged to form a conical shape as a whole; and a joining portion configured to connect the plurality of stays to each other on an apex side of the conical shape. The plurality of stays is mounted on the jet engine near an outer edge of the air intake at a base of the conical shape. An axis of the conical shape coincides with a rotation axis of the jet engine. The number of the stays included in the plurality of stays is determined based on a minimum size of target birds to be prevented from striking the jet engine.
    Type: Grant
    Filed: December 24, 2013
    Date of Patent: December 15, 2015
    Inventor: Khalid Hamad Mutleb Alnafisah
  • Patent number: 9192882
    Abstract: A non-fouling, bypass filter is disclosed. The filter is formed of a tapered structure having particulate material filtering properties. The tapered structure has an open base and a closed top, with its exterior surface being exposed to a gas/fluid stream to be filtered. A gas/fluid stream generating device generates a gas/fluid stream that is drawn into the tapered structure's interior and that is filtered due to the particulate material filtering properties of the tapered structure. The external profile of the conically shaped structure is adapted to cause a plurality of gas/fluid streams from the ambient gas/fluid to flow against the exterior surface of the tapered structure to prevent the building up of particulate material on the exterior surface.
    Type: Grant
    Filed: March 2, 2012
    Date of Patent: November 24, 2015
    Assignee: GAME CHANGERS LLC
    Inventors: Andrew D. Zonenberg, Jason D. Sanchez, Piotr A. Garbuz
  • Patent number: 9187170
    Abstract: An airfoil (10) having a main structure (15) including at least one spar (16) and a front structure (20) forming a leading edge (21), said airfoil (10) having an empty space (25) between said main structure (15) and said front structure (20). The airfoil (10) includes a rigid deflector member (30) in said empty space (25), the deflector member being fastened to the main structure (15), said deflector member (30) having a sharp edge (31) facing towards said front structure (20) in order to deflect an external obstacle impacting against said front structure (20).
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: November 17, 2015
    Assignee: Airbus Helicopters
    Inventors: Luc Lecerf, Vincent Moreau, Xavier Maraninchi, Jean-Charles Sicard
  • Patent number: 9091207
    Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: July 28, 2015
    Assignee: SNECMA
    Inventors: Philippe Gerard Chanez, Gaetan Jean Mabboux, Philippe Gilles Minot, Thomas Alain Christian Vincent, Didier Jean-Louis Yvon
  • Publication number: 20150121821
    Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Application
    Filed: January 12, 2015
    Publication date: May 7, 2015
    Inventor: Michael J. Kline
  • Patent number: 8998691
    Abstract: An energy efficient and quiet air cooling system for a building structure is provided. The air cooling system includes an evaporator system mounted in the wall of the building, a remotely mounted fan, an air intake, and a sound and heat insulating duct. The fan is mounted in the attic and configured to draw air from the living area of the building through the sound insulating duct with sufficient power to create a negative static pressure in the living area. The negative static pressure in turn causes outside air to flow through the evaporator system which removes heat from the outside air. The cooled air is in turn drawn into the building and pulled into the attic through the duct and expelled through the attic.
    Type: Grant
    Filed: December 19, 2011
    Date of Patent: April 7, 2015
    Assignee: QC Manufacturing, Inc.
    Inventor: Dana Charles Stevenson
  • Patent number: 8968437
    Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Grant
    Filed: May 7, 2013
    Date of Patent: March 3, 2015
    Inventor: Michael J Kline
  • Patent number: 8961634
    Abstract: A filter system includes a filter assembly having an interior, an end defining a bypass opening, and another end for coupling to an air intake of an aircraft engine to permit intake air from the interior to enter the air intake. The filter system includes a bypass closure movable relative to the filter assembly between at least a first position and a second position. The bypass closure substantially covers the bypass opening in the first position to inhibit intake air from entering the interior through the bypass opening. The filter system includes an actuator coupled to at least one of the filter assembly and the bypass member to cause relative movement of the bypass closure between the first and second positions.
    Type: Grant
    Filed: October 17, 2011
    Date of Patent: February 24, 2015
    Assignee: Aerospace Filtration Systems, Inc.
    Inventor: Mark Edward Boyce
  • Patent number: 8945254
    Abstract: Embodiments of the present invention provide an inlet particle separator for a gas turbine engine having an inlet flow path, a scavenge flow path, a core flow path, and a flow splitter disposed between the scavenge and core flow paths. A plurality of grooves may be disposed about an inner surface of a wall of the separator within the inlet flow path.
    Type: Grant
    Filed: December 21, 2011
    Date of Patent: February 3, 2015
    Assignee: General Electric Company
    Inventors: Jeffrey Mayer, Brian Roberts, Jonathan Anisko
  • Patent number: 8876930
    Abstract: This invention relates in general to a fixed guard(s)/cap(s) and/or screen(s) apparatus (single and/or double formation) shall effect multiple aspects for example the nacelle and inlet for numerous craft, jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) which may be applied to the engine shaft attached apparatus and/or pole that allows the mechanism to function by self-induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s), cap(s) and/or screen(s) apparatus, which includes a gaseous intake cavity, centrifuge, chamber, manifold and processes—static free and or purification chamber, and a particle collector without limiting engine thrust.
