Search Patents
  • Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
    Patent number: 7234304
    Abstract: A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.
    Type: Grant
    Filed: October 23, 2002
    Date of Patent: June 26, 2007
    Assignee: Pratt & Whitney Canada Corp
    Inventor: Hisham Alkabie
  • Centrifugal separator
    Patent number: 10729992
    Abstract: A centrifugal separator for separating gas and liquid from a gas-liquid mixture, the centrifugal separator comprising: a housing having a cavity and a gas-liquid mixture inlet leading tangentially into the cavity along an inlet path to form a vortex therein, a separated gas outlet and a separated liquid outlet; and a rotor rotatably mounted to the housing inside the cavity in a manner to be freely rotatable around a rotation axis, the rotor having a hub extending axially along said axis, the rotor having a plurality of vanes extending radially from the hub inside the cavity, the vanes being disposed in the inlet path in a manner so that the rotor is rotated by the gas-liquid mixture during use.
    Type: Grant
    Filed: August 28, 2017
    Date of Patent: August 4, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Filip Pulter, Krystian Mazur
  • Gas turbine engine casing arrangement
    Patent number: 11168828
    Abstract: A gas turbine engine includes a casing including a plurality of interconnected casing segments defining an outer surface of the casing. One of the casing segments is a gearbox segment enclosing a gearbox and having a gearbox flange extending radially outwardly from the outer surface of the casing. The engine includes a bearing housing enclosing at least one bearing and having an annular body with an inner segment disposed within the casing. The annular body having an extension segment extending radially outwardly from the inner segment to a bearing housing flange disposed radially-outwardly of the outer surface of the casing. The bearing housing flange is engageable with the gearbox flange to removably mount the gearbox segment to the bearing housing.
    Type: Grant
    Filed: May 2, 2017
    Date of Patent: November 9, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Ian A. Macfarlane
  • Dual cycle intercooled hydrogen engine architecture
    Patent number: 11542869
    Abstract: In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.
    Type: Grant
    Filed: May 27, 2021
    Date of Patent: January 3, 2023
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Scott Smith
  • Compressor diffuser with plasma actuators
    Patent number: 11125247
    Abstract: There is disclosed a centrifugal compressor including an impeller rotatable about an axis and a diffuser downstream of the impeller. The diffuser has walls delimiting flow passages. Plasma actuators are positioned adjacent the walls and are operatively connectable to a source of electricity. The plasma actuators have a first electrode, a second electrode, and a dielectric layer therebetween. The first electrode is upstream of the second electrode. The first electrode is exposed to the flow passage. The second electrode is shielded from the flow passage by the dielectric layer. The plasma actuators are operable to generate an electric field through the dielectric layer. The plasma actuators are located closer to inlets of the flow passage than to outlets of the flow passages. A method of operating the compressor is disclosed.
    Type: Grant
    Filed: November 16, 2018
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Martin Drolet
  • Plug device for gas turbine engine shaft
    Patent number: 8967202
    Abstract: A device for plugging an axially-aligned bore in a shaft of a gas turbine engine comprises a plug. A sealing body of the plug is sealingly received in a bore of the shaft. Legs project from the sealing body and are displaceable between a normally contracted position in which the legs are radially inward relative to a periphery of the bore, and a deployed position in which the legs project radially outward and engage with shaft projections within the bore of the shaft. A wedge is operatively engaged to the plug for movement of the wedge relative to the plug. The wedge comprises a portion in operative contact with the legs of the plug unit to displace the legs between positions as a response to movement of the wedge. A gas turbine engine and a method for plugging a shaft are provided.
    Type: Grant
    Filed: September 22, 2011
    Date of Patent: March 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Marcin Rejman
  • Vane for gas turbine engine
    Patent number: 11454127
    Abstract: A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.
    Type: Grant
    Filed: November 22, 2019
    Date of Patent: September 27, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tammy Yam, Tibor Urac, Paul Aitchison
  • Oil nozzle health detection using liquid flow test
    Patent number: 11885710
    Abstract: A flow measuring system for one or more oil nozzles of a lubrication system of an aircraft engine comprises an external supply of a testing liquid and a pump fluidly connecting the external supply of the testing liquid to an inlet of the lubrication system via a first conduit. The inlet to the lubrication system is disposed upstream of the one or more oil nozzles. A second conduit fluidly connects an outlet of the lubrication system to the external supply of the testing liquid. The outlet of the lubrication system is disposed downstream of the one or more oil nozzles. A flow measuring device is operable to measure a flow resistance through the one or more oil nozzles.
