Search Patents
  • Twisted variable inlet guide vane
    Patent number: 9004850
    Abstract: A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.
    Type: Grant
    Filed: April 27, 2012
    Date of Patent: April 14, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jason Nichols, Hien Duong, Peter Townsend
  • Engine assembly with direct drive of generator
    Patent number: 9994332
    Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, 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 7, 2017
    Date of Patent: June 12, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Ullyott, Anthony Jones, Andre Julien, Jean Thomassin
  • SYSTEM AND METHOD FOR POSITIONING ERROR COMPENSATION DURING MANUFACTURING OF COMPLEX-SHAPED GAS TURBINE ENGINE PARTS
    Publication number: 20140257542
    Abstract: A system and method for error compensation in positioning a complex-shaped gas turbine engine part during manufacturing thereof with a machine. Theoretical measurements for a plurality of control points on the part are first retrieved. Actual measurements for the control points are then acquired in a coordinate system of the machine. If an error between the actual and theoretical measurements is beyond a tolerance, a transformation matrix is computed. The transformation matrix represents a transformation to be applied to the coordinate system to adjust a pose thereof for compensating the error. The transformation matrix may be computed and applied to the coordinate system iteratively until the actual measurements are brought within tolerance. A machining program may then be generated for manufacturing the part accordingly.
    Type: Application
    Filed: March 8, 2013
    Publication date: September 11, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Yuwen LI, Amr ELFIZY
  • Hybrid compressor
    Patent number: 8231341
    Abstract: A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.
    Type: Grant
    Filed: March 16, 2009
    Date of Patent: July 31, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Stephen A. Anderson, Ronald Trumper, Gary Weir
  • Bi-material joint for engine
    Patent number: 11542836
    Abstract: An engine bi-material joint includes a first flange composed of a first material and defining a first coefficient of thermal expansion, and a second flange composed of a second material and defining a second coefficient of thermal expansion. The second flange is different from the first material. An interface flange is engaged with the first flange and with the second flange. The interface flange defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion of the first flange. The third coefficient of thermal expansion is less than the second coefficient of thermal expansion of the second flange. The first coefficient of thermal expansion of the first flange is less than the second coefficient of thermal expansion of the second flange.
    Type: Grant
    Filed: June 3, 2021
    Date of Patent: January 3, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: David Menheere
  • Feedback device with non-axially aligned position markers
    Patent number: 11333020
    Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
    Type: Grant
    Filed: January 9, 2020
    Date of Patent: May 17, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Durand, Richard Kudrna, Ian Farrell
  • Reduction gearbox for a gas turbine engine
    Patent number: 9611789
    Abstract: The described reduction gearbox of a gas turbine engine includes a first gear reduction stage having an input gear adapted to be driven by a turbine output shaft. The input gear transfers power received from the turbine output shaft laterally away from the input gear to an input speed gear. Each input speed gear engages an output speed gear to define a main speed reduction gear set, and the main speed reduction gear sets are laterally spaced apart from one another to define a gap. The gearbox has a second gear reduction stage driven by the output speed gears, the second stage adapted to drive an engine output shaft.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: April 4, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Keith Morgan, Danny Mills
  • Gas turbine engine combustor and method of forming same
    Patent number: 10337736
    Abstract: A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path. The exit duct includes a large exit duct having an annular forged metal section which is butt welded at an upstream end to the outer combustor liner to form a first annular joint. The annular forged metal section is fixed at a downstream end to an annular sheet metal wall to form a second annular joint. Methods of forming and of repairing a gas turbine engine combustor are also disclosed.
