Search Patents
  • GEARBOX POSITIONING DEVICE
    Publication number: 20140084130
    Abstract: A gearbox positioning device to position a gearbox relative to an engine case of a gas turbine engine. The positioning device has a first and second part, with the first part having a connecting cavity of predetermined shape and being secured to the engine case. The second part has a coupling post received in the connecting cavity and constraining displacement of the gearbox in a laterally transverse direction with respect to the central longitudinal axis of the engine. The device permits movement of the gearbox in the axial direction of the engine as well as angular movement to prevent stressing the engine case during thermal growth of the engine case or support linkage imbalance. A gearbox positioning system incorporating the positioning device and the method of attaching same to the engine casing is also included.
    Type: Application
    Filed: September 25, 2012
    Publication date: March 27, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Marcin REJMAN, Louis BRILLON, David GAGNON-MARTIN
  • Combustor heat shield cooling hole arrangement
    Patent number: 10753283
    Abstract: A combustor heat shield has a heat shield body having a first surface configured to face a combustor shell and an opposed second surface configured to face towards the combustion gases in the combustion chamber. A dilution or igniter hole is defined in the heat shield body. An array of circumferentially spaced-apart cooling holes is provided around the at least one dilution or igniter hole. The cooling holes are oriented to locally deliver a swirl of cooling air around an axis of the dilution or igniter hole. The cooling holes are angled relative to the heat shield body and extend from an inlet on the first surface to an outlet on the second surface. The outlet is positioned closer to a perimeter of the dilution or igniter hole than the inlet.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: August 25, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Si-Man Amy Lao
  • Side plate for rotary engine
    Patent number: 11761376
    Abstract: A side housing for a rotary internal combustion engine, has: a side wall; a side plate having a rotor-engaging side facing away from the side wall and a back side opposite the rotor-engaging side and facing the side wall, the side plate defining first threads located on the back side, the first threads extending circumferentially around a central axis of the side plate; and a nut rotatable relative to the side wall about the central axis of the side plate and axially locked to the side wall relative to the central axis, the side plate secured to the side wall via a threaded engagement between the first threads of the side plate and second threads defined by the nut.
    Type: Grant
    Filed: November 11, 2022
    Date of Patent: September 19, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Johnny Vinski, Vincent Savaria, David Gagnon-Martin
  • Partition arrangement for gas turbine engine and method
    Patent number: 11428104
    Abstract: The turbine rotor assembly can include a turbine rotor disc drivingly mounted to a shaft for rotation about a rotation axis and having a central aperture extending coaxially with the shaft through the turbine rotor disc and being defined by a radially inner surface of the turbine rotor disc, a cavity downstream of and housing at least a part of the turbine rotor disc, a nut secured to the shaft and extending across the central aperture, a first air passage defined between an outer surface of the nut and the radially inner surface of the turbine rotor disc and fluidly connected to the cavity, a second air passage defined radially inward of the first air passage by an inner surface of the shaft and an inner surface of the nut.
    Type: Grant
    Filed: July 29, 2019
    Date of Patent: August 30, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Vincent Paradis
  • Engine assembly with a dedicated voltage bus
    Patent number: 11124311
    Abstract: There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, Eric Taillon
  • Bearing housing
    Patent number: 11891906
    Abstract: A bearing housing for a bearing having an outer race, the bearing housing comprising: an annular wall extending about an axis and axially between a first end and a second end, the annular wall including: a plurality of holes spaced circumferentially from one another and spaced axially from the first end, the plurality of holes extending through the annular wall toward the axis; and an interior housing surface extending about the axis and defining interior openings of the plurality of holes, the interior housing surface having a cylindrical portion defining a seat for radial engagement with the outer race, the cylindrical portion extending axially from a first location proximate to the first end to at least a second location between the first location and the interior openings.
