Debris Anti-ingestion Preventer Patents (Class 60/39.092)
  • Patent number: 12188408
    Abstract: A gas turbine engine includes a bypass duct, a heat exchanger, and an inlet shroud. The bypass duct is configured to direct air through a flow path. The heat exchanger is configured to receive a portion of the air flowing through the flow path of the bypass duct. The inlet shroud is coupled with the heat exchanger and configured to adjust a direction of the portion of the air entering the heat exchanger.
    Type: Grant
    Filed: July 31, 2023
    Date of Patent: January 7, 2025
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Scott Schwenker
  • Patent number: 11918943
    Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.
    Type: Grant
    Filed: November 23, 2022
    Date of Patent: March 5, 2024
    Assignee: General Electric Company
    Inventors: Timothy Deryck Stone, Gregory Michael Laskowski, Robert Proctor, Curtis Stover, Robert Francis Manning, Victor Hugo Silva Correia, Jared Peter Buhler, Robert Carl Murray, Corey Bourassa, Byron Andrew Pritchard, Jr., Jonathan Russell Ratzlaff
  • Patent number: 11786854
    Abstract: A ventilation assembly and an air conditioning apparatus are provided. The ventilation assembly includes: a volute, a surface of the volute being provided with a mounting port; a filter assembly arranged in the mounting port or in a portion of the volute adjacent to the mounting port; and a sealing member arranged with the mounting port or with the portion of the volute adjacent to the mounting port, and configured to seal a gap between the filter assembly and the mounting port.
    Type: Grant
    Filed: June 28, 2021
    Date of Patent: October 17, 2023
    Assignee: BEIJING XIAOMI MOBILE SOFTWARE CO., LTD.
    Inventor: Lianyu Shan
  • Patent number: 11608782
    Abstract: An inertial particle separator (IPS) for a gas turbine engine, has: inner and outer walls extending about a central axis, an inlet defined between the inner and outer walls and oriented axially; swirling vanes extending at least radially between the inner and outer walls and circumferentially distributed around the central axis, the swirling vanes configured for inducing a circumferential component in an airflow flowing between the swirling vanes; a plenum between the inner and outer walls downstream of the swirling vanes, the plenum circumferentially extending about the central axis, the outer wall converging toward the central axis in a direction of the airflow; and a splitter radially between the inner and outer walls downstream of the plenum and circumferentially extending around the central axis, a particle outlet radially between the splitter and the outer wall, an air outlet radially between the inner wall and the splitter.
    Type: Grant
    Filed: April 15, 2020
    Date of Patent: March 21, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Menheere, Santo Chiappetta, Tim Redford, Daniel Van Den Ende
  • Patent number: 11541340
    Abstract: A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.
    Type: Grant
    Filed: May 20, 2021
    Date of Patent: January 3, 2023
    Assignee: General Electric Company
    Inventors: Timothy Deryck Stone, Gregory Michael Laskowski, Robert Proctor, Curtis Stover, Robert Francis Manning, Victor Hugo Silva Correia, Jared Peter Buhler, Robert Carl Murray, Corey Bourassa, Byron Andrew Pritchard, Jr., Jonathan Russell Ratzlaff
  • Patent number: 11485481
    Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: November 1, 2022
    Assignee: General Electric Company
    Inventors: Lawrence Chih-Hui Cheung, Nikolai N. Pastouchenko, Kishore Ramakrishnan
  • Patent number: 11326519
    Abstract: A frame for a heat engine, the frame including an inner wall extended from an inlet end to an outlet end, the inner wall forming at least in part a core flowpath, the inner wall comprising a plenum formed between an outer portion of the inner wall and an inner portion of the inner wall, wherein a cavity is formed inward of the inner portion of the inner wall, and wherein the inner wall includes a first plenum opening providing fluid communication between the cavity and the plenum, and wherein the inner wall comprises a second plenum opening providing fluid communication between the plenum and the core flowpath.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: May 10, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matti Veikko Kalevi Makela, Emilio Eramo, Christopher Lloyd McKenzie, Apostolos Pavlos Karafillis
  • Patent number: 11313562