    Type: Grant
    Filed: July 24, 2015
    Date of Patent: July 2, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sri Sreekanth, Douglas Maccaul, Eduardo Hawie, Ion Dinu
  • Seal runner and method
    Patent number: 11143046
    Abstract: A seal runner assembly for a gas turbine engine includes a non-rotational annular wear seal, and an annular seal runner having an annular body defining an annular front face contacting the wear seal, the annular body defining an aperture extending axially through the seal runner, the aperture configured for receiving therein a part of a shaft of the gas turbine engine, the seal runner having a plurality of axially-extending slots at locations that are distributed around a wall of the seal runner that extends circumferentially about at least a portion of the annular front face and extends from the front face in a direction away from the wear seal. A method for sealing a gap between a part of a machine and a rotatable shaft of the machine is also provided.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: October 12, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Bruno Martin
  • Turbine section architecture for gas turbine engine
    Patent number: 8734085
    Abstract: A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator. A turbine exhaust case is located downstream of the aftmost rotor and includes an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor. The turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance that is greater than the first axial distance.
    Type: Grant
    Filed: August 17, 2010
    Date of Patent: May 27, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Guy Lefebvre, Eric Durocher
  • CONFIGURABLE AIRCRAFT DATA ACQUISITION AND/OR TRANSMISSION SYSTEM
    Publication number: 20140121861
    Abstract: An aircraft data acquisition and/or transmission system comprises a memory having stored therein a first state machine configuration comprising a first allocation between a plurality of transition criteria objects stored in a first area of the memory and a plurality of state objects stored in a second area of the memory separate from the first area. A processor is coupled to the memory and at least one application executable by the processor causes a first data acquisition and/or transmission behavior in the aircraft by running the first state machine configuration, receives a second state machine configuration comprising a second allocation between the plurality of transition criteria objects and the plurality of state objects, and causes a second data acquisition and/or transmission behavior in the aircraft by running the second state machine configuration.
    Type: Application
    Filed: October 26, 2012
    Publication date: May 1, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: James MOOD, Jeffrey R. VAHUE
  • Recuperator for gas turbine engine
    Patent number: 9388741
    Abstract: A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core. Feeder members extend radially across the outlet opening for passing the pre-combustion stage air through the air channels of the core, and header members extend radially across the inlet opening of the casing for receiving and redirecting air from the air channels in the core towards the combustor section. The feeder and header members each have a tapered configuration from the casing to the axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeders and headers.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: July 12, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, André Julien
  • DOUBLE FRANGIBLE BEARING SUPPORT
    Publication number: 20150176431
    Abstract: A double frangible bearing support structure supports a low pressure rotor of an aircraft engine. The support structure has a first bearing assembly including a first bearing supported by a first bearing support adapted to buckle or frange when subject to a predetermined critical load resulting from an abnormal rotor imbalance. The support structure has a second bearing assembly comprising a second bearing having rolling elements disposed between inner and outer races. The outer race is connected to a second bearing support by means of frangible bolts adapted to fail when subject to a predetermined critical load resulting from radial displacements and loads of the low pressure rotor following decoupling/franging at the first bearing support.
    Type: Application
    Filed: December 23, 2013
    Publication date: June 25, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: LENA RAYKOWSKI, HARVEY SMAILYS, DAVE BEAMISH
  • Method of sizing a cavity in a part
    Patent number: 10822988
    Abstract: A method of sizing a cavity in a part and a part made from such method. The method includes forming the part having the cavity, including forming a plurality of protrusions extending within the cavity from at least one internal surface of the cavity, the protrusions having distal ends bordering an unobstructed portion of the cavity, the unobstructed portion having an initial dimension at least partially defined by a position of the distal ends, pressing a deforming element against the distal ends of the protrusions to plastically deform the protrusions toward the at least one internal surface of the cavity and increase the initial dimension to a final dimension, and disengaging the deforming element from the distal ends.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Lorenzo Campomanes, Orlando Scalzo, Mathieu Fagnan
  • Impeller rear cavity thrust adjustor
    Patent number: 7775758
    Abstract: An apparatus for adjusting a thrust load on a rotor assembly of a gas turbine engine includes an impeller rear cavity defined between a rear face of an impeller of the rotor assembly and a stationary wall spaced axially apart from the rear surface of the impeller. A pressurized air flow with a tangential velocity is introduced into the impeller rear cavity at a tip of the impeller to pressurize the cavity. Means are provided in the cavity for directly interfering with the tangential velocity of the pressurized air flow to affect an average static pressure of the pressurized air flow within the cavity in order to adjust the thrust load on the rotor assembly caused by the average static pressure in the cavity.
