Search Patents
  • BLADE OUTER AIR SEAL ANTI-ROTATION
    Publication number: 20110044803
    Abstract: A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other.
    Type: Application
    Filed: July 20, 2010
    Publication date: February 24, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Bruno Chatelois
  • Axial load damping system for rotor shaft
    Patent number: 8696312
    Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: April 15, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Charles Faubert, André D. Leblanc
  • Tandem electric machine arrangement
    Patent number: 8710708
    Abstract: The tandem electric machine arrangement comprises an outside rotor having two axially spaced-apart sets of circumferentially-disposed permanent magnets. It also comprises an inside stator having at least two electrically-independent windings, the at least two windings axially spaced apart from one another and disposed relative to the magnet sets to thereby be magnet coupled to a respective one of the sets of permanent magnets during rotation of the rotor. One of the rotor and the stator is provided in two separate pieces, each piece supported from opposite axial sides of the electric machine relative to one another. The other of the rotor and the stator is supported from substantially centrally of the two pieces.
    Type: Grant
    Filed: May 16, 2013
    Date of Patent: April 29, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan Dooley, Joseph Brand
  • Machine tool certification for part specific working volume
    Patent number: 10852709
    Abstract: A method for machining a selected part with a machine tool, comprises obtaining a master part replicating at least a portion of a geometry of a selected part. The master part is loaded in a machine tool. A signature of the machine tool is defined by measuring at least dimensional data of the master part relative to the machine tool, the dimensional data being limited to a selected-part-specific working volume substantially smaller than a complete working volume of the machine tool. The machine tool is certified as being within tolerances to machine the selected part within the working volume, using the dimensional data of the signature. The selected part is machined from a workpiece with the machine tool.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: December 1, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mario Blais, Philippe St-Jacques
  • Exhaust gas discharge system and plenum
    Patent number: 8221073
    Abstract: An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: July 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ian Macfarlane, Zenon Szlanta
  • Method of manufacturing a rotary engine casing
    Patent number: 10995660
    Abstract: A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed.
    Type: Grant
    Filed: October 9, 2019
    Date of Patent: May 4, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Villeneuve, Jean-Gabriel Gauvreau
  • Feedback device with differing magnetic permeability zones
    Patent number: 11371825
    Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having 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 comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, 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: June 28, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Durand, Richard Kudrna, Ian Farrell
  • Method to seal damper cavity of multi-film oil damper
    Patent number: 10808755
    Abstract: A multi-film oil damper suited for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall and radially extending side walls; an inner damper ring; an outer damper ring disposed between the inner damper ring and the radially outward wall of the annular damper cavity; wherein the annular damper cavity has an oil inlet in communication with a source of pressurized oil; and wherein a radial thickness of the inner damper ring exceeds a radial thickness of the outer damper ring.
    Type: Grant
    Filed: March 4, 2019
    Date of Patent: October 20, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, David Beamish
  • Aircraft power plant
    Patent number: 11866181
    Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.
    Type: Grant
    Filed: September 15, 2021
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Serge Dussault
  • Oil seal arrangement for rotary internal combustion engine
    Patent number: 8985085
    Abstract: A rotor of a rotary internal combustion engine, including an annular oil seal assembly snugly received within each oil seal groove, each oil seal assembly including a seal ring retaining first and second axially spaced apart annular sealing elements in substantial radial alignment with one another, the seal ring radially pressing each of the sealing elements in sealing engagement with a respective surface in the groove in opposite directions from one another, and a spring member biasing the seal ring axially away from the end face.
    Type: Grant
    Filed: October 12, 2011
    Date of Patent: March 24, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eugene Gekht, Sebastien Bolduc, Mike Fontaine
  • Machine tool certification for part specific working volume
    Patent number: 9971337
    Abstract: A method for machining a selected part with a machine tool, comprises obtaining a master part replicating at least a portion of a geometry of a selected part. The master part is loaded in a machine tool. A signature of the machine tool is defined by measuring at least dimensional data of the master part relative to the machine tool, the dimensional data being limited to a selected-part-specific working volume substantially smaller than a complete working volume of the machine tool. The machine tool is certified as being within tolerances to machine the selected part within the working volume, using the dimensional data of the signature. The selected part is machined from a workpiece with the machine tool.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: May 15, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mario Blais, Philippe St-Jacques
  • Bearing support with frangible tabs
    Patent number: 11499447
    Abstract: A gas turbine engine has: an engine shaft rotatable about a rotation axis; at least two bearings spaced apart from one another along the rotation axis, the at least two bearings having inner races for rotation with the engine shaft, outer races, and rolling elements disposed radially between the inner races and the outer races; a bearing support extending axially along the rotation axis from one of the at least two bearings to the other, the bearing support secured to both of the outer races of the at least two bearings, the bearing support secured to a structural case of the gas turbine engine via frangible tabs.
