Patents Assigned to Pratt & Whitney Canada Corp.
  • Patent number: 10669854
    Abstract: An impeller comprises a hub and blades extending therefrom. The blades include splitter blades interspersed between full blades. First flow channels are defined between pressure sides of the splitter blades and suction sides of the full blades. Second flow channels are defined between suction sides of the splitter blades and pressure sides of the full blades. A width of the first flow channels at leading edges of the splitter blades and at the hub is less than a width of the second flow channels at the leading edges of the splitter blades and at the hub. The width of the first flow channels at the leading edges of the splitter blades and at the tips is more than the width of the second flow channels at the leading edges of the splitter blades and at the tips.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hien Duong
  • Patent number: 10669892
    Abstract: An oil filtering system comprises: a first inlet, a first outlet, and a first oil filter; a first bypass conduit interconnecting the first inlet to the first outlet; a first valve in the first bypass conduit, the first inlet fluidly connected to the first outlet at least via the first bypass conduit in an opened configuration of the first valve, and via the first oil filter in a closed configuration; a second inlet, a second outlet, and a second oil filter; a second bypass conduit between the first inlet and the second outlet; a second valve disposed in the second bypass conduit, the second outlet fluidly connected to the first inlet via the second bypass conduit in an open configuration of the second valve, and via the second oil filter in the closed configuration thereof.
    Type: Grant
    Filed: September 22, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Jordan Adique, John Adam Logan
  • Patent number: 10669950
    Abstract: There is described an oil and fuel control system and method for an engine. The system comprises an electric machine having a single rotor coupled to a dual channel stator comprising a first stator and a second stator, for operating as a motor to generate motive power; a dual channel motor drive unit coupled to the electric machine; a dual channel full authority digital engine control (FADEC) coupled to the dual channel motor drive unit; an oil delivery system comprising an oil pump and oil accessories, coupled to the single rotor of the electric machine; and a fuel delivery system comprising a fuel pump and fuel accessories, coupled to the single rotor of the electric machine.
    Type: Grant
    Filed: April 20, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Kevin A. Dooley
  • Patent number: 10670041
    Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
    Type: Grant
    Filed: February 17, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate, Sean Kelly, Peter Townsend, Ronald Dutton, Anthony Brown, Paul Stone, Myron Klein, Milica Kojovic, Robert Venditti
  • Patent number: 10662879
    Abstract: The epicyclic gear stage has a carrier body receiving the planet gears via corresponding planet bearings, a first bearing plane where a first axial end of the planet bearings are received by the carrier body, a second bearing plane where a second axial end of the planet bearings are received by the carrier body, a torque transfer body made integral to the carrier body externally to the sun gear, at a balanced torque transfer plane located between the first bearing plane and the second bearing plane, and extending away therefrom to a shaft coupler, for transferring torque between the carrier body and a shaft, and an oil network extending within the carrier, the oil network having an inlet in the torque transfer body, extending within the torque transfer body and into the carrier body, and extending within the carrier body and into the planet bearings.
    Type: Grant
    Filed: August 8, 2017
    Date of Patent: May 26, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Desjardins, Hervé Turcotte
  • Patent number: 10662815
    Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: May 26, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, Chris Pater
  • Patent number: 10648510
    Abstract: A bearing chamber configuration that favorably directs the flow of oil/air mixture inside the bearing chamber of a gas turbine engine is disclosed. The bearing chamber includes an annular baffle surrounding a rotatable shaft. The baffle comprises an annular groove facing radially inwardly and a first radially-inner annular surface extending axially from a first side of the annular groove. The first radially-inner annular surface of the baffle cooperating with the shaft to define a first space inside the bearing chamber and adjacent the seal. The first space is circumferentially uniform.