    Type: Grant
    Filed: February 14, 2007
    Date of Patent: August 17, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Pierre-Yves Legare
  • COMBUSTOR FOR GAS TURBINE ENGINE
    Publication number: 20150107256
    Abstract: An assembly of a combustor and fuel manifold comprises a fuel manifold having at least an annular portion with a plurality of fuel outlets facing at least partially radially inward. A combustor comprises an annular inner liner and an annular outer liner spaced apart from the inner liner, the inner liner and outer liner concurrently forming an annular combustor chamber therebetween. The inner and outer liners concurrently define an annular receptacle in the annular combustor chamber for receiving the fuel manifold. The inner liner and outer liners are shaped to define an annular gas path in the annular combustor chamber having an upstream portion that is substantially radial and oriented toward a center when the combustor is in a gas turbine engine.
    Type: Application
    Filed: October 17, 2013
    Publication date: April 23, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Darien Sussman, Oleg Morenko
  • Swirl reducing gas turbine engine recuperator
    Patent number: 9766019
    Abstract: A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: September 19, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu, Darius Jehangir Karanjia, Daniel Van Den Ende
  • Shared oil system arrangement for an engine component and a generator
    Patent number: 11225888
    Abstract: A method of distributing oil to a component within a gas turbine engine includes directing a first oil flow from an oil source to an engine component and back to the oil source, directing a second oil flow from the oil source to a generator driven by the engine and back to the oil source, monitoring a parameter of the second oil flow downstream of the generator and upstream of the oil source, detecting a contaminant in the second oil flow based on the parameter, and reducing the second oil flow to the generator when the contaminant is detected without reducing the first oil flow to the engine component. A shared oil system for a component of a gas turbine engine and a generator driven by the gas turbine engine is also discussed.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: January 18, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Waddleton, Daniel Matthew McGuire
  • Diffuser case removal apparatus and method
    Patent number: 8528176
    Abstract: A method and apparatus is provided for removing a centrifugal compressor diffuser case from a turbofan gas turbine engine case which may be used while the engine is installed on an aircraft or when the engine has been removed from the aircraft. The tool includes movable gripping members at least one force member for exerting a pushing action on the engine structure on which the diffuser case is mounted the method includes gripping a peripheral portion of the diffuser case and applying an axial pushing force on the case relative to the engine case to thereby overcome an interference fit between the diffuser case and the engine case.
    Type: Grant
    Filed: October 24, 2008
    Date of Patent: September 10, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Enzo Macchia, Robin Hardstaff, Ian Chandler, Tim Bedard, Geoffrey Henriksen
  • Lubricant drain conduit for gas turbine engine
    Patent number: 11319836
    Abstract: An assembly for a gas turbine engine having: static and rotating components; a seal between the static and rotating components, and between a cavity and an environment outside thereof, the cavity having an inlet fluidly connectable to a source of lubricant and an outlet fluidly connectable to a scavenge pump for drawing lubricant out of the cavity; and a drain conduit having a drain inlet outside the cavity in proximity to the seal for receiving leaked lubricant, and a drain outlet fluidly connected to the outlet of the cavity, the drain outlet located in proximity to a scavenge inlet via which the lubricant exits the cavity to flow toward the scavenge pump such that, in use, a lubricant flow within the drain conduit is entrained by the lubricant exiting the cavity via the scavenge inlet.
    Type: Grant
    Filed: August 14, 2019
    Date of Patent: May 3, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Martin Poulin, Sean Powers
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