    Type: Grant
    Filed: January 15, 2020
    Date of Patent: November 15, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, François Doyon
  • Impeller
    Patent number: 10669854
    Abstract: An impeller comprises a hub and blades extending therefrom. The blades include splitter blades interspersed between full blades. First flow channels are defined between pressure sides of the splitter blades and suction sides of the full blades. Second flow channels are defined between suction sides of the splitter blades and pressure sides of the full blades. A width of the first flow channels at leading edges of the splitter blades and at the hub is less than a width of the second flow channels at the leading edges of the splitter blades and at the hub. The width of the first flow channels at the leading edges of the splitter blades and at the tips is more than the width of the second flow channels at the leading edges of the splitter blades and at the tips.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hien Duong
  • Compressor rotor casing with swept grooves
    Patent number: 11346367
    Abstract: The compressor for a gas turbine engine includes a rotor with blades, and a shroud surrounding the rotor and having an inner surface surrounding tips of the blade. A plurality of grooves are defined in the inner surface of the shroud adjacent the blade tips, the grooves extending circumferentially about the shroud and extending radially from groove inlet openings defined in the inner surface to closed end surfaces of the grooves. The grooves are axially spaced-apart from each other and disposed axially between the leading and trailing edges of the blades. The grooves have a forwardly swept angle from the inner surface, and circumferential interruptions such that the grooves extend non-continuously around the shroud circumference.
    Type: Grant
    Filed: July 30, 2019
    Date of Patent: May 31, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hong Yu, Feng Shi
  • Method and apparatus for controlling fuel flow to an engine
    Patent number: 7100378
    Abstract: A method for selectively interrupting fuel flow to an engine. The method comprises: in a normal mode, enabling a normal interruption signal for interrupting the fuel flow in response to a normal shutdown signal; and in an emergency mode, enabling an emergency interruption signal for interrupting the fuel flow in response to at least the normal shutdown signal and an emergency shutdown signal having transient characteristics. The normal shutdown signal has a given normal value and the emergency shutdown signal has a peak value substantially larger than the given normal value, whereby the fuel flow interrupting occurs faster in response to the emergency shutdown signal than in response to the normal shutdown signal.
    Type: Grant
    Filed: March 21, 2006
    Date of Patent: September 5, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Peter John David Matthews
  • Reverse flow combustor duct attachment
    Patent number: 8864492
    Abstract: A reverse flow combustor has an inlet end. A flowpath extends downstream from the inlet end through a turn. The turn directs the flowpath radially inward and reversing an axial flow direction. A large exit duct (LED) is along the turn. A small exit duct (SED) is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction. The joint comprises: a first surface on the SED facing partially radially inward; and a mounting feature engaging the first surface.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: October 21, 2014
    Assignees: United Technologies Corporation, Pratt & Whitney Canada Corp.
    Inventors: Jun Shi, David C. Jarmon, Lee A. Hoffman, David J. Bombara, Shaoluo L. Butler, Lev A. Prociw, Aleksandar Kojovic
  • Electric machine systems having magnetised bi-pole rotors
    Patent number: 11909283
    Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.
    Type: Grant
    Filed: April 15, 2021
    Date of Patent: February 20, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Latulipe, Richard Freer
  • Shaft decouple logic for gas turbine
    Patent number: 6176074
    Abstract: The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses these parameters for making a determination of shaft decoupling in fractions of a second, before serious damage to the gas turbine engine can occur. The control logic also utilizes multiple interval sampling, and sampling over multiple channels to verify any determination of shaft decoupling. Once a shaft decouple has been verified, fuel flow to the engine is cut off, thus shutting down the engine.
    Type: Grant
    Filed: June 5, 1998
    Date of Patent: January 23, 2001
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andrew Hayes Thompson, Carmine Lisio, Antonio Hernani Nobre
  • Aircraft engine, gas turbine intake therefore, and method of guiding exhaust gasses
    Patent number: 11851202
    Abstract: The gas turbine intake can have a swirl housing having an inlet portion fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.
    Type: Grant
    Filed: June 23, 2022
    Date of Patent: December 26, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Christopher Gover, Remy Synnott
  • INTERNAL MANIFOLD WITH FUEL INLET
    Publication number: 20150198096
    Abstract: An internal fuel manifold assembly includes a fuel manifold ring having at least one fuel conveying passage in fluid flow communication with at least one inlet passage defined through an inlet member. The inlet member is connected to the manifold ring proximate its first end and connected proximate its second end to at least one transfer tube. The inlet member includes a drainage passage for collecting possible leaked fuel from an annulus, defined between the inlet member and a heat shield surrounding the inlet member and spaced apart therefrom. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Application
    Filed: January 16, 2014
    Publication date: July 16, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
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