Search Patents
  • Vane segment with ribs
    Patent number: 10876416
    Abstract: There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.
    Type: Grant
    Filed: July 27, 2018
    Date of Patent: December 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jonathan Tebeka, Franco Di Paola, Jasrobin Grewal
  • Shaft assembly for aircraft engine
    Patent number: 10968834
    Abstract: There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labbe, Lukasz Pokrzywa
  • WALL CONSTRUCTION FOR GASPATH TRAVERSING COMPONENT
    Publication number: 20150176425
    Abstract: A gaspath traversing component of a gas turbine engine comprises a wall having an outer edge surface and a thickness relative to the gaspath, the wall having a plurality of layers of composite materials forming the thickness. A wear indication layer is embedded within the plurality of layers of composite material, the wear indication layer being visually contrasting with the composite material. The wear indication layer is positioned interiorly of at least one layer of said plurality of layers of composite material relative to the outer edge surface. A method for attending to a gas traversing component of a gas turbine engine is also provided.
    Type: Application
    Filed: December 20, 2013
    Publication date: June 25, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Stephen CAULFEILD, Kin-Leung CHEUNG, Mathieu POULIN, Bryan William OLVER
  • Retractable washing device
    Patent number: 11306609
    Abstract: A gas turbine engine having an engine core defining a core flow path delimited by an engine casing, a washing device having a spraying member defining a conduit in fluid communication with a source of washing fluid, the spraying member having a spraying section for outputting the washing fluid from the conduit, the spraying member movable relative to the engine casing from a retracted position in which the spraying section is flush with a surface of the engine casing defining said core flow path, and an expanded position in which the spraying section protrudes beyond the surface of the engine casing into the core flow path
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: April 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Richard Ivakitch
  • Fuel injectors and method of purging fuel injectors
    Patent number: 11639687
    Abstract: A method of purging fuel injectors of a gas turbine engine, the fuel injectors fluidly connected to a fuel manifold and having primary and secondary fuel passages fluidly connectable to the fuel manifold, the method includes: selectively fluidly disconnecting one or more of the primary and secondary fuel passages from the fuel manifold; and purging the one or more of the primary and secondary fuel passages by injecting a purging fluid into the one or more of the primary and secondary fuel passages while bypassing the fuel manifold. A fuel injector having two fuel passages, a flow divider valve, and a purging valve is disclosed.
    Type: Grant
    Filed: October 22, 2020
    Date of Patent: May 2, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Joseph Cirtwill, Jian-Ming Zhou, Kian McCaldon
  • Small exit duct for a reverse flow combustor with integrated fastening elements
    Patent number: 10928069
    Abstract: The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Robert Sze
  • Internal combustion engine cooling system
    Patent number: 10920656
    Abstract: A cooling system for an internal combustion engine comprises a fluid circuit having an intercooler, a main cooler and a precooler. The intercooler is configured for receiving coolant and configured for heat exchange relation between the coolant and engine compressed air. The main cooler is configured for receiving the coolant from the intercooler and the internal combustion engine and configured for selectively delivering a first portion of the coolant from the main cooler to the precooler. The precooler is configured to deliver a flow of the coolant to the intercooler. The main cooler and the precooler are configured for cooling the coolant by heat exchange with at least one cooling flow.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: February 16, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andre Julien, Michael Lanktree, Serge Dussault
  • Gas turbine case and reinforcement strut for same
    Patent number: 10227895
    Abstract: A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress dissipation mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: March 12, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Assaf Farah
  • Coupling element for torque transmission in a gas turbine engine
    Patent number: 9297422
    Abstract: A gas turbine engine having a coupling element for coupling a first shaft to a second shaft, the second shaft being substantially axially aligned with the first shaft, the coupling element provided with an exterior surface that engages an opposing interior surface of the first shaft and an interior surface that engages an opposing exterior surface of the second shaft to facilitate torque transfer between the first shaft and the second shaft when rotated together, wherein the coupling element and at least one of the first and second shafts cooperate to define at least one fluid passageway therebetween.
