Search Patents
  • Gas turbine engine exhaust ejector/mixer
    Patent number: 9745919
    Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: August 29, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Turbine stator outer shroud cooling fins
    Patent number: 10822987
    Abstract: A stator of a gas turbine engine is provided. A static shroud of the stator defines a platform having a radially outer surface. An impingement plate has impingement holes extending therethrough, and the impingement plate is radially spaced apart from the radially outer surface of the platform. The impingement holes are configured to direct a high-speed cooling air flow transversally to the radially outer surface of the stator shroud. A plurality of protrusions project away from the radially outer surface of the platform along a protrusion axis. The protrusions have a cruciate cross-sectional shape when viewed in a plane normal to the protrusion axis. A method of cooling a stator of a gas turbine engine is also provided.
    Type: Grant
    Filed: April 16, 2019
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Tardif, Michael Papple, Jason Gillespie
  • Integrated strut-vane
    Patent number: 10221707
    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: Grant
    Filed: March 7, 2013
    Date of Patent: March 5, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Vincent Paradis, Edward Vlasic, Panagiota Tsifourdaris
  • System and method for aircraft propeller control
    Patent number: 10392099
    Abstract: A system and method for controlling an aircraft propeller are provided. In anticipation of a condition in which a parameter related to an angle of a plurality of blades of the propeller reaches a value beyond a predetermined threshold, a first control signal is output comprising instructions to actuate a feather valve operatively coupled to an actuator configured to adjust the angle in response to hydraulic pressure, thereby causing the feather valve to provide the hydraulic pressure to the actuator and the angle to be adjusted for bringing the parameter towards the threshold. When the parameter reaches the predetermined threshold, a second control signal is output comprising instructions to hold the feather valve at a position in which the hydraulic pressure is withheld from the actuator, thereby causing the angle to remain unchanged.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: August 27, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Reza Pedrami, James Jarvo
  • Tandem electric machine arrangement
    Patent number: 8476798
    Abstract: The tandem electric machine arrangement comprises an outside rotor having two axially spaced-apart sets of circumferentially-disposed permanent magnets. It also comprises an inside stator having at least two electrically-independent windings, the at least two windings axially spaced apart from one another and disposed relative to the magnet sets to thereby be magnetically coupled to a respective one of the sets of permanent magnets during rotation of the rotor. One of the rotor and the stator is provided in two separate pieces, each piece supported from opposite axial sides of the electric machine relative to one another. The other of the rotor and the stator is supported from substantially centrally of the two pieces.
    Type: Grant
    Filed: November 28, 2008
    Date of Patent: July 2, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan Dooley, Joseph Brand
  • Overthrust protection system and method
    Patent number: 10487752
    Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: November 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Janusz Fiedler, Tatjana Pekovic, Dave Sellors, Amandeep Singh Chahal
  • Internal combustion engine with common rail injection
    Patent number: 10267217
    Abstract: An internal combustion engine includes first and second common rails each having a metering or pressure regulating valve, with the valves settable at different pressure values from one another. Rotors are each sealingly and rotationally received within a respective cavity to define at least one combustion chamber of variable volume. The engine includes first and second fuel injectors for each of the rotors. Each first fuel injector is in fluid communication with the first common rail and each second fuel injector is in fluid communication with the second common rail. A method of feeding fuel in an internal combustion engine is also provided.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: April 23, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, Edwin Schulz
  • Axial load damping system for rotor shaft
    Patent number: 8696312
    Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: April 15, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Charles Faubert, André D. Leblanc
  • BLADE OUTER AIR SEAL ANTI-ROTATION
    Publication number: 20110044803
    Abstract: A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other.
    Type: Application
    Filed: July 20, 2010
    Publication date: February 24, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Bruno Chatelois
  • Diffuser case removal apparatus and method
    Patent number: 9133858
    Abstract: A method and apparatus is provided for removing a centrifugal compressor diffuser case from a turbofan gas turbine engine case which may be used while the engine is installed on an aircraft or when the engine has been removed from the aircraft. The tool includes movable gripping members at least one force member for exerting a pushing action on the engine structure on which the diffuser case is mounted the method includes gripping a peripheral portion of the diffuser case and applying an axial pushing force on the case relative to the engine case to thereby overcome an interference fit between the diffuser case and the engine case.