    Type: Grant
    Filed: February 22, 2022
    Date of Patent: February 6, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Maciej Piotrowski, Lukasz Pokrzywa
  • System and method for monitoring a bleed valve of a gas turbine engine
    Patent number: 11454176
    Abstract: There are described methods, systems, and assemblies for monitoring a bleed valve of a gas turbine engine. The method comprises determining a rate of change of a gas generator speed of the gas turbine engine; determining a rate of change of a parameter indicative of engine power of the gas turbine engine; comparing at least one ratio based on the rate of change of the gas generator speed and the rate of change of the parameter indicative of engine power to at least one range of values; detecting a modulation delay of the bleed valve when the at least one ratio is within the at least one range of values; and transmitting a signal indicative of the bleed valve malfunction in response to detecting the modulation delay.
    Type: Grant
    Filed: January 31, 2020
    Date of Patent: September 27, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Louis Duranleau-Hendrickx
  • Air-cooled oil cooler for turbofan engine
    Patent number: 9200570
    Abstract: A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air channel is in the nacelle cowl, an inlet and an outlet of the air channel being in an outer surface of the nacelle cowl. An oil cooler has at least one oil passage for oil circulation, the air cooler having a first heat exchange surface in the air channel exposed to air circulating in the air channel, the air channel having a second heat exchange surface in the bypass duct exposed to air circulating in the bypass duct. A method for cooling oil in a turbofan gas turbine engine is also provided.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: December 1, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Daniel T. Alecu
  • SYSTEM AND METHOD FOR ENGINE TRANSIENT POWER RESPONSE
    Publication number: 20140278014
    Abstract: There is provided a system and method for controlling an engine. A request signal indicative of a demand for the engine to output a required power level is first receive. A position control signal is then generated in response to the request signal. The position request signal is indicative of a first request for adjusting a present position of a variable geometry mechanism of the engine towards a commanded position to achieve the required power level. An acceleration rate control signal is further generated on the basis of the position control signal. The acceleration rate control signal is indicative of a second request for adjusting an acceleration rate of the engine in accordance with the commanded position of the variable geometry mechanism. The position control signal and the acceleration rate control signal are then output to the engine.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: François BELLEVILLE, Philippe BEAUCHESNE-MARTEL, Keith MORGAN
  • Method and system for controlling a pneumatic valve
    Patent number: 10767666
    Abstract: Methods and systems for controlling a pneumatic starter air valve of a gas turbine engine are described herein. The starter air valve is controlled in a first mode of operation by actuating a first solenoid of the starter air valve with a steady-state input signal. Passage of the steady-state input signal to a second solenoid of the starter air valve is allowed, to actuate the second solenoid and enable pressure regulation of the starter air valve. The starter air valve is controlled in a second mode of operation by actuating the first solenoid with a pulse-width modulation input signal. Passage of the pulse-width modulation input signal to the second solenoid is prevented, to disable the pressure regulation in the second mode of operation.
    Type: Grant
    Filed: March 27, 2019
    Date of Patent: September 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew Walz, Mehmet Tanju
  • Electric probe assembly, gas turbine engine having same and method of cooling same
    Patent number: 9551281
    Abstract: A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body. In operation, the conduit carries a fluid flowing at a temperature lower than the local ambient temperature. The at least portion of the probe body is embedded in the fluid inside the conduit. The fluid thermally insulates the probe body from the local ambient temperature of the immediate environment around the at least one electric probe assembly.
    Type: Grant
    Filed: January 15, 2014
    Date of Patent: January 24, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, John Pietrobon
  • Vane array structure for a hot section of a gas turbine engine
    Patent number: 11814989
    Abstract: An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a first platform, a second platform, a plurality of vanes and a plurality of beams. The first platform extends axially along and circumferentially about an axis. The second platform extends axially along and circumferentially about the axis. The vanes are arranged circumferentially about the axis. Each of the vanes extends radially across a gas path between the first platform and the second platform. The vanes include a first vane movably connected to the first platform. The beams are arranged circumferentially about the axis. The beams are fixedly connected to the first platform and the second platform. The beams include a first beam extending radially through the first vane.
