Patents by Inventor Peter John Wood
Peter John Wood 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).
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Patent number: 11950967Abstract: A system for planning and performing a repeat interventional procedure is provided which includes a registration device and an image generation device which map current targets in a reference image for a first interventional procedure to at least one guidance image acquired from a different imaging modality. Biopsy locations are recorded to the guidance images during the first interventional procedure and the biopsy locations are mapped to the reference image to provide a planning image for use in a subsequent interventional procedure on the patient. In a subsequent interventional procedure, the prior planning image (124) may be registered to a current reference image and the prior biopsy locations and prior and current targets are mapped to a guidance image acquired from a different imaging modality. Biopsy locations are then mapped to the guidance image and mapped back to the current reference image.Type: GrantFiled: May 25, 2021Date of Patent: April 9, 2024Assignees: KONINKLIJKE PHILIPS N.V., THE UNITED STATES of AMERICA, as Represented by the Secreatary, Dept. of Health and Human ServicesInventors: Jochen Kruecker, Pingkun Yan, Amir Mohammad Tahmasebi Maraghoosh, Peter A Pinto, Bradford Johns Wood
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Patent number: 10443626Abstract: A circular row of non-uniformally spaced vanes includes only one first group and only one second group of adjacent vanes, unequal first and second spacing between adjacent vanes in the first and second groups, and first spacing greater than second spacing. An embodiment with second group including only three adjacent vanes. Second spacing may be about 25%-35% smaller than a nominal uniform spacing used as a design parameter for designing spacing of the non-uniformly spaced stator vanes. Circular row may be sectored. A gas turbine engine section may include one or more rings or circular rows of fixed and/or variable non-uniformally spaced vanes. Method for designing non-uniform vane spacing for circular row includes determining nominal uniform spacing and forming first spacing and second spacing from nominal uniform spacing of vanes.Type: GrantFiled: March 15, 2016Date of Patent: October 15, 2019Assignee: General Electric CompanyInventors: Mark Joseph Mielke, Peter John Wood, Brian Richard Green, Steven Mitchell Taylor, Curtis Moeckel, Mark Joseph Frisch, Joseph Michael Bruni
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Patent number: 10408217Abstract: An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.Type: GrantFiled: March 15, 2016Date of Patent: September 10, 2019Assignee: General Electric CompanyInventors: Curtis William Moeckel, Andrew Breeze-Stringfellow, Peter John Wood, Eric Andrew Falk
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Patent number: 10221859Abstract: An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.Type: GrantFiled: February 8, 2016Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: Curtis William Moeckel, Peter John Wood, Matthew Ford Adam, Eric Andrew Falk, Mark Joseph Stecher
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Patent number: 9982598Abstract: A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and close a bleed slot open to a booster bleed flowpath located outwardly of transition duct and having an airflow restrictor. Airflow restrictor may be variable such as a flapper valve. Booster bleed flowpath may pass through a bifurcated bleed duct including an inner passage radially bound by spaced apart inner and middle bleed walls and an outer passage radially bound by middle bleed wall and an outer bleed wall. Airflow restrictor may include an outlet area smaller than an inlet area of inner passage. Door seals against middle bleed wall to open inner passage and against outer bleed wall to open both passages.Type: GrantFiled: October 22, 2012Date of Patent: May 29, 2018Assignee: General Electric CompanyInventors: Byron Andrew Pritchard, Jr., Charles Daniel Califf, Peter John Wood, Raymond Gust Holm, Allan George van de Wall, Peter Alfred Pezzi
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Publication number: 20170268537Abstract: A circular row of non-uniformally spaced vanes includes only one first group and only one second group of adjacent vanes, unequal first and second spacing between adjacent vanes in the first and second groups, and first spacing greater than second spacing. An embodiment with second group including only three adjacent vanes. Second spacing may be about 25%-35% smaller than a nominal uniform spacing used as a design parameter for designing spacing of the non-uniformly spaced stator vanes. Circular row may be sectored. A gas turbine engine section may include one or more rings or circular rows of fixed and/or variable non-uniformally spaced vanes. Method for designing non-uniform vane spacing for circular row includes determining nominal uniform spacing and forming first spacing and second spacing from nominal uniform spacing of vanes.Type: ApplicationFiled: March 15, 2016Publication date: September 21, 2017Inventors: Mark Joseph Mielke, Peter John Wood, Brian Richard Green, Steven Mitchell Taylor, Curtis Moeckel, Mark Joseph Frisch, Joseph Michael Bruni
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Publication number: 20170268520Abstract: An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.Type: ApplicationFiled: March 15, 2016Publication date: September 21, 2017Inventors: Curtis William Moeckel, Andrew Breeze-Stringfellow, Peter John Wood, Eric Andrew Falk
