Patents by Inventor Bruce Fielding
Bruce Fielding has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 10533424Abstract: A rotor for a gas turbine engine includes a hub having an outer periphery, a first plurality of blades arranged on the outer periphery of the hub, and a second plurality of blades arranged on the outer periphery of the hub. The first plurality of blades is made of a first material and has a first elastic modulus over density ratio. The first plurality of blades has a first natural frequency. The second plurality of blades is made of a second material and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented.Type: GrantFiled: April 20, 2015Date of Patent: January 14, 2020Assignee: Pratt & Whitney Canada Corp.Inventor: Bruce Fielding
-
Patent number: 9506361Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.Type: GrantFiled: March 8, 2013Date of Patent: November 29, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bruce Fielding, Nathan Tomes, Thomas Veitch
-
Publication number: 20160305251Abstract: A rotor for a gas turbine engine includes a hub having an outer periphery, a first plurality of blades arranged on the outer periphery of the hub, and a second plurality of blades arranged on the outer periphery of the hub. The first plurality of blades is made of a first material and has a first elastic modulus over density ratio. The first plurality of blades has a first natural frequency. The second plurality of blades is made of a second material and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented.Type: ApplicationFiled: April 20, 2015Publication date: October 20, 2016Inventor: Bruce FIELDING
-
Patent number: 9291070Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.Type: GrantFiled: December 2, 2011Date of Patent: March 22, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bruce Fielding, Assaf Farah, Karl D. Blume, Lam Nguyen, Theodore W Kapustka
-
Publication number: 20140255179Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.Type: ApplicationFiled: March 8, 2013Publication date: September 11, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Bruce FIELDING, Nathan TOMES, Thomas VEITCH
-
Patent number: 8313293Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.Type: GrantFiled: May 15, 2009Date of Patent: November 20, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver, Bruce Fielding, Carl Smythe
-
Publication number: 20120141294Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.Type: ApplicationFiled: December 2, 2011Publication date: June 7, 2012Inventors: Bruce Fielding, Assaf Farah, Karl D. Blume, Lam Nguyen, Theodore W. Kapustka
-
Patent number: 8075247Abstract: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.Type: GrantFiled: December 21, 2007Date of Patent: December 13, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Giuseppe Romani, Xiaoliu Liu, Paul Stone, Bruce Fielding
-
Patent number: 7926287Abstract: A method of operating a gas turbine engine having a rotatable turbine shaft with an electric machine mounted to the shaft. The method includes providing supplemental acceleration and/or deceleration of the turbine shaft of the gas turbine engine through the use of the electric machine operated as an electric motor and/or an electric generator, in order to avoid an undesirable engine speed range during engine operation.Type: GrantFiled: May 8, 2007Date of Patent: April 19, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Richard Ullyott, Bruce Fielding, Ronald Trumper
-
Publication number: 20100290903Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.Type: ApplicationFiled: May 15, 2009Publication date: November 18, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Jeffrey Bernard HEYERMAN, Bryan W. OLVER, Bruce FIELDING, Carl SMYTHE
-
Publication number: 20090162190Abstract: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.Type: ApplicationFiled: December 21, 2007Publication date: June 25, 2009Inventors: Giuseppe Romani, Xiaoliu Liu, Paul Stone, Bruce Fielding
-
Patent number: 7530782Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined about a circumference of the shroud and vanes extending radially from the shroud with a vane tip in each opening. Isolating apparatus are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining apparatus for restricting movement of the vane tip in an axial direction relative to the shroud.Type: GrantFiled: September 12, 2005Date of Patent: May 12, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Barry Barnett, Bruce Fielding
-
Publication number: 20080276620Abstract: A method of operating a gas turbine engine having a rotatable turbine shaft with an electric machine mounted to the shaft. The method includes providing supplemental acceleration and/or deceleration of the turbine shaft of the gas turbine engine through the use of the electric machine operated as an electric motor and/or an electric generator, in order to avoid an undesirable engine speed range during engine operation.Type: ApplicationFiled: May 8, 2007Publication date: November 13, 2008Inventors: Richard Ullyott, Bruce Fielding, Ronald Trumper
-
Publication number: 20070237632Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined therein about a circumference thereof and vanes extending radially from the shroud with a vane tip in each opening. Isolating means are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining means for restricting movement of the vane tip in an axial direction relative to said shroud.Type: ApplicationFiled: September 12, 2005Publication date: October 11, 2007Inventors: Barry Barnett, Bruce Fielding