Patents by Inventor Richard David Cedar
Richard David Cedar 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: 11555449Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.Type: GrantFiled: November 3, 2020Date of Patent: January 17, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Mustafa Dindar, Joseph Donofrio, Richard David Cedar, David William Crall
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Patent number: 11434819Abstract: An acoustic liner may include an acoustic core having an array of resonant cells, and an acoustic screen disposed across the array of resonant cells. The resonant cells include a plurality of cell walls and a resonant space defined by the plurality of cell walls. The acoustic core may include a folded acoustic core. Additionally, or in the alternative, at least some of the resonant cells may include an oblique polyhedral cellular structure and/or a multitude of sound-attenuating protuberances. The acoustic screen may include a reticulate membrane and a support lattice.Type: GrantFiled: March 29, 2019Date of Patent: September 6, 2022Assignees: GENERAL ELECTRIC COMPANY, MRA SYSTEMS, LLCInventors: Shanmugam Murugappan, Michael Moses Martinez, Egbert Geertsema, Rudramuni Kariveerappa Majjigi, Richard David Cedar, Wendy Wenling Lin, Robert William Davidoff, David Patrick Calder, Graham Frank Howarth
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Publication number: 20220106907Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.Type: ApplicationFiled: December 15, 2021Publication date: April 7, 2022Inventors: William Joseph Bowden, David Vickery Parker, Mark Gregory Wotzak, Richard David Cedar
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Publication number: 20210231054Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.Type: ApplicationFiled: November 3, 2020Publication date: July 29, 2021Inventors: Mustafa Dindar, Joseph Donofrio, Richard David Cedar, David William Crall
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Patent number: 11059559Abstract: The present disclosure provides acoustic structures and related systems and methods which may be used to dampen or attenuate sound waves, including, for example, noise generated by or emanating from various aspects or components of turbomachines such as turbine engines. These acoustic structures include oblique polyhedral cellular structures, including converging polyhedral cells and diverging polyhedral cells, and related systems and methods of making and using such acoustic structures.Type: GrantFiled: March 5, 2018Date of Patent: July 13, 2021Assignee: General Electric CompanyInventors: Richard David Cedar, Michael William Siekman
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Patent number: 10971128Abstract: An acoustic liner (20) with perforation (30) and method of constructing (100) an acoustic liner including forming perforations in the facing sheet by grit blasting (104) the facing sheet and mounting (106) the facing sheet to one side of a support layer having a set of partitioned cavities wherein the facing sheet closes an open face of the cavities except for the perforations to form a set of acoustic resonator cells.Type: GrantFiled: April 10, 2015Date of Patent: April 6, 2021Assignee: MRA SYSTEMS, LLCInventors: Andrew Michael Roach, Graham Frank Howarth, Steven Thomas Davies, Richard David Cedar, Michael Moses Martinez, Timothy Richard Depuy
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Patent number: 10961913Abstract: An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.Type: GrantFiled: March 10, 2015Date of Patent: March 30, 2021Assignee: MRA SYSTEMS, LLCInventors: Graham Frank Howarth, Andrew Michael Roach, Steven Thomas Davies, Richard David Cedar, Michael Moses Martinez, Timothy Richard DePuy
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Patent number: 10907495Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.Type: GrantFiled: May 11, 2020Date of Patent: February 2, 2021Assignee: General Electric CompanyInventors: Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Richard David Cedar
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Patent number: 10837362Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.Type: GrantFiled: October 12, 2016Date of Patent: November 17, 2020Assignee: General Electric CompanyInventors: Mustafa Dindar, Joseph Donofrio, Richard David Cedar, David William Crall
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Patent number: 10814955Abstract: An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.Type: GrantFiled: February 7, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Jixian Yao, Nikolai N. Pastouchenko, Patrick John Lonneman, Patrick Michael Marrinan, Richard David Cedar
