Search Patents
  • Patent number: 10717543
    Abstract: Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Richard Ullyott
  • Patent number: 6179555
    Abstract: The invention provides a novel sealing device and plenum assembly particularly adapted for forming a plenum inwardly of a circumferential stator blade array in a gas turbine engine. A Tangential On Board Injection plenum (T.O.B.I.) is defined by assembly of: a forward plate; a rearward plate; and a segmented inner shroud disposed between the forward and rearward plates. Releasable elongate fasteners are disposed in joints between a series of inner shroud segments with sealing sheaths laterally surrounding the fasteners. While clamping the shroud segments between the forward and rearward plates, the fasteners and sheaths simultaneously seal the joints and secure the inner shroud segments with forward and rearward plates in a rigid structural assembly.
    Type: Grant
    Filed: October 6, 1998
    Date of Patent: January 30, 2001
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Eric Tremaine
  • Patent number: 10927944
    Abstract: A planet carrier for an epicyclic gear train of a gas turbine engine gearbox includes a centrally disposed torque transfer coupling, a pair of carrier plates parallel to each to each other and perpendicular to a longitudinal axis, and center arms radially extending radially outward from the torque transfer coupling to the carrier plates. A central bore is concentric with the longitudinal axis and forming a torque transmission point on the planet carrier. The center arms are axially disposed between the axially spaced apart carrier plates and have radially outer ends which terminate at an outer perimeter of the carrier plates. The center arms are thus entirely radially disposed within a radial outer perimeter of the carrier plates.
    Type: Grant
    Filed: January 26, 2018
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Desjardins, Louis Brillon
  • Patent number: 10865657
    Abstract: A sealing assembly for sealing between an oil cavity and an air cavity of a gas turbine is provided. The sealing assembly comprising a seal having a seal element and a circumferential seal housing receiving the seal element. The seal housing has an annulus extending circumferentially around a center axis, radially between an outer periphery and an inner periphery, and axially along the center axis between a first surface and a second surface. The seal housing has a collecting channel defined circumferentially in the inner periphery about the center axis and a draining pocket defined in a portion of the seal housing configured and disposed to in use collect liquid oil during engine operation. The draining pocket extends from the collecting channel to the first surface and configured to communicate collected liquid oil from the collecting channel to the oil cavity.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Maksim Pankratov
  • Publication number: 20140060074
    Abstract: Systems and methods for driving an oil cooling fan (36) of a gas turbine engine (10) during different modes of operation of the gas turbine engine (10) are described. A system may include a coupling device (40) configured to: transmit motive power from a power turbine shaft (22) of the gas turbine engine (10) to the oil cooling fan (36) during a first mode of operation where the power turbine shaft (22) is turning, and to decouple the oil cooling fan (36) from the power turbine shaft (22) during a second mode of operation where the power turbine shaft (22) is prevented from turning. An alternate source (42) of motive power may be configured to drive the oil cooling fan (36) during the second mode of operation.
    Type: Application
    Filed: September 4, 2012
    Publication date: March 6, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Ian A. MACFARLANE
  • Patent number: 11021975
    Abstract: The gas turbine engine can have a first and second rotary components structurally joined to one another via a connector, a first spigot fit between the connector and the first rotary component, the first spigot fit forming an interference fit at a first operating condition and forming a gap at a second operating condition, a second spigot fit between the connector and the first rotary component, the second spigot fit forming an interference fit at the second operating condition and forming a gap at the first operating condition, the gas turbine engine being further configured to form a radial interference fit between the connector and the second rotary component in both the first and second operating conditions.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: June 1, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Yves Roussel, Max Bergeron-Fillion
  • Patent number: 10578012
    Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface bordering the cavity, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the housing and having a tip communicating with the cavity at a location spaced apart from the insert.
    Type: Grant
    Filed: March 1, 2018
    Date of Patent: March 3, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
  • Patent number: 10378554
    Abstract: A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: August 13, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Hong Yu, Peter Townsend
  • Publication number: 20130133332
    Abstract: Systems and methods for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) are described. Such a system may comprise a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).
    Type: Application
    Filed: November 29, 2011
    Publication date: May 30, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Ian A. MACFARLANE
  • Patent number: 10174665
    Abstract: A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: January 8, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, David Meisels, Richard Ullyott
  • Patent number: 10221776
    Abstract: Systems and methods for controlling a gas turbine engine are provided. The system comprises an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command and a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow. The controller comprises a feedforward controller configured for receiving a requested engine speed, obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed, and determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed.