    Abstract: A method for operating a burner arrangement of a heat engine, particularly a gas turbine, having a plurality of burners, each having at least one pilot burner and main burner, in which method, on the basis of a preset operation of the heat engine, the total quantity of fuel supplied to the burners is maintained substantially constant in a load-controlled manner: in a first group of burners, for each burner, both the pilot burner as well as the main burner are supplied with fuel; in a second group of burners, the fuel supply to the main burners is interrupted, while the pilot burners continue to be operated; and the fuel quantity remaining as a result of the interruption of the fuel supply to the main burners of the second group is redistributed to the still active main burners of the first group. CO emissions are reduced as a result.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: April 26, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Udo Schmitz, Carsten Seiler, Stefan Wyhnalek
  • Patent number: 11255264
    Abstract: A thermal management system for a heat engine, the system including an forming at least in part a core flowpath and a cavity, wherein the core flowpath and the cavity are separated by a double wall structure formed by at least a portion of inner wall, and wherein the double wall structure includes a plenum. A first opening provides fluid communication between the cavity and the plenum, and a second opening provides fluid communication between the plenum and the core flowpath. The inner wall is configured to receive a first flow of fluid. An outer wall forms a passage extended at least partially around the core flowpath. The outer wall is configured to receive a second flow of fluid fluidly separated from the core flowpath.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: February 22, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matti Veikko Kalevi Makela, Emilio Eramo, Christopher Lloyd McKenzie
  • Patent number: 11149638
    Abstract: An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.
    Type: Grant
    Filed: April 22, 2019
    Date of Patent: October 19, 2021
    Assignee: Rolls-Royce Corporation
    Inventor: Philip R. Owen
  • Patent number: 11111855
    Abstract: A gas turbine engine includes an engine core, a propulsion unit, and a particle separator. The engine core is configured to combust fuel and air to drive rotation of the propulsion unit. The propulsion unit is driven to rotate by the engine core to provide thrust for the gas turbine engine. The particle separator is configured to separate unwanted particles from air being directed toward the engine core.
    Type: Grant
    Filed: May 23, 2019
    Date of Patent: September 7, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier
  • Patent number: 11090600
    Abstract: A method and apparatus for a turbine engine having a compressor section, combustion section, and a turbine section in an axial flow arrangement with a cooling circuit in fluid communication with at least one of the compressor section, combustion section, or turbine section. The method and apparatus further including separating particles from a cooling air that flows through the cooling circuit.
    Type: Grant
    Filed: January 4, 2017
    Date of Patent: August 17, 2021
    Assignee: General Electric Company
    Inventor: Jeffrey Douglas Rambo
  • Patent number: 10988265
    Abstract: Disclosed is an apparatus for protecting an engine of an aircraft to prevent an inlet of an engine of an aircraft from being damaged. The apparatus includes: a protective net attached to an inlet arranged at a front of the engine of the aircraft; and hangers configured to fix the protective net along a side surface of the engine, wherein the protective net includes a plurality of circular fibers concentrically arranged while forming a circle, and a fixing fiber configured to fix an outer peripheral surface of the circular fibers to an outer surface of the engine while being bound to inner surfaces of the circular fibers and passing through a center of the circular fibers.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: April 27, 2021
    Inventors: Yoon-ki Baek, Yu-dam Baek
  • Patent number: 10829237
    Abstract: An inlet barrier filter system for a tiltrotor aircraft comprising a filter duct extending from a filter to a filter outlet, a ram air duct extending from a ram air inlet to an engine where the filter duct connects to the ram air duct at the filter outlet, and a closure member movable between a first position blocking the ram air duct and a second position blocking the filter outlet. In use, the inlet barrier filter system provides for two mutually exclusive air flow paths, one for introducing ram air to the engine while closing off the filter and another air flow path for introducing filtered air to the engine while closing off the ram air duct.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: November 10, 2020
    Assignee: Bell Textron Inc.