    Type: Grant
    Filed: October 29, 2021
    Date of Patent: November 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Eric Durocher
  • Compound cycle engine
    Patent number: 9194232
    Abstract: A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a velocity turbine, and a turbocharger is discussed. The velocity turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the velocity turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the pressure turbine of the turbocharger is in fluid communication with the flowpath of the velocity turbine downstream of its rotor. A method of compounding at least two rotary engines is also discussed.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: November 24, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sébastien Bolduc, Mike Fontaine, Luc Landry, Jean Thomassin
  • Mechanical disconnects for parallel power lanes in hybrid electric propulsion systems
    Patent number: 11732639
    Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured 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. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.
    Type: Grant
    Filed: December 9, 2019
    Date of Patent: August 22, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric LaTulipe, Jean Thomassin, Todd A. Spierling, Robert A. Bayles
  • Systems and methods for engine calibration
    Patent number: 11591974
    Abstract: Methods and systems for calibrating an engine having a rotating shaft are provided. Readings from a plurality of speed sensors provided in one of a plurality of configurations about the shaft are obtained over a plurality of rotations of the shaft, the readings indicative of the passage of position markers and associated with a first precision level. A parameter indicative of relative spacing between the plurality of speed sensors is determined by applying a statistical algorithm to the readings, the parameter being associated with a second precision level higher than the first precision level. The parameter is compared to reference parameters associated with the plurality of configurations to identify an actual speed sensor configuration from amongst the plurality of configurations. The engine is calibrated based on the actual speed sensor configuration.
    Type: Grant
    Filed: April 2, 2020
    Date of Patent: February 28, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Jason Tremblay
  • Gas turbine engine comprising liquid hydrogen evaporators and heaters
    Patent number: 11761381
    Abstract: In accordance with at least on aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine and a fuel feed conduit. The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank fluidly connected to a combustor of the gas turbine engine, a liquid hydrogen pump to drive fuel to the combustor of the gas turbine engine, an evaporator, and an electric heat source in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.
    Type: Grant
    Filed: August 14, 2021
    Date of Patent: September 19, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Scott Smith
  • CUTTING TOOL AND CORRESPONDING ASSEMBLY
    Publication number: 20150209054
    Abstract: A one-piece cutting tool has a shank portion with a mounting end and a cutting end. The cutting end has a body portion and a substantially hemispherical portion. The cutting end further comprises a plurality of flutes, each flute helically extending adjacent to one another about the cutting end along a length from the body portion to the hemispherical portion. Each flute has a cutting edge divided into a first cutting edge section and a second cutting edge section, the first cutting edge section extending along the body portion and being substantially straight-edged or serrated, and the second cutting edge section extending along the hemispherical portion and being serrated along at least a part of the hemispherical portion. A cutting tool assembly is also provided.
    Type: Application
    Filed: January 29, 2014
    Publication date: July 30, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Fuat ATABEY
  • Buffer fluid delivery system and method for a shaft seal of a gas turbine engine
    Patent number: 11572837
    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: Grant
    Filed: January 22, 2021
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Alecu, David Menheere
  • Lubricant pump system and method for aircraft engine
    Patent number: 11788427
    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: Grant
    Filed: June 10, 2021
    Date of Patent: October 17, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hervé Turcotte
  • Engine monitoring display for maintenance management
    Patent number: 6408258
    Abstract: The present invention is directed to a system and method for aircraft engine monitoring to permit management of individual aircraft in a fleet of aircraft. A processing system collects data on engine operational parameters and then uses this data to perform calculations to accurately determine time remaining until service and relative wear of specific engines in the fleet of aircraft. The time remaining until service and relative wear is displayed on a display screen which is configured to display this data for each engine separately. The displayed results can be used by an aircraft maintenance manager to accurately determine if the aircraft engines are being operated according to a maintenance plan, or to rotate the service of the aircraft to balance the wear on the aircraft engines in the fleet.
    Type: Grant
    Filed: December 20, 1999
    Date of Patent: June 18, 2002
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Serge Richer
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