    Type: Grant
    Filed: November 15, 2010
    Date of Patent: November 4, 2014
    Inventor: Marina Ellen Marinella Pavlatos
  • Patent number: 8869537
    Abstract: A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavorable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: October 28, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Torsten Geis, Edward Brook
  • Publication number: 20140260127
    Abstract: An inlet protection system for filtering air prior to entry into an air intake of an engine of an aircraft includes interchangeably a particle separator panel and a barrier filter panel. The barrier filter panel is adapted to be mounted conformal to the contour of the aircraft and to be interchangeable with the particle separator panel. The particle separator panel has an outer skin and a plurality of particle separators. The outer skin has an opening disposed along a portion of it to discharge filtered particles from within the removable panel directly outward therefrom.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: AEROSPACE FILTRATION SYSTEMS, INC.
    Inventor: Aerospace Filtration Systems, Inc.
  • Publication number: 20140237954
    Abstract: One embodiment of the present disclosure is a unique particle separator. Another embodiment is a unique aircraft. Another embodiment is a unique inertial particle separator. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft, engines and particle separators for aircraft and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present disclosure will become apparent from the description and figures provided herewith.
    Type: Application
    Filed: February 12, 2014
    Publication date: August 28, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventor: Phillip H. Snyder
  • Publication number: 20140202121
    Abstract: A system for preventing foreign objects from entering an air unit of an aircraft is provided including a reverse J-tube mounted to a wall of the ram air header. The first end of the reverse J-tube defines a portion of a cool fluid flowpath. The ram air header also includes a particle separator that is removably mounted to the first end of the reverse J-tube. The particle separator prevents foreign objects from entering the cool fluid flowpath. The particle separator has a generally conical shape. An airflow, opposite the direction of the cool fluid flowpath removes foreign objects from a surface of the particle separator.
    Type: Application
    Filed: June 18, 2012
    Publication date: July 24, 2014
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Craig M. Beers, Brent J. Merritt
  • Patent number: 8757551
    Abstract: A foreign object damage protection system comprises a sensor for detecting a foreign object, a fluid in a reservoir, a means for dispensing the fluid, the means for dispensing the fluid in communication with the reservoir, and a control unit, whereby when the sensor detects a foreign object, the control unit causes fluid to be dispensed from the reservoir through the means for dispensing and towards the foreign object. The sensor is attachable to one or more locations on an aircraft, such as a wing, nose, windshield, fuselage or tail. The sensor can be a radar sensor, weather radar sensor, weather radar sensor modified to detect objects at short ranges, infra-red sensor, forward-looking infrared sensor, a light detection and ranging sensor, motion sensor, thermal sensor, or video sensor. The system provides a way to protect an aircraft from striking foreign objects, such as birds, in the path of the aircraft.
    Type: Grant
    Filed: June 4, 2012
    Date of Patent: June 24, 2014
    Inventor: Zamir Margalit
  • Patent number: 8685126
    Abstract: A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: April 1, 2014
    Assignee: Turbomeca
    Inventor: Olivier Pierre Descubes
  • Patent number: 8679210
    Abstract: A particle separator includes a first housing and a second housing. The first housing extends along an axis from an open proximal end to an open distal end. The second housing has a closed proximal end disposed adjacent the open proximal end of the outer housing. The second housing extends from the closed proximal end into the first housing along substantially a same axis as the axis of the first housing. The second housing has one or more passages disposed at a distance from the closed proximal end of the second housing. Additionally, the one or more passages are disposed within the first housing at a distance from the open proximal end thereof.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: March 25, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Christopher McAuliffe, Brent J. Merritt
  • Patent number: 8663350
    Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: March 4, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Philip Harold Snyder
  • Patent number: 8657895
    Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: February 25, 2014
    Inventor: Michael J. Kline
  • Publication number: 20130305668
    Abstract: The Debris Intrusion Shield for Jet Engine Applications is a prolate hemispheroid metallic assembly installed at the intake of a jet engine. The assembly is designed and intended to limit or prevent the intrusion of solid or semi-solid objects into the engine intake while on the ground or in-flight. All elements of the assembly are arrayed symmetrically about the longitudinal axis of the engine. The assembly is constructed of four basic parts. Tubing is positioned as a radial array about the engine circumference, and serves as the primary debris deflection element. The engine mounting collar serves as the aft point-of-attachment of the assembly to the engine nacelle, and as the aft mounting point for the radial array of tubing. The forward mounting fixture serves as the forward point of connection for the tubing elements. The forward mounting fixture cover serves as a protective cover for the electrical anti-icing elements located at the forward surface of the forward mounting fixture.
    Type: Application
    Filed: May 18, 2012
    Publication date: November 21, 2013
    Inventors: Stephen Douglas Nichols, Susan Gail Nichols
  • Publication number: 20130291726
    Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
    Type: Application
    Filed: May 2, 2012
    Publication date: November 7, 2013
    Inventor: Michael J. Kline