    Inventors: James Everett Kooiman, George Ryan Decker, Michael Rinehart, Jeffrey Matthew Williams
  • Patent number: 10822112
    Abstract: Methods for detecting events, e.g., failures, in actuating systems for turbine engines are provided. In one exemplary aspect, a first slope and a second slope are determined. The first slope is determined by calculating the slope of an engine operating characteristic as a function of time prior to an actuation command. The second slope is determined by calculating the slope of the engine operating characteristic as a function of time after the actuation command. Thereafter, a delta slope is generated based at least in part on the difference between the first slope and the second slope. The delta slope is then compared to a predetermined threshold to determine whether a failure in the actuating system has occurred. Turbine engines configured to detect such events are also provided.
    Type: Grant
    Filed: February 14, 2018
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventor: Thomas William Brown
  • Patent number: 10816014
    Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.
    Type: Grant
    Filed: July 25, 2018
    Date of Patent: October 27, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shakeel Nasir, John Schugardt, Mahmoud Mansour, Richard Bonvouloir
  • Patent number: 10738699
    Abstract: An air-inlet particle separator includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to separate particles entrained in an inlet flow moving through the air-inlet particle separator to provide a clean flow of air for a compressor section of a gas turbine engine.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: August 11, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Phillip H. Burnside
  • Patent number: 10584613
    Abstract: A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: March 10, 2020
    Assignee: United Technologies Corporation
    Inventors: Michael S. Stevens, David Richard Griffin
  • Patent number: 10443428
    Abstract: A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 21, 2015
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventor: JinQuan Xu
  • Patent number: 10415576
    Abstract: An ascertainment method for determining a final angle of vanes that are adjustable between an initial angle and the final angle and are part of a row of leading vanes which are arranged upstream of a row of trailing vanes of a compressor in a gas turbine, in order to prevent ice from forming in the compressor. During operation of the gas turbine, a current value of at least one process parameter is determined in a parameter ascertainment step, whereupon the final angle is defined in accordance with the value in a final-angle defining step, an aerodynamic speed being determined as the process parameter.
    Type: Grant
    Filed: November 28, 2014
    Date of Patent: September 17, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Stefan Braun, Tjark Eisfeld, Marco Larson, Ulrich Waltke
  • Patent number: 10393021
    Abstract: An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: August 27, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Crawford F. Smith, III, Victor Oechsle, Philip Snyder
  • Patent number: 10271684
    Abstract: A lid and adaptor assembly capable of being used with at least two food containers such as baking pans having different external dimensions. A pair of clasps are rotatably disposed on opposite side of the lid, each clasp capable of being rotated from an open position to a closed position. A pair of adaptors are provided for connection to the clasps in a first orientation and a second orientation, and each adaptor has a first surface capable of engaging a first food container when the adaptor is in the first orientation, and a second surface capable of engaging a second food container when the adaptor is in the second orientation. A pair of flexible fingers may also be used on the clasp to act as the adaptors to enable use with food containers having different external dimensions.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: April 30, 2019
    Assignee: COLUMBIA INSURANCE COMPANY
    Inventor: E. Mark Harris
  • Patent number: 9599064
    Abstract: A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: March 21, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
  • Patent number: 9382808
    Abstract: There is disclosed a seal assembly (32) for a machine such as a gas turbine engine. The seal assembly has a support structure (38) to which a resiliently deformable seal member (34) is mounted. A seal land (40) is opposingly spaced from the support structure (38) to define a gap therebetween, wherein the height of the seal member (34) in an undeformed condition is greater than the height (36) of the gap such that the seal member is deformingly pressed against the seal land (40) by the support structure to seal the gap therebetween in use. The support structure (38) and/or seal land (40) comprise an actuable member (40; 44; 46), said member being actuable in a direction towards the other of the support structure and seal land to improve the resistance of the seal assembly (32) to an adverse condition in use, such as a fire.