    Type: Grant
    Filed: October 17, 2018
    Date of Patent: May 12, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Ivan Sidorovich Paradiso
  • Patent number: 10641325
    Abstract: A damping device for connecting a bearing housing to a bearing outer race is provided. The damping device may permit an allowable range of radial movement of the bearing. The damping device has an elastomeric body connected to one of the bearing outer race and the bearing housing and a cover portion connected to the other one of the bearing outer race and the bearing housing. It also has two or more deformable fluid chambers fluidly connected to one another via at least one orifice and in which fluid is encapsulated. The damping device may dissipate at least partially vibrations travelling between the bearing housing and the bearing outer race by compressing its elastomeric body and by discharging fluid from one fluid chamber to another. There may be a plurality of such damping devices disposed circumferentially about the bearing outer race.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: May 5, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Nathan Tomes
  • Patent number: 10639734
    Abstract: A system and method for machining a workpiece to provide a toothed member having a desired tooth pattern. A cutting tool machines the workpiece to a first depth, thereby forming a semi-finished tooth pattern, the first depth less than a full depth to which the workpiece is to be machined to provide the desired tooth pattern. Dimensions of the semi-finished tooth pattern are acquired and compared to nominal dimensions. If the acquired dimensions are not within a tolerance of the nominal dimensions, the geometry of the cutting tool is modified for correcting deviations of the acquired dimensions from tolerance and the workpiece further machined by the modified cutting tool. Once the dimensions of the semi-finished tooth pattern are within tolerance, the workpiece is machined to the full depth for providing the desired tooth pattern.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: May 5, 2020
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: William Ferry, Mario Blais, Yan Cousineau
  • Patent number: 10634049
    Abstract: A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.
    Type: Grant
    Filed: January 16, 2017
    Date of Patent: April 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andre Julien, Jean Thomassin, Serge Dussault
  • Patent number: 10634169
    Abstract: A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 50% and 90% of the total span length. The natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 4th natural vibration mode.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: April 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Balike
  • Patent number: 10633992
    Abstract: A rim seal located between a stator and a rotor in a gas turbine engine includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: April 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Remy Synnott, John Pietrobon, Franco Di Paola, Lorenzo Sanzari
  • Patent number: 10627376
    Abstract: Methods and systems for failure prediction using analysis of oil or other lubricant. Raw data about feature(s) of each of a plurality of particles filtered from a fluid sample are used to categorize each particle into one of a plurality of categories, each category being defined by one or more of: chemical composition, size and morphology. Particle physical characteristics in each category are quantified to obtain a set of categorized data. The categorized data are compared with historical data. Results of the comparing are evaluated to generate a prediction of any failure or mechanism of failure.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: April 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Maurice Jean, Daniel Meilleur
  • Patent number: 10619596
    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 20, 2017
    Date of Patent: April 14, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Patent number: 10612403
    Abstract: A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct.
    Type: Grant
    Filed: August 7, 2014
    Date of Patent: April 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Robert Sze
  • Patent number: 10611501
    Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.
    Type: Grant
    Filed: June 1, 2017
    Date of Patent: April 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Brian Wirth, Robert Winchcomb, Bruce Calvert, Robert Wigny
  • Patent number: 10605166
    Abstract: A system and method for controlling a variable inlet geometry mechanism of an aircraft engine. At least one first input signal indicative of at least one operating parameter of an aircraft engine is received. At least one second input signal indicative of a level of crosswind experienced by the aircraft and of an airspeed of the aircraft being below a predetermined threshold is received. A schedule is determined for positioning a the variable inlet geometry mechanism based on the at least one first input signal and of the at least one second input signal. The variable inlet geometry mechanism is then positioned in accordance with the schedule.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: March 31, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew Roach, Wai-Lyn Wong, Sebastian Jaehun Kim
  • Patent number: 10604268
    Abstract: The present disclosure provides methods and systems for controlling a propeller-driven aircraft powered by at least one gas turbine engine. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When the thrust change is greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands are output to cause the setting change of the control input(s).
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: March 31, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Carmine Lisio, Kenneth Matheson
  • Patent number: 10605084
    Abstract: A rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by a first eccentricity and the rotor has a peripheral outer surface having a peritrochoid inner envelope configuration defined by a second eccentricity larger than the first eccentricity. Also, a rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by an eccentricity, and a rotor with a peripheral outer surface between adjacent ones of the apex portions being inwardly offset from a peritrochoid inner envelope configuration defined by the eccentricity. The engine may have an expansion ratio with a value of at most 8. The rotary engine may be part of a compound engine system.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: March 31, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean-Gabriel Gauvreau, David Gagnon-Martin, Andre Julien
  • Patent number: 10598018
    Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
    Type: Grant
    Filed: November 2, 2016
    Date of Patent: March 24, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Paul Stone