Search Patents
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • Load distribution system for gas turbine engine
    Patent number: 8182201
    Abstract: There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line is adapted to sense static pressure in the high-pressure compressor gas path. The line has an outlet end producing the static pressure. An air-tight pressure actuator is operatively connected to the outlet end and to one of the axial bearings to exert a force on the axial bearing proportionally to a pressure of the outlet end.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: May 22, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Daniel T. Alecu, John Watson
  • 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
  • Oil scavenge system having churning damper for gas turbine engines
    Patent number: 8499893
    Abstract: An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation.
    Type: Grant
    Filed: March 29, 2012
    Date of Patent: August 6, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Daniel T. Alecu, Kenneth Parkman
  • Mid turbine frame system for gas turbine engine
    Patent number: 8245518
    Abstract: A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design.
    Type: Grant
    Filed: November 28, 2008
    Date of Patent: August 21, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Lam Nguyen
  • System and method for synthesizing engine output power
    Patent number: 11739696
    Abstract: A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.
    Type: Grant
    Filed: December 13, 2021
    Date of Patent: August 29, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labrecque, Kevin Nguyen, Ninad Joshi
  • Turbine rim seal with lip
    Patent number: 11668203
    Abstract: A turbine section has: a rotor rotatable about a central axis, the rotor having blades each protruding radially outwardly from a platform relative to the central axis; a stator having vanes each protruding radially outwardly from a shroud; a rim seal between the platform and the shroud, the rim seal having: an axial overlap between the platform and the shroud, and a lip protruding in a direction having a radial component relative to the central axis from one of the platform and the shroud toward the other of the platform and the shroud, the lip axially overlapping the other of the platform and the shroud, the lip having a radial height such that a radial gap remains between the lip and the other of the platform and the shroud when the turbine section is in operation.
    Type: Grant
    Filed: July 8, 2021
    Date of Patent: June 6, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Francis Gemme
  • Method of balancing a gas turbine engine rotor
    Patent number: 10570741
    Abstract: A gas turbine engine rotor including a disc adapted to be mounted for rotation about an axis, the disc including an annular balancing flange integrally connected thereto, the balancing flange having a first radial dimension around a first arc angle and a second radial dimension greater than the first radial dimension around a second arc angle, the second arc angle corresponding to 360 minus the first arc angle, the second arc angle being less than 180 degrees, the balancing flange around the second arc angle defining a protuberance, the protuberance being defined through machining of the balancing flange, the protuberance compensating for an unbalance of the rotor.
    Type: Grant
    Filed: April 11, 2017
    Date of Patent: February 25, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Paul Stone, Richard Ivakitch
  • Voltage discharge channelling assembly for a gas turbine engine
    Patent number: 9784132
    Abstract: A gas turbine engine including a composite case having a conductive path therein, and a conductive case connected to the composite case. The conductive case is made of a conductive material. A fastener connects the composite case to the conductive case. The fastener is conductively connected to the conductive material of the conductive case and not directly conductively connected to the conductive path. At least one voltage discharge channeling assembly is connected to the fastener and to the conductive case. The at least one voltage discharge channeling assembly has a portion conductively connected to the conductive path. The at least one voltage discharge channeling assembly is conductively connected to the fastener. A method of assembling an engine casing in a gas turbine engine is also provided.
    Type: Grant
    Filed: April 20, 2015
    Date of Patent: October 10, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bryan William Olver, Suresh Sivavarman, Brant Duke
  • Combustor with fuel plenum with mixing passages having baffles
    Patent number: 11867400
    Abstract: A combustor for a gas turbine engine includes a liner surrounding a fuel and air mixing body. A gaseous fuel supply passage delivers gaseous fuel into the mixing body. A wall of the mixing body has air openings to communicate air into mixing passages. At least one fuel opening in each of the mixing passages allows fuel to flow into the mixing passages and mix with the air. There are passage sections downstream of a location of the fuel openings, such that the mixed air and fuel travel downstream of the location and into a combustion chamber. The passage sections have baffles that create a tortuous path. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: February 2, 2023
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Tin Cheung John Hu
  • Combustor primary zone cooling flow scheme
    Patent number: 10876730
    Abstract: A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: December 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hayley Ozem, Si-Man Amy Lao, Sri Sreekanth, Jeffrey Verhiel
  • Tank and filler tube device with protective arrangement
    Patent number: 9770978
    Abstract: A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: September 26, 2017
    Assignee: PRATT & WHITNEY CANADA CORPORATION
    Inventors: Marcin Rejman, Michel Labbe
  • Inertial particle separator duct assembly with splitter
    Patent number: 11692481
    Abstract: An inertial particle separator (IPS) duct assembly is disclosed having a duct having an inlet section extending downstream from an intake flow opening for receiving airflow to a junction, a scavenge flow section and a core flow section, the scavenge flow section and the core flow section splitting from the inlet section at the junction, the scavenge flow section having a scavenge flow outlet downstream of the junction, the core flow section having a core flow outlet downstream of the junction and fluidly connectable to the air intake of an engine core. A splitter cartridge is removably mounted at the junction, the splitter cartridge including a splitter body extending between a duct wall of the scavenge flow section and a duct wall of the core flow section.
    Type: Grant
    Filed: April 29, 2022
    Date of Patent: July 4, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Patrice Remy
Narrow Results

Filter by US Classification