    Type: Grant
    Filed: January 23, 2015
    Date of Patent: July 5, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Carl Hodgkinson
  • Patent number: 9046056
    Abstract: Embodiments include an inlet particle separator system for a gas turbine engine. The inlet particle separator system includes an inertial particle separator that separates incoming air into a cleaned air flow and a scavenge flow. Embodiments may also include an ejector that provides a draw on a scavenge duct and entrains the scavenge flow into a charged flow, e.g., such as the output of a first stage fan. The ejector may have a variable output.
    Type: Grant
    Filed: December 5, 2009
    Date of Patent: June 2, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Bryan H. Lerg
  • Publication number: 20150113938
    Abstract: 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.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Applicant: BHA Altair, LLC
    Inventors: Bradly Aaron Kippel, Stephen David Hiner, Timothy John Nicholas
  • Patent number: 9003759
    Abstract: A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.
    Type: Grant
    Filed: December 1, 2004
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel Suciu, Gary D. Roberge, Brian Merry
  • Patent number: 8997450
    Abstract: 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.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: April 7, 2015
    Assignee: BHA Altair, LLC
    Inventors: Etienne Rene Jarrier, Charles Brake, Paul Sherwood Bryant
  • Patent number: 8984855
    Abstract: 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.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: March 24, 2015
    Assignee: SNECMA
    Inventors: Mickael Delapierre, Herve Gignoux, Gael Loro, Sylvie Wintenberger
  • 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
  • Publication number: 20150040535
    Abstract: 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.
    Type: Application
    Filed: August 7, 2013
    Publication date: February 12, 2015
    Inventors: Zedic Daniel Judd, Yogendra Yogi Sheoran, Devinder N. Katariya, Eduardo Guerra
  • Patent number: 8943791
    Abstract: A separator device is provided for separating dirt particles from a flow of cooling air fed to airfoils of the turbine section of a gas turbine engine. In use the separator device extends across a conduit which bypasses the combustor of the engine to convey pressurized cooling air carrying dirt particles from the compressor section of the engine to openings which direct the air into the airfoils. The separator device is configured to direct a first portion of the impinging cooling air flow away from the openings and to allow a second portion of the impinging cooling air to continue to the openings. The first portion of cooling air has a higher concentration of the coarsest dirt particles carried by the cooling air than the second portion of cooling air.
    Type: Grant
    Filed: September 7, 2010
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Ian Tibbott, Dougal Jackson
  • 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: 20140260183
    Abstract: A gas generator for a reverse core engine propulsion system has a variable cycle intake for the gas generator, which variable cycle intake includes a duct system. The duct system is configured for being selectively disposed in a first position and a second position, wherein free stream air is fed to the gas generator when in the first position, and fan stream air is fed to the gas generator when in the second position.
    Type: Application
    Filed: December 30, 2013
    Publication date: September 18, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph B. Staubach
  • Patent number: 8770512
    Abstract: A plate including a body with an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: July 8, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Robert James Flemming, Eric G. Olsen
  • Patent number: 8756909
    Abstract: 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-axel 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-axel 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.
    Type: Grant
    Filed: July 21, 2010
    Date of Patent: June 24, 2014
    Assignee: The CTFOT Group LLC
    Inventor: Donna Avery
  • Publication number: 20140144123
    Abstract: 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.
    Type: Application
    Filed: November 29, 2012
    Publication date: May 29, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Zedic Daniel Judd, Yogendra Yogi Sheoran, Eduardo Guerra, Yates Wong
  • Patent number: 8721755
    Abstract: 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.
    Type: Grant
    Filed: July 2, 2010
    Date of Patent: May 13, 2014
    Assignee: BHA Altair, LLC
    Inventors: Paul Sherwood Bryant, Alan Edwin Baigent, Paul Christopher James Bissett, John Carl Davies, Evdokia Ivanovna Huddlestone, Etienne Rene Jarrier, Ian Hugh Sutherland
  • Publication number: 20140123621
    Abstract: 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.
