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  • HEALTH MONITORING OF IGNITERS
    Publication number: 20150036781
    Abstract: Methods and associated devices useful for the health monitoring of igniters of gas turbine engines are disclosed. Exemplary embodiments disclosed include the use of an accumulated spark count to an igniter to obtain an indication of wear on the igniter and/or the remaining life of the igniter. An exemplary method disclosed includes: receiving one or more signals indicative of a commanded spark count to the igniter for one or more ignition events; processing the one or more signals indicative of the commanded spark count to the igniter, determining a total accumulated commanded spark count to the igniter; and generating one or more signals indicative of at least one of an estimated wear on the igniter or an estimated remaining life of the igniter based on the total accumulated commanded spark count to the igniter.
    Type: Application
    Filed: August 2, 2013
    Publication date: February 5, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Michael Youssef
  • Composite fan case with nanoparticles
    Patent number: 11391297
    Abstract: A composite case for a gas turbine engine includes an inner structure assembly defining an impact containment zone. The inner structure assembly is configured to circumscribe a plurality of rotatable blades of the gas turbine engine and to receive blade fragments in an event of blade failure. The inner structure assembly includes one or more layers containing a resin impregnated therein, and an outer structure assembly surrounding the inner structure assembly and integrally molded thereon. The outer structure assembly includes one or more layers containing a resin impregnated therein. One or more layers of the inner and the outer structure assemblies include resin reinforced by nanoparticles.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Kin-Leung Cheung
  • Power plant thrust management system for turboprop engines
    Patent number: 10473038
    Abstract: Methods and systems for operating a turboprop engine having a high pressure spool and a low pressure spool rotating independently from one another. Each spool contains at least one compressor stage and the low pressure spool is connected to a propeller. The method comprises determining a target temperature-corrected rotational speed of the low pressure spool for a given set of operating parameters; and controlling a mechanical speed of the low pressure spool to maintain the temperature-corrected rotational speed of the low pressure spool substantially constant throughout at least a portion of a range of a power demand on the turboprop engine.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: November 12, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Keith Morgan, Ghislain Plante, Tania Fauchon
  • Method and system for operating an engine in a multi-engine aircraft
    Patent number: 11168621
    Abstract: Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.
    Type: Grant
    Filed: March 5, 2019
    Date of Patent: November 9, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean McCarthy, Patrick Manoukian, Zachary Mounir Faty, Carmine Lisio, Philippe Beauchesne-Martel
  • Fuel injector for fuel spray nozzle
    Patent number: 10047959
    Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: August 14, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Marenko
  • Composite fan case with integral containment zone
    Patent number: 9032706
    Abstract: A turbofan engine which has a composite fan case surrounding a fan with a plurality of fan blades is disclosed. The composite fan case includes a containment zone having an inner fabric layer composed of resin-impregnated fibers substantially uni-axially oriented in a common angular direction corresponding to a blade release angle of the fan blades. The fan case also includes a composite outer shell and an energy absorbing core disposed radially between the inner fabric layer and the composite outer shell. The energy absorbing core includes non resin impregnated multidirectional fibers.
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: May 19, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Andrew R. Marshall
  • Method for manufacturing a composite guide vane having a metallic leading edge
    Patent number: 11352891
    Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.
    Type: Grant
    Filed: October 19, 2020
    Date of Patent: June 7, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Barry Barnett
  • MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE
    Publication number: 20100132369
    Abstract: A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design.
    Type: Application
    Filed: November 28, 2008
    Publication date: June 3, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON, Lam NGUYEN
  • Method of starting turbine engine from low engine speed
    Patent number: 7861534
    Abstract: A method of starting a turbine engine at a first engine speed value which is lower than a second engine speed value designed for a normal engine starting operation, comprises varying a fuel flow into a combustor of the engine to start the engine in repeatedly alternating speed acceleration and deceleration cycles in order to create an engine speed augmentation in each of the speed acceleration and deceleration cycles, thereby achieving the second engine speed value while preventing the engine from being overheated, and then beginning the normal engine starting operation.
    Type: Grant
    Filed: May 3, 2007
    Date of Patent: January 4, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andrej Terlecki, Graham Bridges, Christopher Day, Mark Laderman
  • Segmented multi-lobe mixer
    Patent number: 10082043
    Abstract: A multi-lobe exhaust mixer has an annular body composed of a plurality of circumferentially adjacent lobe segments. The lobe segments may be made of a ceramic matrix composite material to reduce the weight of the mixer and ensure proper behavior when exposed to high thermal gradients. Each lobe segment may have partial lobes at circumferentially opposed ends thereof and at least one complete lobe therebetween. The partial lobes of the circumferentially adjacent lobe segments combining to conjointly form complete lobes at the junction between the circumferentially adjacent lobe segments. The partial lobes may be nested into each other to dampen vibrations.
