Search Patents
  • Oil purge system for a mid turbine frame
    Patent number: 8944749
    Abstract: An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Zenon Szlanta, Roger Huppe
  • Engine architecture using electric machine
    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
  • Hybrid gas turbine engine and torque transfer assembly therefore
    Patent number: 11530649
    Abstract: The torque transfer assembly can include a sleeve having an elongated internal opening, a shaft having an elongated body extending in the internal opening of the sleeve, a first coupler at a first end of the elongated body coupled to a gas turbine engine rotor, and a second coupler at a second end of the elongated body coupled to a generator, the second coupler opposite the first coupler relative to a length of the elongated body, the shaft being made of a metal, and a bushing extending around the elongated body of the shaft, trapped between the shaft and the sleeve, the bushing made of plastic, the bushing having a coefficient of thermal expansion greater than a coefficient of thermal expansion of the sleeve.
    Type: Grant
    Filed: March 30, 2021
    Date of Patent: December 20, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Alecu, David Menheere
  • Turbine shroud segment sealing
    Patent number: 9850775
    Abstract: An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: December 26, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: John Pietrobon, Remy Synnott
  • Method of manufacturing a rotary engine casing
    Patent number: 10473026
    Abstract: A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: November 12, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Villeneuve, Jean-Gabriel Gauvreau
  • Circulating coolant fluid in hybrid electrical propulsion systems
    Patent number: 11453508
    Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. A first lubrication/coolant system is connected for circulating a first lubricant/coolant fluid through the heat engine. A second lubricant/coolant system in fluid isolation from the first lubrication/coolant system is connected for circulating a second lubricant/coolant fluid through the electric motor.
    Type: Grant
    Filed: December 20, 2021
    Date of Patent: September 27, 2022
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Dubreuil, Eric LaTulipe
  • Portable test stand and method for testing aircraft engines
    Patent number: 11874196
    Abstract: A portable attitude test stand (PATS) for an aircraft engine, has: a support frame mountable on a trailer of a road vehicle; a test cell supported by the support frame and sized to receive the aircraft engine, the test cell operable to rotate the aircraft engine about a pitch axis and a roll axis of the aircraft engine; and an actuator operatively connected to the test cell and to the support frame, the actuator operable to lower and raise the test cell relative to the support frame between a transport configuration in which the test cell has a transport height and a test configuration in which the test cell has a test height, the test height being greater than the transport height.
    Type: Grant
    Filed: August 25, 2022
    Date of Patent: January 16, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Douglas Monahan, Gabor Kafka
  • Unison member for variable guide vane
    Patent number: 11767768
    Abstract: A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.
    Type: Grant
    Filed: February 12, 2021
    Date of Patent: September 26, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Daniel Poick
  • Integrated strut-vane
    Patent number: 11193380
    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: January 21, 2019
    Date of Patent: December 7, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, Edward Vlasic, Panagiota Tsifourdaris
  • Bypass duct louver for noise mitigation
    Patent number: 10823055
    Abstract: A bleed air system is disclosed for a turbofan engine having a bypass duct. The bleed air system includes a bleed air conduit having an inlet end connected to the bypass duct and a bleed air flow control valve disposed downstream of the inlet end, and a louver assembly disposed within the opening at inlet end of the bleed air conduit. The louver assembly includes an airfoil-shaped louver blade which extends across the opening in a direction transverse to the flow direction within the bypass duct. A reinforcing rib is attached to the louver blade and extends across the louver assembly in a direction generally parallel to the flow direction.