    Type: Grant
    Filed: November 25, 2016
    Date of Patent: March 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Meunier, Reza Pedrami
  • Patent number: 11066944
    Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: July 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Tibor Urac, Barry Barnett
  • Patent number: 10738709
    Abstract: A gas turbine engine has a LP spool including an LP shaft and a HP spool including an HP shaft, an accessory gear box (AGB) drivingly engaged to a plurality of accessories, an engine starter drivingly engaged to the AGB, and a drive shaft drivingly engaged to the AGB. In a first engine mode, the drive shaft is drivingly engaged to the HP shaft and is disengaged from the LP shaft, the engine starter is in driving engagement with the HP shaft via the drive shaft, and the LP shaft is disengaged from the AGB. In a second engine mode, the drive shaft is drivingly engaged to the LP shaft and is disengaged from the HP shaft, the LP shaft is in driving engagement with the AGB via the drive shaft, and the HP shaft is disengaged from the AGB.
    Type: Grant
    Filed: February 9, 2017
    Date of Patent: August 11, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean-Jacques Forest, Martin Poulin
  • Patent number: 11268453
    Abstract: An epicyclic gear train includes a sun gear and planet gears mounted to a carrier and engaged to the sun gear. The planet gears and the carrier are rotatable about a center axis, and the carrier is engaged with a power output at a carrier-output engagement location. Ring gears are in meshed engagement with the planet gears. Planet gear bearings are disposed between one of the planet gears and the carrier. A lubrication interface is defined between each planet gear bearing and one of the planet gears. A bearing lubrication system includes a lubricant supply conduit extending between a conduit inlet at the carrier-output engagement location and conduit outlets at the lubrication interfaces of the planet gear bearings. A lubricant strainer is mounted about the conduit inlet at the carrier-output engagement location.
    Type: Grant
    Filed: March 17, 2021
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Desjardins, Vincent Savaria
  • Patent number: 11118601
    Abstract: A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.
    Type: Grant
    Filed: October 4, 2018
    Date of Patent: September 14, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hong Yu, Peter Townsend
  • Patent number: 10087761
    Abstract: Devices and methods useful for balancing high-pressure spools of gas turbine engines are disclosed. An exemplary device may comprise: an input shaft configured to be coupled to an output of an accessory gear box driven by a high-pressure spool of a gas turbine engine; a first trigger rotatably coupled to the input shaft at a first speed ratio; and a sensor configured to detect the trigger at each revolution of the trigger. The first speed ratio may permit a rotational speed of the first trigger to be substantially the same as a rotational speed of the high-pressure spool. Upon detection of the trigger, the sensor may generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: October 2, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruce Alan Calvert, Richard Brian Wirth, Danny Krause
  • Publication number: 20150246371
    Abstract: A method of cold spray coating a target surface of a component, the coating provided using selected solid powders, the method comprising: placing a mask onto the component to cover an area of the component adjacent the target surface which is not to be coated, the mask having a masking top surface provided of a material selected to be non-adhesive with the selected solid powders when cold-sprayed onto the masking top surface, the mask having a melting point above a temperature at which cold spray is performed; cold spraying the target surface with the selected solid powders, including at least some overspraying onto the mask; removing the overspray from the mask; and removing the mask from the component. A mask for a cold sprayed component of a gas turbine engine is also presented.
    Type: Application
    Filed: February 28, 2014
    Publication date: September 3, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Pierre VERRIER
  • Patent number: 9618927
    Abstract: A method of determining a radius of a cutting end of a tool for a turning machine using a touch probe is provided. One of the cutting end and the touch probe is movable relative to a reference frame having a first axis and a second axis and having a reference point trackable in the reference frame. The method comprises establishing a first contact point and recording a first coordinate of the reference point on the first axis; establishing a second contact point and recording a second coordinate of the reference point on the second axis; establishing a third contact point and recording a third coordinate of the reference point on the first axis and a fourth coordinate of the reference point on the second axis upon contact; and determining a radius of the cutting end based on the first, second, third and fourth coordinates.
    Type: Grant
    Filed: April 15, 2014
    Date of Patent: April 11, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lafleche Gagnon, Rachid Guiassa, Philippe St-Jacques
  • Patent number: 9046041
    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: Grant
    Filed: September 25, 2012
    Date of Patent: June 2, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Marcin Rejman, Louis Brillon, David Gagnon-Martin
  • Patent number: 9239005
    Abstract: The combined cooling system uses a single heat exchanger to cool both engine air for use in an engine system and aircraft air for use in an aircraft system. More particularly, a bleed air path leads from the compressor stage to the heat exchanger where it is placed in thermal exchange contact with a flow of cooling air coming from a cooling path. From an outlet end of the heat exchanger, the bleed air splits into two paths: an aircraft air path leading to at least one aircraft system such as an Environmental control system (ECS), a wind de-icing system or the like, and an engine air path leading to at least one engine system such as a buffer air system for pressurizing the bearing cavities.
    Type: Grant
    Filed: November 25, 2011
    Date of Patent: January 19, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Steven Strecker, Xiaoliu Liu, Adam Logan
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