Search Patents
  • Internal combustion engine with common rail pilot and main injection
    Patent number: 9200563
    Abstract: An internal combustion engine including a pilot subchamber, a pilot fuel injector having a tip in communication with the pilot subchamber, an ignition element positioned to ignite fuel within the pilot subchamber, and a main fuel injector spaced apart from the pilot fuel injector. The engine includes a common rail in fluid communication with the main fuel injector and with the pilot fuel injector and a pressure regulating mechanism in fluid communication with the common rail for regulating a fuel pressure therein. A method of combusting fuel in an internal combustion engine is also provided.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: December 1, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Jean Thomassin
  • Turbine shroud cooling
    Patent number: 10570773
    Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: February 25, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
  • LOW ENERGY PLASMA COATING
    Publication number: 20140255613
    Abstract: A method of coating an aluminum alloy or magnesium alloy component, including cleaning and drying surfaces of the component to be coated; suspending a powdered coating material in a carrier gas and feeding the suspended powdered coating material through a plasma torch in a flowing gas; heating the coating material in the plasma torch to a molten or semi-molten state using a nominal power below 25 kW; and depositing the coating material with the plasma torch directly on the surfaces to be coated. The component may be made of a magnesium alloy containing at one or more of zinc, cerium and zirconium, or of an aluminum alloy containing one or more of magnesium, silicon, copper and chromium. The powder material may be made in majority of aluminum.
    Type: Application
    Filed: March 5, 2013
    Publication date: September 11, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Pierre VERRIER
  • Journal bearing assembly with dual oil cavities
    Patent number: 10935076
    Abstract: A gas turbine engine comprising a gearbox, the gearbox having gear(s). A journal bearing assembly rotatably supports the gear, the journal bearing assembly having at least a pin, and a journal having a tubular body defining a pin-receiving inner cavity having an inner surface, a first cavity and a second cavity defined in the inner surface of the pin-receiving inner cavity, a rib support located between the first cavity and the second cavity, the rib support being aligned with a longitudinal center of the tubular body, with the first cavity and the second cavity on opposed axial sides of the rib support.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: March 2, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Martin, Louis Brillon, Julien Simard-Bergeron
  • Apex and face seals with rotary internal combustion engine
    Patent number: 9850758
    Abstract: A rotor for a rotary internal combustion engine with a first face seal biased axially outwardly away from the first end face has opposed curled ends abutting a first end seal of a respective one of the adjacent apex portions, and a second face seal biased axially outwardly away from the second end face has opposed curled ends abutting a second end seal of a respective one of the adjacent apex portions. A rotary internal combustion engine and a method of sealing chambers of a Wankel engine are also discussed.
    Type: Grant
    Filed: January 27, 2015
    Date of Patent: December 26, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Jean Thomassin, Sebastien Bolduc, David Gagnon-Martin
  • Shaft shear detection through shaft oscillation
    Patent number: 10228304
    Abstract: There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed, the oscillation wave having a wave modulation frequency and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.
    Type: Grant
    Filed: January 18, 2016
    Date of Patent: March 12, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jeffrey Bernard Heyerman, Antwan Shenouda, Michael Krynski, Poi Loon Tang
  • Rotor having crack mitigator
    Patent number: 11795821
    Abstract: A rotor for an aircraft engine, has: a hub extending circumferentially about a central axis, the hub having a bore, a gaspath-facing surface located radially outwardly of the bore relative to the central axis, a first face extending from the bore to the gaspath-facing surface, and a second face opposite the first face and extending from the bore to the gaspath-facing surface; blades circumferentially distributed about the central axis, the blades protruding away from the gaspath-facing surface of the hub; and a crack mitigator located on the first face, the crack mitigator extending circumferentially relative to the central axis, the crack mitigator extending axially from a baseline surface of the first face.
    Type: Grant
    Filed: April 8, 2022
    Date of Patent: October 24, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dikran Mangardich
  • Method of making a structural reinforcement strut for a turbine exhaust case of a gas turbine engine
    Patent number: 8561415
    Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.
    Type: Grant
    Filed: March 1, 2013
    Date of Patent: October 22, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mike Fontaine, Rene Paquet, Jean Fournier
  • Normally open reverse flow flapper valve
    Patent number: 7114519
    Abstract: A fluid flow actuated valve for controlling the fluid flow in a conduit comprises a support structure adapted to be mounted within the conduit and at least one flap member pivotally mounted to the support structure. The at least one flap member is pivotable between an first position for a minimum fluid flow and a second position for a maximum fluid flow. A torsion spring is attached to the at least one flap member to urge the same to pivot against a fluid pressure differential, from the first position to the second position when the fluid pressure differential is smaller than a predetermined level.