    Type: Grant
    Filed: June 8, 2022
    Date of Patent: January 30, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Steven Farber, Patrick E Paradis, Lukasz Jost, Piotr Grabski, Marcin Siedlarz, Piotr Mazur, Rafał Panek
  • Fuel nozzle retaining bracket
    Patent number: 10823073
    Abstract: A fuel supply assembly for a gas turbine engine includes at least one fuel transfer tube, at least one fuel nozzle, and at least one retaining bracket. The transfer tube and the nozzle are assembled in fluid communication with one another. The retaining bracket is fixedly attached to one of the nozzle and the transfer tube and displaceable relative thereto between a first position and a second position. A free end of the bracket is engageable with the other of the fuel nozzle and the transfer tube to retain the transfer tube to the fuel nozzle when the bracket is in the second position. The retaining bracket is disengaged from one of the fuel nozzle and the transfer tube in the first position so that the fuel nozzle and the transfer tube are disengageable from one another.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Ryan Miskie
  • Plate cooler for aircraft electronic components
    Patent number: 11412640
    Abstract: A heat exchanger for aircraft electronic components includes a first plate having channels arranged with side-by-side channel inlets fed from a common fluid supply manifold extending to the channel inlets from a manifold inlet. The channel inlets include a first set of inlets spaced further away from the manifold inlet than a second set of inlets. The fluid supply manifold has a flow divider positioned fluidly between the manifold inlet and the channel inlets. The flow divider is configured in use to direct heat exchange fluid entering the manifold from the manifold inlet preferentially toward the first set of inlets. A second plate is coupled with the first plate to seal the channels and the fluid supply manifold.
    Type: Grant
    Filed: August 13, 2019
    Date of Patent: August 9, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dana Tomescu
  • Fast engine re-start for multi-engine system and method
    Patent number: 11859554
    Abstract: A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.
    Type: Grant
    Filed: July 29, 2021
    Date of Patent: January 2, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Coutu, Philippe Beauchesne-Martel
  • Gas turbine engine component with integral heat exchanger
    Patent number: 11873758
    Abstract: An apparatus is provided for a gas turbine engine. This apparatus includes a vane array and a heat exchanger integrated with the vane array. The vane array includes an inner platform, an outer platform and a plurality of vanes. The inner platform extends circumferentially about a centerline and forms an inner peripheral boundary of a flowpath through the vane array. The outer platform extends circumferentially about the centerline and forms an outer peripheral boundary of the flowpath through the vane array. The vanes extend across the flowpath between the inner platform and the outer platform. The heat exchanger includes a passage following a tortuous trajectory along a first wall of the vane array.
    Type: Grant
    Filed: October 28, 2022
    Date of Patent: January 16, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric S. Durocher, Gabriel Naccache
  • GRINDING WHEEL AND METHOD
    Publication number: 20150202742
    Abstract: A grinding wheel including an impeller structure for circulating coolant within the wheel defining a plurality of grooves. An angle between a second wall of each groove and a tangent to the outer circumference adjacent the groove outlet is defined based on the desired coolant flow rate, the predetermined wheel rotational speed, the radius of the outer circumference of the impeller structure, the combined surface area of the groove outlets, and a desired angle of exit of the coolant being at most 15 degrees. Also, a wheel is disclosed where the angle of the second wall of each groove is defined based on the desired coolant flow rate, the combined surface area of the groove outlets, the tangential speed of the wheel, and a value of n being at least 0.9 and less than 1. A method for distributing a coolant to a grinding site is also discussed.
    Type: Application
    Filed: January 20, 2014
    Publication date: July 23, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Amr ELFIZY, François PERRON
  • Method and system for wire electro-discharge machining a component
    Patent number: 11338381
    Abstract: Methods and systems for wire-electro discharge machining of components are described. The method comprises machining a first component by moving a wire-EDM electrode along a first set of cutting paths associated with a plurality of cutting passes, the cutting paths determined based on a desired profile shape of the component, obtaining a cutting parameter of the first component post-machining, determining a first modified cutting path for a second component based on the cutting parameter, and machining the second component by moving the wire-EDM electrode along a second set of cutting paths associated with the plurality of cutting passes, the second set of cutting paths comprising the first modified cutting path.