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: September 25, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Rene Paquet
  • Multi-rotor rotary engine architecture
    Patent number: 8707929
    Abstract: A multi-rotor internal combustion engine has a plurality of rotary internal combustion units axially distributed along an engine axis. Each unit has a rotor mounted on an eccentric portion of the shaft inside a housing. The housings of adjacent rotary internal combustion units have different angular positions about the engine axis so as to angularly offset the housing from adjacent housings, which may provide for a more uniform temperature distribution around the housings and may also or instead allow optimising of the balancing of pressure induced side loads on the shaft of the rotors.
    Type: Grant
    Filed: October 14, 2011
    Date of Patent: April 29, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Richard Ullyott, André Julien
  • Lubrication system and method, and vortex flow separator for use therewith
    Patent number: 8201664
    Abstract: An aircraft engine lubrication system has a vortex separator, a first pump line having a first pump, an inlet connected to a separated lubricant area at the outlet end of the separator, and an outlet connectable to the engine. A scavenge line is provided for returning lubricant from the engine to an inlet end of the separator. A lubricant tank is connected in fluid flow communication with the separator by a connection line. A second pump line having a second pump has an inlet connected to the lubricant tank and an outlet connected to the separator for pumping lubricant from the tank to the inlet end of the separator.
    Type: Grant
    Filed: January 23, 2008
    Date of Patent: June 19, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sylvain Brouillet, Pierre-Yves Légaré
  • DC bus voltage control
    Patent number: 11649065
    Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for aircraft power. The system includes a DC/DC converter having a DC input and a DC output and a switching circuit connecting the DC input to the DC output operable to vary voltage at the DC output. A control module is operatively connected to the switching circuit for variable control of the DC output. The control module includes machine readable instructions to cause the control module to receive input indicative of altitude and control the switching circuit to vary voltage of the DC output as a function of environmental conditions such as altitude and humidity. In embodiments the altitude sensor is operatively connected to the controller.
    Type: Grant
    Filed: August 13, 2021
    Date of Patent: May 16, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Richard Freer
  • Deflector for a gas turbine strut and vane assembly
    Patent number: 8182204
    Abstract: A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: May 22, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Mohamad Sleiman, Panagiota Tsifourdaris
  • Blade for a gas turbine engine
    Patent number: 9909425
    Abstract: A gas turbine airfoil blade comprises an airfoil having a leading edge and a trailing edge defining fore and aft points of an airfoil chord relative to a flowpath direction. The airfoil extends generally radially from a root to a tip, the root of the airfoil intersecting a platform of the blade. A body of the airfoil is composed of a plurality of airfoil sections stacked along a stacking line extending radially from the platform. A root airfoil section being the one of said airfoil sections intersecting the platform, the trailing edge at the root airfoil section extending to intersect the platform chordwise aft of the trailing edge of the airfoil section immediately radially outwardly adjacent to the root airfoil section.
    Type: Grant
    Filed: October 31, 2011
    Date of Patent: March 6, 2018
    Assignee: PRATT & WHITNEY CANADA CORPORATION
    Inventor: Paul Stone
  • BUFFER FLUID DELIVERY SYSTEM AND METHOD FOR A SHAFT SEAL OF A GAS TURBINE ENGINE
    Publication number: 20230304444
    Abstract: Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.
    Type: Application
    Filed: January 3, 2023
    Publication date: September 28, 2023
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel ALECU, David MENHEERE
  • OIL SCAVENGE SYSTEM HAVING CHURNING DAMPER FOR GAS TURBINE ENGINES
    Publication number: 20120181113
    Abstract: An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation.
    Type: Application
    Filed: March 29, 2012
    Publication date: July 19, 2012
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel T. ALECU, Kenneth PARKMAN
  • Method and system for sensing a fluid level associated with an engine
    Patent number: 11635321
    Abstract: Methods and systems for sensing a fluid level associated with an engine are described. The method comprises generating an input signal and applying the input signal to a resistive portion and a capacitive portion of a fluid level sensing device, measuring a first varying output of the resistive portion of the fluid level sensing device through a first channel of a controller of the engine, measuring a second varying output of the capacitive portion of the fluid level sensing device through a second channel of the controller of the engine, and translating at least one of the first varying output and the second varying output into a level of fluid and outputting the level of fluid.
    Type: Grant
    Filed: January 16, 2020
    Date of Patent: April 25, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Sarmad Khan
  • Retaining ring arrangement for a rotary assembly
    Patent number: 8491267
    Abstract: A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: July 23, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David F. Glasspoole, Bruno Chatelois
  • Gas turbine auxiliary power unit
    Patent number: 11008116
    Abstract: A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.
    Type: Grant
    Filed: April 15, 2019
    Date of Patent: May 18, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, Daniel Alecu, Enzo Macchia
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