    Type: Grant
    Filed: December 17, 2004
    Date of Patent: October 3, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Paul Archibald Aitchison, Patrick David Germain, Henry Smith
  • IMPELLER REAR CAVITY THRUST ADJUSTOR
    Publication number: 20080193277
    Abstract: An apparatus for adjusting a thrust load on a rotor assembly of a gas turbine engine includes an impeller rear cavity defined between a rear face of an impeller of the rotor assembly and a stationary wall spaced axially apart from the rear surface of the impeller. A pressurized air flow with a tangential velocity is introduced into the impeller rear cavity at a tip of the impeller to pressurize the cavity. Means are provided in the cavity for directly interfering with the tangential velocity of the pressurized air flow to affect an average static pressure of the pressurized air flow within the cavity in order to adjust the thrust load on the rotor assembly caused by the average static pressure in the cavity.
    Type: Application
    Filed: February 14, 2007
    Publication date: August 14, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Pierre-Yves LEGARE
  • Oil tank installation in gas turbine engine
    Patent number: 10816007
    Abstract: Oil tanks for gas turbine engines and associated assembly methods are disclosed. In one exemplary embodiment, an oil tank is configured to be installed to occupy a radially-inner space defined by an annular radial air inlet duct of a reverse flow gas turbine engine. The oil tank may comprise a first tank portion and a second tank portion assembled together to cooperatively define an interior volume of the tank. An optional intermediate spacer may be disposed between the first tank portion and the second tank portion in order to form an oil tank of a larger size.
    Type: Grant
    Filed: November 11, 2016
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Desjardins, Francis Bonacorsi, Keith Morgan
  • Bleed valve actuating system for a gas turbine engine
    Patent number: 7850419
    Abstract: The bleed valve actuating system is for use in a gas turbine engine. The system comprises an actuator mounted adjacent the engine case and having a main actuation axis extending generally parallel to a surface of the engine case. A drive rod extends from the bleed valve to the actuator generally perpendicularly with reference to the main actuation axis of the actuator. The drive rod connected to the actuator via a linkage mechanically connects the actuator to the drive rod. The linkage is configured to convert axial motion of the actuator along the main actuation axis into generally perpendicular motion of the drive rod.
    Type: Grant
    Filed: November 30, 2006
    Date of Patent: December 14, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ljubisa Vrljes, Christopher Daniel Ongley, Zoran Markovic
  • INTEGRATED STRUT-VANE
    Publication number: 20140255159
    Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.
    Type: Application
    Filed: March 7, 2013
    Publication date: September 11, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: VINCENT PARADIS, EDWARD VLASIC, PANAGIOTA TSIFOURDARIS
  • Turbine shroud segment with inter-segment overlap
    Patent number: 10328490
    Abstract: A method of manufacturing a turbine shroud segment for a gas turbine engine comprises: metal injection molding (MIM) a shroud segment body with a groove defined in a first lateral side thereof and with a flow restrictor projecting integrally from an opposite second lateral side thereof. The groove is oversized relative to the flow restrictor to provide for a clearance fit between the flow restrictor and the groove of adjacent turbine shroud segments when assembled together in a ring formation. The shroud segment body with the integrated flow restrictor are then subjected to debinding and sintering operations.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 25, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Turbine blade airfoil profile
    Patent number: 11572789
    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: November 11, 2021
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Constantinos Ravanis, Vincent Paradis, Eduardo Hawie, Michael Papple, Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Philippe Boyer, Jasrobin Grewal
  • Multi-phase cable
    Patent number: 9991029
    Abstract: A multi-phase cable, the cable including a plurality of conductors for conducting currents of two or more different phases, each phase being associated with one or more conductors and each conductor being associated with one respective phase. Each conductor has a cross-section with at least one dimension that is sized to decrease a skin effect of the conductor at a maximum or nominal operation frequency of the conductor. The conductors are arranged to permit free air cooling of the cable on at least two sides of each conductor, and such that each conductor of a given phase has, as immediate neighbors, only conductors of one or more different phases.
    Type: Grant
    Filed: November 27, 2012
    Date of Patent: June 5, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Antwan Shenouda
  • Gas turbine engine exhaust system
    Patent number: 10508599
    Abstract: An exhaust system for a gas turbine engine, such as an APU, comprises a pressure vessel having an annular wall circumscribing an exhaust plenum. The annular wall is composed of an arrangement of individual tubes assembled side-by-side around a central axis of the exhaust plenum. The tubes are fed with pressurized cooling air, such as P3 air. A heat exchanger in heat transfer relationship with the exhaust gases flowing through the exhaust plenum receives air from the tubes. The heat transferred from the exhaust gases to the air circulated through the heat exchanger may be used to provide pre-heated air to the engine combustor.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: December 17, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David H Menheere, Adam Trumpour
  • ELECTRIC DISTRIBUTED PROPULSION USING EXHAUST RECOVERY POWER
    Publication number: 20220297843
    Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.
    Type: Application
    Filed: March 19, 2021
    Publication date: September 22, 2022
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Todd A. Spierling
  • MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE
    Publication number: 20100135770
    Abstract: A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine.
    Type: Application
    Filed: November 28, 2008
    Publication date: June 3, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON, Lam NGUYEN
  • Machine having a liquid lubrication system and a shaft
    Patent number: 11692466
    Abstract: A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.
    Type: Grant
    Filed: May 30, 2019
    Date of Patent: July 4, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Dana Tomescu, Daniel Alecu
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