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  • Reverse flow multi-spool gas turbine engine with aft-end accessory gearbox drivingly connected to both high pressure spool and low pressure spool
    Patent number: 10465611
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: November 5, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Keith Morgan, Lazar Mitrovic, Jean Dubreuil, Martin Poulin
  • Tangential on-board injector
    Patent number: 11598265
    Abstract: The gas turbine engine includes a casing assembly located proximate a turbine section of the gas turbine engine, and a tangential on-board injector (TOBI) having a body defining a plurality of air passages extending in a radial direction, the plurality of air passages circumferentially distributed and directing cooling air toward a turbine rotor of the turbine section of the gas turbine engine. An interference fit is provided between a face of the body and a face of a member of the casing assembly, the interference fit defining a fastener-free engagement between the bearing housing and the TOBI to prevent relative movement between the member of the casing and the TOBI.
    Type: Grant
    Filed: February 3, 2021
    Date of Patent: March 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Christophe Tremblay, Franco Di Paola, Olivier Nadeau
  • Actively controlled bleed valve
    Patent number: 11674408
    Abstract: A bleed valve has a valve body enclosing a valve chamber defining a passageway between an inlet port and an outlet port. A panel is mounted into the valve body. The panel is deflectable under fluid pressure between a sealing position blocking the passageway when the bleed valve is in a close state, and a bleeding position allowing fluid flow communication between the inlet port and the outlet port when the bleed valve is an open state. A pressure control device is provided to vary a fluid pressure differential between opposite sides of the panel within the valve chamber and selectively open or close the bleed valve.
    Type: Grant
    Filed: April 14, 2022
    Date of Patent: June 13, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: David Menheere
  • Aircraft power plant cooling system
    Patent number: 11352885
    Abstract: A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.
    Type: Grant
    Filed: April 8, 2020
    Date of Patent: June 7, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Luc Dionne
  • Fan hub design
    Patent number: 9169730
    Abstract: A fan rotor has a fan web and a plurality of circumferentially spaced-apart fan blades extending radially outwardly from an outer rim of the fan web. The outer rim is integrally connected to an inner rim through an axially facing web section. The web section has an inward concavature and extends aft of the center of gravity of the fan blades to shift the center of gravity of the hub rearwards while maintaining airfoil stress below critical levels. The rim section may have an inwardly projecting annular channel formed in a leading edge thereof and tuned to the 2M3ND mode of the fan hub.
    Type: Grant
    Filed: November 16, 2011
    Date of Patent: October 27, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Barry Barnett
  • Compressor wash nozzle integrated in an inlet case strut
    Patent number: 8245952
    Abstract: A compressor wash nozzle integrated in an inlet case strut of a turbine engine is described. A fluid passage and a nozzle are defined in the inlet case strut for delivering a wash/rinse fluid into the inlet gas path of the engine. A fluid connector communicates with the fluid passage and is positioned exteriorly of the inlet gas strut and adapted for receiving pressurized wash/rinse fluid for injection through the nozzle into gases flowing in the inlet gas path and in the direction of the compressor for washing and/or rinsing the blades of the compressor.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: August 21, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Julien de la Bruère-Terreault, Andrew Robert Marshall
  • Anti-icing apparatus and method for aero-engine nose cone
    Patent number: 8015789
    Abstract: An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: September 13, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Joseph Horace Brand, Michael John Dowhan
  • Variable geometries transient control logic
    Patent number: 10822104
    Abstract: Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A power level difference between a requested engine power level and a current engine power level is determined at a computing device. The power level difference is compared to a predetermined power threshold at the computing device. When the power level difference exceeds the predetermined power threshold, a position control signal for changing a position of the variable geometry mechanism is generated and output at the computing device, the position control signal generated based on a requisite bias level, the requisite bias level being based on the power level difference.
    Type: Grant
    Filed: August 23, 2018
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Philippe Beauchesne-Martel
  • Method and system for adjusting a variable geometry mechanism
    Patent number: 11486316
    Abstract: Systems and methods for adjusting a variable geometry mechanism of an engine are described herein. An engine control request indicative of a desired output power for the engine is monitored. A rate of change of the engine control request is determined. The rate of change is compared to a threshold. Responsive to determining that the rate of change is beyond the threshold, a transient bias map is applied to a steady-state schedule to generate a variable geometry mechanism request indicative of a target position for the variable geometry mechanism. The variable geometry mechanism is adjusted toward the target position according to the variable geometry mechanism request.