    Type: Grant
    Filed: July 26, 2019
    Date of Patent: May 24, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Joel Jean, Ghislain Hardy, Visal Ing
  • Nested channel ducts for nozzle construction and the like
    Patent number: 7028484
    Abstract: A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from an inlet to an outlet. At least a first sealing member is disposed within the channel and divides the channel into at least a first discrete conduit and a second discrete conduit. A second sealing member encloses the channel to define the second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.
    Type: Grant
    Filed: August 30, 2002
    Date of Patent: April 18, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, John Sokalski, Claude Raymond Pelletier
  • SYSTEM AND METHOD FOR CONDITIONING NOISY SIGNALS
    Publication number: 20150006058
    Abstract: There is provided a system and method for conditioning a noisy signal. A sensing signal is received during each one of a plurality of successive control cycles, the sensing signal comprising a measurement component indicative of a measurement of at least one engine parameter and a noise component. A curve-fitting technique is applied to the received sensing signal for filtering thereof to attenuate the noise component, the filtering comprising, during a first one of the plurality of the control cycles, asymmetrically filtering the sensing signal received during the first control cycle, thereby generating filtered data, and, during a second control cycle subsequent to the first control cycle, symmetrically filtering the sensing signal received during the first control cycle, thereby generating corrected data.
    Type: Application
    Filed: November 1, 2013
    Publication date: January 1, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Kim GEORGE, Poi Loon TANG
  • Foam wall combustor construction
    Patent number: 7263772
    Abstract: A method of manufacturing a composite wall with an open cell metal foam core layer bonded to an inner cladding layer and an outer cladding layer. The method involves: creating a core substrate of open cell gas permeable foam in a chosen shape; impregnating the open cell foam substrate with metal vapour and depositing a porous layer of metal on exposed internal and external surfaces of the substrate thereby forming the open cell metal foam core through metal vapour deposition; and forming the inner and outer cladding layers upon the metal foam core through spray application of metal or ceramic.
    Type: Grant
    Filed: June 18, 2004
    Date of Patent: September 4, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Michael Dowhan, Joseph Brand
  • Flow mixer stiffener ring segmented springs
    Patent number: 10801441
    Abstract: A gas turbine engine comprises a main gas path having an inner flow boundary wall and an outer flow boundary wall. A turbine exhaust case inner body defines a portion of the inner flow boundary wall of the main gas path. A lobed exhaust mixer defines a portion of the outer flow boundary wall of the main gas path. A stiffener ring is interconnected to at least a number lobes of the lobed exhaust mixer by a plurality of circumferentially spaced-apart struts extending through the main gas path. The stiffener ring is attached to the turbine exhaust case inner body by flexible features, such as circumferentially spaced-apart spring blades.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: October 13, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Summers-Lepine, Philippe Boyer, Assaf Farah, Daniel Coutu
  • Turbofan bypass air cooled oil cooler fairings
    Patent number: 9982630
    Abstract: A cooler assembly disposed in and cooled by an air stream according to one embodiment includes a cooler matrix and a fairing. The fairing assembly is disposed generally around the cooler matrix and includes side fairing-housings, first and second side fairing-housings being joined to one another at respective leading and trailing edges, the leading edges partially defining a cooler inlet and the trailing edges partially defining a cooler outlet, the first and second side fairing-housing trailing edges angled transversely toward each other to define a trapezoidal shape for the outlet.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: May 29, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Remo Marini, Roberto Marrano, Adam Trumpour
  • Detection of abnormal engine starts
    Patent number: 11560850
    Abstract: Methods and systems for detecting an abnormal start of a gas turbine engine are described. Speed data points are sampled from a sensor associated with the engine in accordance with a sampling rate, the speed data points being indicative of a rotational speed of a gas generator of the engine during engine start. The speed data points are continuously stored during the engine start. Previously-obtained speed data points which are older than an abnormal start delay are discarded. An abnormal engine start event is detected by comparing a first one of the stored speed data points with a second one of the stored speed data points, the second one of the stored speed data points obtained before the first one.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: January 24, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Farzad Baghernezhad, Antoine Pierre
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