    Type: Grant
    Filed: June 19, 2013
    Date of Patent: September 15, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Enzo Macchia, Geoffrey Henriksen, Robin Hardstaff, Ian Chandler, Tim Bedard
  • Tandem electric machine arrangement
    Patent number: 8710708
    Abstract: The tandem electric machine arrangement comprises an outside rotor having two axially spaced-apart sets of circumferentially-disposed permanent magnets. It also comprises an inside stator having at least two electrically-independent windings, the at least two windings axially spaced apart from one another and disposed relative to the magnet sets to thereby be magnet coupled to a respective one of the sets of permanent magnets during rotation of the rotor. One of the rotor and the stator is provided in two separate pieces, each piece supported from opposite axial sides of the electric machine relative to one another. The other of the rotor and the stator is supported from substantially centrally of the two pieces.
    Type: Grant
    Filed: May 16, 2013
    Date of Patent: April 29, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan Dooley, Joseph Brand
  • Static take-off port
    Patent number: 11300002
    Abstract: A duct for a gas turbine engine, the duct has a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow and a scoop downstream of the opening relative to the direction of the airflow.
    Type: Grant
    Filed: December 9, 2019
    Date of Patent: April 12, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ivan Sidorovich Paradiso, Daniel Alecu
  • Exhaust gas discharge system and plenum
    Patent number: 8221073
    Abstract: An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: July 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ian Macfarlane, Zenon Szlanta
  • Active clearance control system and method for an aircraft engine
    Patent number: 11655725
    Abstract: There is provided a system and a method for controlling a tip clearance between a turbine casing and turbine blade tips of an aircraft engine. At least one operational parameter of the aircraft engine is obtained. Based on the at least one operational parameter, a current value of the tip clearance and a target value of the tip clearance are determined. A limiting factor to be applied to the target value of the tip clearance is computed. The limiting factor is applied to the target value of the tip clearance to obtain a tip clearance demand for the aircraft engine. A tip clearance control apparatus of the aircraft engine is controlled based on a difference between the current value of the tip clearance and the tip clearance demand.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: May 23, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jeffrey Poissant, Cristina Crainic
  • Feedback device with differing magnetic permeability zones
    Patent number: 11371825
    Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
    Type: Grant
    Filed: January 9, 2020
    Date of Patent: June 28, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Durand, Richard Kudrna, Ian Farrell
  • Composite fire shield
    Patent number: 8222165
    Abstract: A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fiber cloth impregnated with a sacrificial resin which has a melting point that is below that of the fiber cloth. When exposed to fire, the fiber cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed.
    Type: Grant
    Filed: October 27, 2008
    Date of Patent: July 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Bryan William Olver
  • Aircraft power plant
    Patent number: 11866181
    Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.
    Type: Grant
    Filed: September 15, 2021
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Serge Dussault
  • Bearing support with frangible tabs
    Patent number: 11499447
    Abstract: A gas turbine engine has: an engine shaft rotatable about a rotation axis; at least two bearings spaced apart from one another along the rotation axis, the at least two bearings having inner races for rotation with the engine shaft, outer races, and rolling elements disposed radially between the inner races and the outer races; a bearing support extending axially along the rotation axis from one of the at least two bearings to the other, the bearing support secured to both of the outer races of the at least two bearings, the bearing support secured to a structural case of the gas turbine engine via frangible tabs.
    Type: Grant
    Filed: January 15, 2020
    Date of Patent: November 15, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, François Doyon
  • Machine tool certification for part specific working volume
    Patent number: 9971337
    Abstract: A method for machining a selected part with a machine tool, comprises obtaining a master part replicating at least a portion of a geometry of a selected part. The master part is loaded in a machine tool. A signature of the machine tool is defined by measuring at least dimensional data of the master part relative to the machine tool, the dimensional data being limited to a selected-part-specific working volume substantially smaller than a complete working volume of the machine tool. The machine tool is certified as being within tolerances to machine the selected part within the working volume, using the dimensional data of the signature. The selected part is machined from a workpiece with the machine tool.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: May 15, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mario Blais, Philippe St-Jacques
  • Machine tool certification for part specific working volume
    Patent number: 10852709
    Abstract: A method for machining a selected part with a machine tool, comprises obtaining a master part replicating at least a portion of a geometry of a selected part. The master part is loaded in a machine tool. A signature of the machine tool is defined by measuring at least dimensional data of the master part relative to the machine tool, the dimensional data being limited to a selected-part-specific working volume substantially smaller than a complete working volume of the machine tool. The machine tool is certified as being within tolerances to machine the selected part within the working volume, using the dimensional data of the signature. The selected part is machined from a workpiece with the machine tool.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: December 1, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mario Blais, Philippe St-Jacques
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