Search Patents
  • Method of making a structural reinforcement strut for a turbine exhaust case of a gas turbine engine
    Patent number: 8561415
    Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.
    Type: Grant
    Filed: March 1, 2013
    Date of Patent: October 22, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mike Fontaine, Rene Paquet, Jean Fournier
  • Normally open reverse flow flapper valve
    Patent number: 7114519
    Abstract: A fluid flow actuated valve for controlling the fluid flow in a conduit comprises a support structure adapted to be mounted within the conduit and at least one flap member pivotally mounted to the support structure. The at least one flap member is pivotable between an first position for a minimum fluid flow and a second position for a maximum fluid flow. A torsion spring is attached to the at least one flap member to urge the same to pivot against a fluid pressure differential, from the first position to the second position when the fluid pressure differential is smaller than a predetermined level.
    Type: Grant
    Filed: December 17, 2004
    Date of Patent: October 3, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Paul Archibald Aitchison, Patrick David Germain, Henry Smith
  • IMPELLER REAR CAVITY THRUST ADJUSTOR
    Publication number: 20080193277
    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: Application
    Filed: February 14, 2007
    Publication date: August 14, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Pierre-Yves LEGARE
  • Oil tank installation in gas turbine engine
    Patent number: 10816007
    Abstract: Oil tanks for gas turbine engines and associated assembly methods are disclosed. In one exemplary embodiment, an oil tank is configured to be installed to occupy a radially-inner space defined by an annular radial air inlet duct of a reverse flow gas turbine engine. The oil tank may comprise a first tank portion and a second tank portion assembled together to cooperatively define an interior volume of the tank. An optional intermediate spacer may be disposed between the first tank portion and the second tank portion in order to form an oil tank of a larger size.
    Type: Grant
    Filed: November 11, 2016
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Desjardins, Francis Bonacorsi, Keith Morgan
  • Bleed valve actuating system for a gas turbine engine
    Patent number: 7850419
    Abstract: The bleed valve actuating system is for use in a gas turbine engine. The system comprises an actuator mounted adjacent the engine case and having a main actuation axis extending generally parallel to a surface of the engine case. A drive rod extends from the bleed valve to the actuator generally perpendicularly with reference to the main actuation axis of the actuator. The drive rod connected to the actuator via a linkage mechanically connects the actuator to the drive rod. The linkage is configured to convert axial motion of the actuator along the main actuation axis into generally perpendicular motion of the drive rod.
    Type: Grant
    Filed: November 30, 2006
    Date of Patent: December 14, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ljubisa Vrljes, Christopher Daniel Ongley, Zoran Markovic
  • INTEGRATED STRUT-VANE
    Publication number: 20140255159
    Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.
    Type: Application
    Filed: March 7, 2013
    Publication date: September 11, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: VINCENT PARADIS, EDWARD VLASIC, PANAGIOTA TSIFOURDARIS
  • Turbine shroud segment with inter-segment overlap
    Patent number: 10328490
    Abstract: A method of manufacturing a turbine shroud segment for a gas turbine engine comprises: metal injection molding (MIM) a shroud segment body with a groove defined in a first lateral side thereof and with a flow restrictor projecting integrally from an opposite second lateral side thereof. The groove is oversized relative to the flow restrictor to provide for a clearance fit between the flow restrictor and the groove of adjacent turbine shroud segments when assembled together in a ring formation. The shroud segment body with the integrated flow restrictor are then subjected to debinding and sintering operations.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 25, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Turbine blade airfoil profile
    Patent number: 11572789
    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: November 11, 2021
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Constantinos Ravanis, Vincent Paradis, Eduardo Hawie, Michael Papple, Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Philippe Boyer, Jasrobin Grewal
  • Multi-phase cable
    Patent number: 9991029
    Abstract: A multi-phase cable, the cable including a plurality of conductors for conducting currents of two or more different phases, each phase being associated with one or more conductors and each conductor being associated with one respective phase. Each conductor has a cross-section with at least one dimension that is sized to decrease a skin effect of the conductor at a maximum or nominal operation frequency of the conductor. The conductors are arranged to permit free air cooling of the cable on at least two sides of each conductor, and such that each conductor of a given phase has, as immediate neighbors, only conductors of one or more different phases.
    Type: Grant
    Filed: November 27, 2012
    Date of Patent: June 5, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Antwan Shenouda
  • OIL FEED ASSEMBLY
    Publication number: 20080073154
    Abstract: An oil feed assembly suitable for use in a gas turbine engine having a bearing housing, an outer ring surrounding the bearing housing and a monocase extending therebetween. The assembly provides an oil supply tube for extension within the monocase and between the outer ring and the bearing housing. An oil nozzle support means is employed for selective releasable engagement with one end of the oil supply tube. This is also supported by an oil supply tube support means for selective releasable engagement with a second end of the oil supply tube. A coupling means for coupling said oil supply tube support means and the outer ring completes the assembly.