    Type: Grant
    Filed: October 25, 2012
    Date of Patent: March 29, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Barry Barnett, Phillipe Bonniere, Daniel Alecu
  • System and method for engine operation in a multi-engine aircraft
    Patent number: 11668250
    Abstract: Methods and systems for operating a gas turbine engine in a multi-engine aircraft are described. The method comprises operating the gas turbine engine in a standby mode to provide substantially no motive power to the aircraft when another engine of the multi-engine aircraft is operated in an active mode to provide motive power to the aircraft, transitioning the gas turbine engine from the standby mode to the non-standby mode, and applying pulse width modulation to an air switching system of the gas turbine engine while transitioning the gas turbine engine from the standby mode to the non-standby mode.
    Type: Grant
    Filed: November 11, 2019
    Date of Patent: June 6, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Patrick Manoukian
  • Turbine blade airfoil profile
    Patent number: 11512595
    Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
    Type: Grant
    Filed: February 4, 2022
    Date of Patent: November 29, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Fariba Ajalli, Panagiota Tsifourdaris, Michael Paolucci, Othmane Leghzaouni, Stephane Bigras
  • Compressor turbine blade airfoil profile
    Patent number: 8105044
    Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: April 23, 2010
    Date of Patent: January 31, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remo Marini, Dan Olaru, Edward Vlasic, Silvio De Santis, Sophia Levy
  • CONNECTOR FOR MULTI-PHASE CONDUCTORS
    Publication number: 20130288498
    Abstract: A connector for multi-phase conductors. The connector includes conductors for conducting multi-phase currents, and at least one conductive plate corresponding to each phase. Each conductive plate defines apertures for the conductors to pass through, there being at least one aperture in each conductive plate for each respective conductor. Each conductive plate includes at least one connecting member for forming an external electrical connection. Each conductor passes through a respective aperture of each conductive plate. Each conductor is selectively coupled to form electrical connection only to a conductive plate corresponding to the respective phase of the conductor.
    Type: Application
    Filed: April 25, 2012
    Publication date: October 31, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Antwan SHENOUDA, Steve STRECKER, Nathan TOMES
  • Internal fuel manifold having temperature reduction feature
    Patent number: 7703289
    Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: April 27, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
  • Hybrid slinger combustion system
    Patent number: 9874148
    Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: January 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Process for joining powder injection molded parts
    Patent number: 10226818
    Abstract: A process for joining two or more powder injection molded parts by preparing at least two green parts from a feedstock including a binder and an injection powder. Placing the two or more green part into intimate contact, and maintaining the two green parts in intimate contact at a position with a linkage between the at least two green parts to produce an interconnected green assembly. Placing the assembly under shape retaining conditions, melting the binder of the interconnected green assembly under shape retaining conditions to produce a seamless body.
    Type: Grant
    Filed: March 20, 2009
    Date of Patent: March 12, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Orlando Scalzo, Marc Campomanes, Melissa Despres, Alain Bouthillier, Vincent Savaria
  • Positioning assembly and method
    Patent number: 10751808
    Abstract: A method for positioning a rotary part on a machining fixture adapted to hold the rotary part for a machining operation is described. The machining fixture has a center axis and a diaphragm with engaging segments affixed thereto and extending away therefrom. The method includes mounting the rotary part on the machining fixture concentrically about the center axis and adjacent to the engaging segments, and then applying an axial force in a direction substantially parallel to the center axis against the diaphragm. This elastically deforms the diaphragm and radially displaces the contact members of the engaging segments into frictional engagement with a circumferential surface of the rotary part.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: August 25, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yuwen Li, Amr Elfizy
  • Balancing ring geometry
    Patent number: 11480071
    Abstract: An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.
    Type: Grant
    Filed: June 2, 2020
    Date of Patent: October 25, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hugues Pellerin
  • Low profile vane retention
    Patent number: 9506361
    Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: November 29, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruce Fielding, Nathan Tomes, Thomas Veitch
  • Bearing support structure with variable stiffness
    Patent number: 11268405
    Abstract: A method of manufacturing a bearing support structure of a gas turbine engine, includes: obtaining a bearing support and a casing assembly, the casing assembly having first and second casings extending around a central axis and connected together via struts, the bearing support securable to the first casing at attachment points; selecting a distance between the attachment points of the bearing support and the struts as a function of a required stiffness of the bearing support structure; and adjusting a position of the bearing support relative to the casing assembly until the attachment points are distanced from the struts by the selected distance and joining the bearing support to the casing assembly at the attachment points.
    Type: Grant
    Filed: March 4, 2020
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Menheere, Richard Kostka
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