Search Patents
  • Turbine blade airfoil profile
    Patent number: 11512595
    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 external 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 defined 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: February 4, 2022
    Date of Patent: November 29, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Fariba Ajalli, Panagiota Tsifourdaris, Michael Paolucci, Othmane Leghzaouni, Stephane Bigras
  • Internal fuel manifold having temperature reduction feature
    Patent number: 7703289
    Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: April 27, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
  • CONNECTOR FOR MULTI-PHASE CONDUCTORS
    Publication number: 20130288498
    Abstract: A connector for multi-phase conductors. The connector includes conductors for conducting multi-phase currents, and at least one conductive plate corresponding to each phase. Each conductive plate defines apertures for the conductors to pass through, there being at least one aperture in each conductive plate for each respective conductor. Each conductive plate includes at least one connecting member for forming an external electrical connection. Each conductor passes through a respective aperture of each conductive plate. Each conductor is selectively coupled to form electrical connection only to a conductive plate corresponding to the respective phase of the conductor.
    Type: Application
    Filed: April 25, 2012
    Publication date: October 31, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Antwan SHENOUDA, Steve STRECKER, Nathan TOMES
  • Process for joining powder injection molded parts
    Patent number: 10226818
    Abstract: A process for joining two or more powder injection molded parts by preparing at least two green parts from a feedstock including a binder and an injection powder. Placing the two or more green part into intimate contact, and maintaining the two green parts in intimate contact at a position with a linkage between the at least two green parts to produce an interconnected green assembly. Placing the assembly under shape retaining conditions, melting the binder of the interconnected green assembly under shape retaining conditions to produce a seamless body.
    Type: Grant
    Filed: March 20, 2009
    Date of Patent: March 12, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Orlando Scalzo, Marc Campomanes, Melissa Despres, Alain Bouthillier, Vincent Savaria
  • Hybrid slinger combustion system
    Patent number: 9874148
    Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: January 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Balancing ring geometry
    Patent number: 11480071
    Abstract: An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.
    Type: Grant
    Filed: June 2, 2020
    Date of Patent: October 25, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hugues Pellerin
  • Positioning assembly and method
    Patent number: 10751808
    Abstract: A method for positioning a rotary part on a machining fixture adapted to hold the rotary part for a machining operation is described. The machining fixture has a center axis and a diaphragm with engaging segments affixed thereto and extending away therefrom. The method includes mounting the rotary part on the machining fixture concentrically about the center axis and adjacent to the engaging segments, and then applying an axial force in a direction substantially parallel to the center axis against the diaphragm. This elastically deforms the diaphragm and radially displaces the contact members of the engaging segments into frictional engagement with a circumferential surface of the rotary part.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: August 25, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yuwen Li, Amr Elfizy
  • Bearing support structure with variable stiffness
    Patent number: 11268405
    Abstract: A method of manufacturing a bearing support structure of a gas turbine engine, includes: obtaining a bearing support and a casing assembly, the casing assembly having first and second casings extending around a central axis and connected together via struts, the bearing support securable to the first casing at attachment points; selecting a distance between the attachment points of the bearing support and the struts as a function of a required stiffness of the bearing support structure; and adjusting a position of the bearing support relative to the casing assembly until the attachment points are distanced from the struts by the selected distance and joining the bearing support to the casing assembly at the attachment points.
    Type: Grant
    Filed: March 4, 2020
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Menheere, Richard Kostka
  • Low profile vane retention
    Patent number: 9506361
    Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: November 29, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruce Fielding, Nathan Tomes, Thomas Veitch
  • Multi-film oil damper with tapered damper rings
    Patent number: 11067121
    Abstract: A multi-film oil damper has a housing defining an annular damper cavity between a radially outward wall and radially extending side walls. The annular damper cavity has an oil inlet configured for connection to a source of pressurized oil. A closure ring defines a radially inward boundary of the annular damper cavity. First and second damper rings are nested together coaxially within the annular damper cavity. At least one of the first damper ring and the second damper ring has an axial end radial thickness less than an intermediate-portion radial thickness.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: July 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, David Beamish
  • Aircraft with engine assembly mounted to wheel well
    Patent number: 10870493
    Abstract: An assembly for an aircraft having a propeller, including a wheel well configured for receiving a retracted landing gear, the wheel well including walls and a closable bottom opening for deploying the landing gear therethrough, an engine assembly having an engine shaft configured for driving engagement with the propeller, and a mount assembly for supporting the engine assembly, the mount assembly connected to at least one of the walls of the wheel well. A method of supporting an engine assembly in an aircraft having a retractable landing gear and a propeller driven by the engine assembly is also discussed.
    Type: Grant
    Filed: February 19, 2018
    Date of Patent: December 22, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Luc Dionne, Bruno Villeneuve, Jean Thomassin
  • System and method for testing engine performance in-flight
    Patent number: 11427353
    Abstract: Systems and Methods are described for testing engine performance in-flight in an aircraft having a first engine and a second engine. The method comprises operating the first engine at a first power level in an output speed governing mode, operating the second engine at a second power level greater than the first power level in a core speed governing mode concurrently with the first engine operating at the first power level in the output speed governing mode, and performing an engine performance test on the second engine while the second engine is at the second power level in the core speed governing mode.
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: August 30, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Martin Drolet, Patrick Manoukian, Zachary Mounir Faty
  • Surface cooler for aero engine
    Patent number: 10125684
    Abstract: A gas turbine engine has a surface cooler having a cooler member defining a fluid passage and at least partially contained in an airfoil shaped flow guide member. The cooler member is disposed within a bypass duct and supported on one of the duct walls. The flow guide member provides a smooth outer surface to guide a main portion of a bypass air stream passing over the surface cooler, and defines an inner air channel between the flow guide member and that supporting one of the duct walls for a secondary portion of the bypass air stream to pass through the inner air channel.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: November 13, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hong Yu
  • Method and system for taxiing an aircraft
    Patent number: 7802757
    Abstract: The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.
    Type: Grant
    Filed: November 9, 2005
    Date of Patent: September 28, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan Dooley, Nashed Youssef
  • 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
  • Propeller balancing using inflight data
    Patent number: 10981675
    Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.
    Type: Grant
    Filed: February 28, 2020
    Date of Patent: April 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Brian Wirth, Robert Winchcomb, Bruce Calvert, Robert Wigny
  • 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
  • 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
  • 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
  • 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
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