    Type: Application
    Filed: February 25, 2013
    Publication date: May 8, 2014
    Applicant: Donaldson Company, Inc.
    Inventor: Donaldson Company, Inc.
  • 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
  • Publication number: 20140077039
    Abstract: An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater.
    Type: Application
    Filed: December 28, 2012
    Publication date: March 20, 2014
    Applicant: Aerospace Filtration Systems, Inc.
    Inventor: Aerospace Filtration Systems, Inc.
  • 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: 8661831
    Abstract: An adaptive vane separator system is provided for use with an inlet filter house of a gas turbine engine system. The vane separator system is coupled to the inlet filter house. The vane separator system includes a slide rail and a plurality of vanes rotatably coupled to the slide rail. The inlet filter house is configured to channel air to an air inlet of a turbine engine. A drive motor is coupled to the vane separator system. The drive motor is operable to selectively move at least one of the vanes to facilitate reducing an amount of moisture channeled through the air inlet.
    Type: Grant
    Filed: January 15, 2010
    Date of Patent: March 4, 2014
    Assignee: BHA Altair, LLC
    Inventors: Etienne Rene Jarrier, Simon Larcombe
  • Patent number: 8590832
    Abstract: An engine inlet flap for mounting on the housing of an air inlet or air inlet duct of an engine of an aircraft, having a first end and a second end arranged in opposition thereto at a distance therefrom in the longitudinal direction of the inlet flap, where the longitudinal direction in the given installation is aligned against the flow direction of the air flowing into the engine; and the inlet flap includes an inlet flap base body with a connector device for a jointed connector for jointed connection of the inlet flap base body to the housing of the air inlet or air inlet duct, with a rotational axis running along the second end, an inlet flap extension piece structurally integrated with the inlet flap base body, with a first and a second lateral piece, which extends from the inlet flap base body on the two opposed lateral edges of the inlet flap running in the longitudinal direction with a number of transverse struts or longitudinal struts, arranged in the leading region of the engine inlet flap.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: November 26, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Lars Bolender, Sébastien Wagnon
  • Patent number: 8590309
    Abstract: According to one aspect of the invention, an ice separating apparatus for a gas turbine engine includes a can having a first end and a tangential inlet proximate the first end of the can to receive a fluid flow within the can, wherein the fluid flow includes fuel and ice. The apparatus also includes a first conduit within the can to receive a separated fuel flow proximate a second end of the can, wherein the fluid flow separates ice from fuel to form the separated fuel flow.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: November 26, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Bruce Paradise
  • Publication number: 20130305684
    Abstract: 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.
    Type: Application
    Filed: May 21, 2012
    Publication date: November 21, 2013
    Inventor: Jacob Peter Mastro
  • Patent number: 8561411
    Abstract: 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.
    Type: Grant
    Filed: September 2, 2009
    Date of Patent: October 22, 2013
    Assignee: United Technologies Corporation
    Inventor: Enzo DiBenedetto
  • Patent number: 8539748
    Abstract: A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.
    Type: Grant
    Filed: December 15, 2006
    Date of Patent: September 24, 2013
    Assignee: General Electric Company
    Inventors: John Paul Petrowicz, Timothy Joseph Higgins, Walter Jackson Tingle
  • Patent number: 8539775
    Abstract: Systems and methods are provided for removing particulate matter from gas turbine engines during operation are provided. Gas turbine engines are also provided. The particulate matter is suspended in a primary gas flow stream passing through an engine flowpath. A flowpath surface of the engine flowpath is electrostatically charged to a first polarity to thereby impart an electrostatic charge of the first polarity to the particulate matter. A bleed discharge duct is electrostatically charged to a second polarity and intersects the engine flowpath to define a bleed air flowpath. The second polarity is opposite to the first polarity. A bleed port is in fluid communication with the bleed discharge duct and has an outlet exterior of the gas turbine engine.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: September 24, 2013
    Assignee: Honeywell International Inc.
    Inventor: Yates Wong