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Publication number: 20170227016Abstract: An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.Type: ApplicationFiled: February 8, 2016Publication date: August 10, 2017Inventors: Curtis William Moeckel, Peter John Wood, Matthew Ford Adam, Eric Andrew Falk, Mark Joseph Stecher
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Patent number: 9054425Abstract: The present invention provides a high-performance and small sized helical antenna element and array thereof for use in an aircraft communication system or the like, where stringent spatial restrictions and gain requirements generally apply. The performance of the array is enhanced by increasing the lateral distances between the antenna elements over a portion of the elements where the windings thereof have high current amplitude. The sweeping envelope of the array is maintained small by recovering the initial distancing over a portion of the elements where the windings thereof have low current amplitude.Type: GrantFiled: March 9, 2010Date of Patent: June 9, 2015Assignee: EMS Technologies Canada, Ltd.Inventors: Colin Sutherland, Peter John Wood, Peter C. Strickland
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Publication number: 20140109589Abstract: A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and close a bleed slot open to a booster bleed flowpath located outwardly of transition duct and having an airflow restrictor. Airflow restrictor may be variable such as a flapper valve. Booster bleed flowpath may pass through a bifurcated bleed duct including an inner passage radially bound by spaced apart inner and middle bleed walls and an outer passage radially bound by middle bleed wall and an outer bleed wall. Airflow restrictor may include an outlet area smaller than an inlet area of inner passage. Door seals against middle bleed wall to open inner passage and against outer bleed wall to open both passages.Type: ApplicationFiled: October 22, 2012Publication date: April 24, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Byron Andrew Pritchard, JR., Charles Daniel Califf, Peter John Wood, Raymond Gust Holm, Allan George van de Wall, Peter Alfred Pezzi
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Patent number: 8517677Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: GrantFiled: May 31, 2012Date of Patent: August 27, 2013Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20120280875Abstract: The present invention provides a high-performance and small sized helical antenna element and array thereof for use in an aircraft communication system or the like, where stringent spatial restrictions and gain requirements generally apply. The performance of the array is enhanced by increasing the lateral distances between the antenna elements over a portion of the elements where the windings thereof have high current amplitude. The sweeping envelope of the array is maintained small by recovering the initial distancing over a portion of the elements where the windings thereof have low current amplitude.Type: ApplicationFiled: March 9, 2010Publication date: November 8, 2012Applicant: EMS TECHNOLOGIES CANADA, LTD.Inventors: Colin Sutherland, Peter John Wood, Peter C. Strickland
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Patent number: 8292574Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: GrantFiled: November 30, 2006Date of Patent: October 23, 2012Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20120237344Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: ApplicationFiled: May 31, 2012Publication date: September 20, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Patent number: 8087884Abstract: A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.Type: GrantFiled: November 30, 2006Date of Patent: January 3, 2012Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Patent number: 7967571Abstract: A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.Type: GrantFiled: November 30, 2006Date of Patent: June 28, 2011Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20100260609Abstract: A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.Type: ApplicationFiled: November 30, 2006Publication date: October 14, 2010Inventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20100170224Abstract: A booster system is disclosed, comprising a first rotor stage having a plurality of first rotor blades spaced circumferentially around a rotor hub with a longitudinal axis and having a first pitch-line radius extending from the longitudinal axis, a last rotor stage located axially aft from the first rotor stage, the last rotor stage comprising a plurality of last rotor blades spaced circumferentially around the longitudinal axis and having a second pitch-line radius extending from the longitudinal axis, and a gooseneck duct located axially aft from the last rotor stage and capable of receiving an airflow, the gooseneck duct comprising an inlet end and an exit end located at a distance axially aft from the inlet end and having at least one plasma actuator mounted in the gooseneck duct.Type: ApplicationFiled: January 8, 2009Publication date: July 8, 2010Inventors: DAVID SCOTT CLARK, ASPI RUSTOM WADIA, CHING PANG LEE, PETER JOHN WOOD
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Patent number: 7730714Abstract: A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.Type: GrantFiled: November 29, 2005Date of Patent: June 8, 2010Assignee: General Electric CompanyInventors: Peter John Wood, Ruby Lasandra Zenon, Donald George LaChapelle, Mark Joseph Mielke, Carl Grant
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Publication number: 20080131271Abstract: A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey