Search Patents
  • Blade under platform pocket cooling
    Patent number: 8152436
    Abstract: Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.
    Type: Grant
    Filed: January 8, 2008
    Date of Patent: April 10, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David F. Glasspoole, François Caron
  • Shroud leading edge cooling
    Patent number: 7246989
    Abstract: A cooling device includes a plurality of passages extending through outer platforms of turbine vane segments for directing cooling air in a choked flow condition towards a downstream turbine shroud.
    Type: Grant
    Filed: December 10, 2004
    Date of Patent: July 24, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David Glasspoole, Ricardo Trindade
  • Leakage control in a gas turbine engine
    Patent number: 7128522
    Abstract: A gas turbine engine expansion joint comprises first and second members having confronting faces defining a gap therebetween. At room temperature, the gap varies in accordance with the temperature distribution profile of the first and second members during normal engine operation.
    Type: Grant
    Filed: October 28, 2003
    Date of Patent: October 31, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Martin Jutras
  • Dynamically tuned turbine blade growth pocket
    Patent number: 8167572
    Abstract: A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket.
    Type: Grant
    Filed: July 14, 2008
    Date of Patent: May 1, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Marc Tardif, Harris Shafique, Mario Guerra
  • Shroud and vane segments having edge notches
    Patent number: 7114920
    Abstract: Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent segments.
    Type: Grant
    Filed: June 25, 2004
    Date of Patent: October 3, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Remy Synnott
  • Rotor casing treatment with recessed baffles
    Patent number: 8337146
    Abstract: A compressor rotor casing treatment comprises a plurality of axially spaced-apart circumferential grooves defined in the inner surface of the compressor casing adjacent the tips of the compressor rotor blades. A plurality of circumferentially spaced-apart recessed baffles projects from a bottom surface of each groove to a distance less than a full height of the groove.
    Type: Grant
    Filed: June 3, 2009
    Date of Patent: December 25, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Hong Yu
  • Shroud segment cooling configuration
    Patent number: 8246297
    Abstract: An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.
    Type: Grant
    Filed: July 21, 2008
    Date of Patent: August 21, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kapila Jain, Marc Tardif
  • SEALING FOR VANE SEGMENTS
    Publication number: 20110081237
    Abstract: A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array.
    Type: Application
    Filed: October 1, 2009
    Publication date: April 7, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON
  • BLADE OUTER AIR SEAL SUPPORT
    Publication number: 20110044804
    Abstract: A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case.
    Type: Application
    Filed: July 20, 2010
    Publication date: February 24, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco DiPaola, Roger Gates
  • Sealing and cooling at the joint between shroud segments
    Patent number: 8684680
    Abstract: A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform. Cooling underneath the radial seals may be done by conduction heath transfer through the platform of the shroud segments.
    Type: Grant
    Filed: August 27, 2009
    Date of Patent: April 1, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Yves Martin, Franco Di Paola
  • Turbine shroud segment with integrated impingement plate
    Patent number: 8784037
    Abstract: A turbine shroud segment is metal injection molded (MIM) about an insert having a cooling air cavity covered by an impingement plate. The insert is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the insert.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • BLADE OUTER AIR SEAL COOLING
    Publication number: 20110044801
    Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.
    Type: Application
    Filed: July 20, 2010
    Publication date: February 24, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Kapila Jain
  • Shroud segment arrangement for gas turbine engines
    Patent number: 8240985
    Abstract: The gas turbine engine shroud comprises a plurality of circumferentially-disposed and concentric shroud segments. Each shroud segment has an arc-shaped platform with opposite ends, each end comprising an inter-segment seal slot, at least one slot extending substantially across each corresponding end and having a lengthwise-variable depth.
    Type: Grant
    Filed: April 29, 2008
    Date of Patent: August 14, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Yves Martin
  • Sheet metal turbine or compressor static shroud
    Patent number: 6918743
    Abstract: A static shroud for ducting an axial gas flow past an array of blades rotating about an axis, made of a sheet of metal bent to form a contiguous shroud body having a substantially uniform sheet thickness and a uniform axial profile, initiating with an upstream flange flowing into a tip clearance portion and terminating in a downstream flange.
    Type: Grant
    Filed: October 23, 2002
    Date of Patent: July 19, 2005
    Assignee: Pratt & Whitney Canada Ccorp.
    Inventors: Eugene Gekht, Franco Di Paola
  • ACTIVE TIP CLEARANCE CONTROL ARRANGEMENT FOR GAS TURBINE ENGINE
    Publication number: 20100247297
    Abstract: An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance.
    Type: Application
    Filed: March 26, 2009
    Publication date: September 30, 2010
    Applicant: PRATT & WHITNEY CANADA CORP
    Inventors: Pierre-Yves LEGARE, Stephen MAH
  • Blade outer air seal cooling
    Patent number: 8740551
    Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: June 3, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Franco Di Paola, Kapila Jain
  • Turbine shroud cooling
    Patent number: 11274569
    Abstract: A turbine shroud segment has a body extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. Upstream and downstream plenums are defined in the body. The upstream plenum has a plurality of cooling inlets. The downstream plenum has a plurality of cooling outlets. A flow constricting slot extends across the body between the first and second lateral edges. The flow constricting slot fluidly connects the downstream plenum to the upstream plenum.
    Type: Grant
    Filed: October 24, 2019
    Date of Patent: March 15, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mohammed Ennacer, Ion Dinu
  • APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR
    Publication number: 20100040453
    Abstract: A compressor comprises a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips.
    Type: Application
    Filed: October 30, 2008
    Publication date: February 18, 2010
    Applicants: PRATT & WHITNEY CANADA CORP., POLYVALOR S.E.C.
    Inventor: Huu Duc VO
  • Turbine shroud segment seal
    Patent number: 7207771
    Abstract: A ring seal for sealing an annular gap defined between opposed surfaces of concentric inner and outer annular engine parts in a gas turbine engine. The ring seal being wholly disposed within the annular gap and having a wave pattern with alternating peaks. The ring seal radially inwardly loads the inner engine part and provides a fluid seal between the inner and outer engine parts.
    Type: Grant
    Filed: October 15, 2004
    Date of Patent: April 24, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remy Synnott, Dany Blais
  • Turbine shroud cooling system
    Patent number: 8182199
    Abstract: A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring, and impinging cooling air on to an outer surface of the shroud ring. More cooling air is impinged onto regions which correspond to the high temperature regions on the shroud ring than to regions corresponding to the lower temperature regions of the shroud ring.
    Type: Grant
    Filed: February 1, 2007
    Date of Patent: May 22, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Assaf Farah, Terrence Lucas