    Type: Application
    Filed: September 27, 2006
    Publication date: March 27, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas ELEFTHERIOU, David DENIS, Denis LECLAIR, Julien GARON, Jean FOURNIER
  • Gaseous fuel leakage from fuel system manifold to engine
    Patent number: 11767795
    Abstract: There are describes methods and systems for operating an engine coupled to a fuel system having a fuel manifold configured to supply fuel to a combustor of the engine. The method comprises receiving a gaseous fuel flow request indicative of a change in demand for gaseous fuel to the engine; applying a fuel loss bias to the gaseous fuel flow request to obtain a biased fuel flow request, the fuel loss bias associated with a change in mass flow rate of the gaseous fuel from the fuel manifold to the combustor in response to the change in demand; and causing the gaseous fuel to flow into the combustor in accordance with the biased fuel flow request.
    Type: Grant
    Filed: August 19, 2021
    Date of Patent: September 26, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Dillon, Todd Miller
  • Gas turbine engine exhaust system
    Patent number: 10508599
    Abstract: An exhaust system for a gas turbine engine, such as an APU, comprises a pressure vessel having an annular wall circumscribing an exhaust plenum. The annular wall is composed of an arrangement of individual tubes assembled side-by-side around a central axis of the exhaust plenum. The tubes are fed with pressurized cooling air, such as P3 air. A heat exchanger in heat transfer relationship with the exhaust gases flowing through the exhaust plenum receives air from the tubes. The heat transferred from the exhaust gases to the air circulated through the heat exchanger may be used to provide pre-heated air to the engine combustor.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: December 17, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David H Menheere, Adam Trumpour
  • Machine having a liquid lubrication system and a shaft
    Patent number: 11692466
    Abstract: A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.
    Type: Grant
    Filed: May 30, 2019
    Date of Patent: July 4, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Dana Tomescu, Daniel Alecu
  • Gas turbine engine with bearing buffer air flow and method
    Patent number: 9617916
    Abstract: The gas turbine engine has a bleed air aperture formed in the radially outer wall upstream from the combustor and a bearing cavity formed within the radially inner wall, at least two bearing seals enclosing at least one bearing in the bearing cavity and separating the bearing cavity from associated buffer air entry points, an oil supply system including oil paths leading to each of the bearings; a buffer air supply system including buffer air paths leading to each of the entry points and a baffle partitioning one of the entry points.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: April 11, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Pierre-Yves Légaré, Alessandro Ciampa, Michel Labbé
  • Fuel nozzle and associated method of assembly
    Patent number: 11486581
    Abstract: The fuel nozzle can have a proximal member having a first mating portion defined around an assembly axis, a first fluid conduit internal to the proximal member and spaced apart from the assembly axis, and a first stop facing a first circumferential direction; and a distal member having a second mating portion configured for axial engagement with the first mating portion along the assembly axis, a second stop facing a second circumferential direction, the second circumferential direction opposite the first circumferential direction and configured to abut against the first stop when the distal member and proximal member are axially engaged to one another in a predetermined relative circumferential alignment.
    Type: Grant
    Filed: September 29, 2020
    Date of Patent: November 1, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Nadia Swaby
  • ELECTRIC DISTRIBUTED PROPULSION USING EXHAUST RECOVERY POWER
    Publication number: 20220297843
    Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.
    Type: Application
    Filed: March 19, 2021
    Publication date: September 22, 2022
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Todd A. Spierling
  • MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE
    Publication number: 20100135770
    Abstract: A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine.
    Type: Application
    Filed: November 28, 2008
    Publication date: June 3, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON, Lam NGUYEN
  • Multiple zone cooling apparatus
    Patent number: 8784022
    Abstract: A cooling assembly for a machine tool including at least first and second nozzle rings mounted on the spindle housing, respectively defining first and second coolant conduits and respectively including first and second pluralities of nozzles in fluid communication with the respective conduit. Each first nozzle is oriented with an outlet thereof directed toward a first machining zone containing cutting edges of at last one tool having a first length. Each second nozzle is oriented with an outlet thereof directed toward a second machining zone different from the first machining zone and containing the cutting edges of at least one tool having a second length.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: James Leishman, Fuat Atabey
  • Gas turbine engine with bearing support structure
    Patent number: 11391179
    Abstract: The gas turbine engine can have a structure for holding bearings within a casing, with a shaft being rotatably mounted to the casing via the bearings and via the structure, the structure having a first wall segment and a base structure receiving the bearings, the first wall segment having a proximal end structurally joined to the base structure, the first wall segment extending away from the base structure, and having a portion extending at least partially axially and thereby being radially flexible relative to the second wall segment, the structure providing both structural resistance and radial stretchability.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott, François Doyon
  • Mistuned fan for gas turbine engine
    Patent number: 10837459
    Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: November 17, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Daniel Fudge, Kari Heikurinen, Paul Stone, Ignatius Theratil, Peter Townsend, Tibor Urac
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