    Type: Grant
    Filed: September 26, 2016
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui
  • Method of balancing a spool of a gas turbine engine
    Patent number: 9932832
    Abstract: A method of balancing a spool of a gas turbine engine, the spool including a forward rotor assembly and an aft rotor assembly separated by a spacer, the method comprising: balancing the forward rotor assembly and the aft rotor assembly independently from one another using conventional balancing techniques; and mathematically modeling the spool; applying a modeled axial load to the modeled spool to determine a trim weight which would balance the spool when subjected to the modeled axial load; and physically placing the trim weight to one of the forward rotor assembly and the aft rotor assembly.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: April 3, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jiemin Wang, Cameron Walters, Ron Robinson, Jeffrey Bernard Heyerman, David Beamish
  • Laser drilling methods of shallow-angled holes
    Patent number: 8631557
    Abstract: A method for providing a shallow-angled hole through a thermal barrier coated component in accordance with one aspect thereof, includes a step of applying a pulse laser beam to pre-drill the hole through a base metal of the component. A thermal barrier coating is then applied to the base metal, covering the pre-drilled hole in the base metal. A further step is conducted to apply the pulse laser beam through the thermal barrier coating a location to coincide with pre-drilled hole in the base metal in order to complete the formation of the hole extending through the component.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Amr Elfizy, Ghislain Hardy, Sylvain Cournoyer
  • Inertial separator
    Patent number: 4592765
    Abstract: A particle separator for a gas turbine engine is described having an inlet passage to the compressor of the gas turbine engine, with the inlet passageway being defined by an inner wall and an outer wall. The inner wall diverges outwardly to form a throat with a diverging outer wall and converges inwardly downstream thereof. A first bypass opening is provided immediately upstream of the diverging inner wall, whereby solid and liquid particles can be diverted and passed overboard. A splitter ring is provided in the inlet passageway downstream of the converging inner wall, such that the finer particles escaping from the first bypass openings would be separated by the splitter ring.
    Type: Grant
    Filed: January 15, 1985
    Date of Patent: June 3, 1986
    Assignee: Pratt & Whitney Canada Inc.
    Inventors: Daniel S. Breitman, Ernest G. Dueck
  • 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 ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE
    Publication number: 20140012481
    Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.
    Type: Application
    Filed: September 13, 2013
    Publication date: January 9, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
  • Methods for measuring part size and runout
    Patent number: 11230393
    Abstract: A part measuring kit for a rotary table on a machine bed includes a part fixture mountable on the rotary table for retaining a part to be measured and/or an object having known dimensions. The kit further includes a measuring device mountable on the machine bed and movable relative to the rotary table for taking measurements of the part to be measured and/or the object having known dimensions, wherein the rotary table is rotatable between each taken measurement. The kit further includes a calibration offset calculator for calculating a calibration offset for the measuring device by comparing taken measurements of the object having known dimensions with the known dimensions, and correcting taken measurements of the part to be measured via the calculated calibration offset.
    Type: Grant
    Filed: July 23, 2020
    Date of Patent: January 25, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Rachid Guiassa, Lafleche Gagnon
  • Aircraft propulsion system with intermittent combustion engine(s)
    Patent number: 11719166
    Abstract: An aircraft system is provided that includes a first propulsor rotor, a second propulsor rotor, a drivetrain and an intermittent combustion engine. The first propulsor rotor is rotatable about a first propulsor axis. The second propulsor rotor is rotatable about a second propulsor axis. The drivetrain includes a drive structure and a transmission. The drive structure is rotatable about a drive axis that is angularly offset from the first propulsor axis and the second propulsor axis. An output of the transmission is coupled to the first propulsor rotor and the second propulsor rotor through the drive structure. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the drivetrain.
    Type: Grant
    Filed: July 15, 2022
    Date of Patent: August 8, 2023
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Richard Freer
  • Internal manifold with fuel inlet
    Patent number: 10294865
    Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 21, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • LUBRICANT PUMP SYSTEM AND METHOD FOR AIRCRAFT ENGINE
    Publication number: 20230417153
    Abstract: Lubricant pump systems and associated methods for aircraft engines are provided. The method includes receiving an input torque, dividing the input torque between a first load path receiving a first portion of the input torque, and a second load path receiving a second portion of the input torque. A first lubricant pump of the aircraft engine is driven via the first load path using the first portion of the input torque. A second lubricant pump of the aircraft engine is driven via the second load path using the second portion of the input torque. When a malfunction of the second lubricant pump occurs, the method includes ceasing to drive the first lubricant pump and the second lubricant pump using the input torque.
    Type: Application
    Filed: September 12, 2023
    Publication date: December 28, 2023
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Hervé TURCOTTE
  • Airfoil for gas turbine engine
    Patent number: 10718216
    Abstract: An airfoil for a gas turbine engine including a tip extension disposed at the tip of the airfoil body. The tip extension extends from the suction side surface and/or the pressure side surface and defines a tip thickness that is larger than a true thickness of the airfoil body. The true thickness is defined within a plane perpendicular to a root axis and extending transversely to the airfoil chord around a midpoint thereof. The tip extension includes a side transitional surface forming a curve extending tangentially from the side surface and/or the pressure side surface. The tip thickness increases over a radial dimension in the plane that is at least 2 times the true thickness.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Rockarts, Peter Townsend
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