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Publication number: 20200309028Abstract: An acoustic liner may include an acoustic core having an array of resonant cells, and an acoustic screen disposed across the array of resonant cells. The resonant cells include a plurality of cell walls and a resonant space defined by the plurality of cell walls. The acoustic core may include a folded acoustic core. Additionally, or in the alternative, at least some of the resonant cells may include an oblique polyhedral cellular structure and/or a multitude of sound-attenuating protuberances. The acoustic screen may include a reticulate membrane and a support lattice.Type: ApplicationFiled: March 29, 2019Publication date: October 1, 2020Inventors: Shanmugam Murugappan, Michael Moses Martinez, Egbert Geertsema, Rudramuni Kariveerappa Majjigi, Richard David Cedar, Wendy Wenling Lin, Robert William Davidoff, David Patrick Calder, Graham Frank Howarth
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Publication number: 20200271010Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.Type: ApplicationFiled: May 11, 2020Publication date: August 27, 2020Inventors: Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Richard David Cedar
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Patent number: 10669881Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.Type: GrantFiled: October 23, 2013Date of Patent: June 2, 2020Assignee: General Electric CompanyInventors: Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Richard David Cedar
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Patent number: 10563578Abstract: An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.Type: GrantFiled: February 18, 2015Date of Patent: February 18, 2020Assignee: MRA Systems, LLCInventors: Andrew Michael Roach, Richard David Cedar, Steven Thomas Davies, Timothy Richard Depuy, Graham Frank Howarth, Michael Moses Martinez
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Publication number: 20190270504Abstract: The present disclosure provides acoustic structures and related systems and methods which may be used to dampen or attenuate sound waves, including, for example, noise generated by or emanating from various aspects or components of turbomachines such as turbine engines. These acoustic structures include oblique polyhedral cellular structures, including converging polyhedral cells and diverging polyhedral cells, and related systems and methods of making and using such acoustic structures.Type: ApplicationFiled: March 5, 2018Publication date: September 5, 2019Inventors: Richard David Cedar, Michael William Siekman
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Patent number: 10399664Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.Type: GrantFiled: May 4, 2016Date of Patent: September 3, 2019Assignee: General Electric CompanyInventors: William Joseph Bowden, Andrew Breeze-Stringfellow, Richard David Cedar, Syed Arif Khalid, Patrick John Lonneman, Aleksander Piotr Pasieczny, Daniel Lawrence Tweedt
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Publication number: 20190241248Abstract: An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.Type: ApplicationFiled: February 7, 2018Publication date: August 8, 2019Inventors: Jixian Yao, Nikolai N. Pastouchenko, Patrick John Lonneman, Patrick Michael Marrinan, Richard David Cedar
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Publication number: 20190107046Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.Type: ApplicationFiled: October 5, 2017Publication date: April 11, 2019Inventors: William Joseph Bowden, David Vickery Parker, Mark Gregory Wotzak, Richard David Cedar
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Patent number: 10167088Abstract: Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.Type: GrantFiled: October 19, 2015Date of Patent: January 1, 2019Assignee: General Electric CompanyInventors: Adam Wayne Clark, Richard David Cedar, David Baker Riddle
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Publication number: 20180237120Abstract: The present disclosure is directed to an aircraft including a fuselage to which a pair or more of wings attaches. The aircraft defines a transverse direction, a longitudinal direction, and a latitudinal direction. The aircraft includes a wing extended from the fuselage along the transverse direction in which the wing defines a leading edge, and a gas turbine engine coupled to the wing. The engine defines an axial centerline therethrough along the longitudinal direction. The engine includes a nacelle including an outer wall extended around the axial centerline. The nacelle defines a radial reference plane extended perpendicular from the axial centerline. The outer wall defines an outer wall point closest to the fuselage. The radial reference plane extends through a reference line defined along the latitudinal direction from the outer wall point to the leading edge of the wing.Type: ApplicationFiled: February 22, 2017Publication date: August 23, 2018Inventors: Brandon Wayne Miller, Richard Byron Stewart, Jeffrey Donald Clements, Richard David Cedar, David William Crall