    Type: Grant
    Filed: March 8, 2019
    Date of Patent: November 1, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Poi Loon Tang, Kirsten Joan Evetts, Philippe Beauchesne-Martel
  • Method and apparatus for pilot training
    Patent number: 4831567
    Abstract: A method and system for providing training mode operation of a multiple engine aircraft simulates the failure of one engine and the simultaneous operation of at least one other engine in an elevated, emergency power condition. The engines (20, 22) are mechanically linked (24) and provide a single power output (26). A training power schedule (56a, 56b) is selected (60, 62) to limit the combined engine power output to a level equivalent to the combined output with one engine inoperative and another in an elevated, emergency power operating condition.
    Type: Grant
    Filed: April 4, 1988
    Date of Patent: May 16, 1989
    Assignee: Pratt & Whitney Canada Inc.
    Inventor: Alan J. Lea
  • System and method for exiting an asymmetric engine operating regime
    Patent number: 11725597
    Abstract: Methods and systems for operating an aircraft having two or more engines are described. The method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft, receiving a request to exit the asymmetric operating regime, the request having at least one parameter associated therewith, selecting one of a plurality of available exit protocols as a function of the at least one parameter, and applying the exit protocol by commanding the engines accordingly.
    Type: Grant
    Filed: October 18, 2019
    Date of Patent: August 15, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Patrick Manoukian
  • Method and system for configuring operation of an engine
    Patent number: 11686257
    Abstract: Systems and methods for configuring operation of an engine are described herein. A computer-readable label associate with the engine is read by a mobile device to obtain label information having at least one trim value for the engine encoded therein. The at least one trim value is extracted from the label information on the mobile device. The at least one trim value is wirelessly transmitted from the mobile device to a data transmission unit of the engine. The data transmission unit is configured for instructing an electronic engine controller to trim the engine with the at least one trim value during operation of the engine.
    Type: Grant
    Filed: October 2, 2019
    Date of Patent: June 27, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bjorn Stickling, Jonathan Miller, James Jarvo
  • Multi-spool gas turbine engine architecture
    Patent number: 10767567
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool and the HP spool are independently rotatable about an axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is axially mounted at one end of the engine. The LP compressor is axially positioned between the HP compressor and the AGB. The AGB is drivingly connected to the HP spool through the center of the LP compressor.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: September 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Guy Lefebvre
  • Fan blade platform feature for improved blade-off performance
    Patent number: 6991428
    Abstract: A fan blade for a gas turbine engine having an airfoil with a leading edge; a trailing edge; a concave side; and a convex side. The blade has an integral platform with: a convex fillet merging with the airfoil; a forward edge; an aft edge; and a thickness defined between a top surface and an underside surface. The platform includes a stiffener on the underside surface adjacent the convex side of the blade, such that the stiffener defines a blade-off event platform fracture path on a second side of the platform adjacent the following blade and adjacent the convex side of the airfoil.
    Type: Grant
    Filed: June 12, 2003
    Date of Patent: January 31, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Nathan Brad Crane
  • Inclement weather detection in aircraft
    Patent number: 10829236
    Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: November 10, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Yen-Wen Wang, Tony Yee
  • Blade angle position feedback system with extended markers
    Patent number: 10829201
    Abstract: A blade angle feedback assembly for an aircraft-bladed rotor and an aircraft-bladed rotor system are provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor, the feedback device having a root surface having an edge. At least one position marker extends from the root surface and extends laterally beyond the edge. At least one sensor is mounted adjacent the feedback device and configured to detect a passage of the at least one position marker as the feedback device rotates about the longitudinal axis.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: November 10, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dana Tomescu
  • Turbine blade airfoil profile
    Patent number: 11578600
    Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
    Type: Grant
    Filed: October 15, 2021
    Date of Patent: February 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Tardif, Francois Roy, Jonathan Dorai, Mohammed Ennacer, Benjamin Luymes
  • Air inlet for a gas turbine engine
    Patent number: 10385785
    Abstract: A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: August 20, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ian MacFarlane, Lazar Mitrovic
  • Engine assembly for an auxiliary power unit
    Patent number: 10501200
    Abstract: An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.
    Type: Grant
    Filed: June 11, 2018
    Date of Patent: December 10, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Ullyott, Anthony Jones, Andre Julien, Jean Thomassin
  • Active turbine or compressor tip clearance control
    Patent number: 9598974
    Abstract: A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: March 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Terrence Lucas, Thomas Francis Haslam-Jones, Danny Mills, Guy Bouchard
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