Patents by Inventor Mark Huzzard CUNNINGHAM
Mark Huzzard CUNNINGHAM 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: 10899464Abstract: The aircraft can have an aircraft engine and a cowl, the engine having an engine part disposed within the cowl, the cowl having a cowl section movable relative to a remainder of the cowl, the engine further having a gas path duct internal to the cowl with a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section moveable between a first position in which the first portion and the second portion are in fluid flow communication with one another and a second position in which the cowl section and the second portion are moved away from the first portion, wherein in the first position at least the second portion obstructs external access to the engine part and in the second position at least the second portion is displaced to permit external access to the engine part.Type: GrantFiled: March 14, 2018Date of Patent: January 26, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Paul Weaver, Scott Smith, Mark Huzzard Cunningham
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Patent number: 10794280Abstract: An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.Type: GrantFiled: May 8, 2018Date of Patent: October 6, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guo Rong Yan, Mark Huzzard Cunningham
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Publication number: 20190283893Abstract: The aircraft can have an aircraft engine and a cowl, the engine having an engine part disposed within the cowl, the cowl having a cowl section movable relative to a remainder of the cowl, the engine further having a gas path duct internal to the cowl with a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section moveable between a first position in which the first portion and the second portion are in fluid flow communication with one another and a second position in which the cowl section and the second portion are moved away from the first portion, wherein in the first position at least the second portion obstructs external access to the engine part and in the second position at least the second portion is displaced to permit external access to the engine part.Type: ApplicationFiled: March 14, 2018Publication date: September 19, 2019Inventors: Paul WEAVER, Scott SMITH, Mark Huzzard CUNNINGHAM
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Publication number: 20180328283Abstract: An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.Type: ApplicationFiled: May 8, 2018Publication date: November 15, 2018Inventors: Guo Rong YAN, Mark Huzzard CUNNINGHAM
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Patent number: 10018150Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.Type: GrantFiled: April 25, 2016Date of Patent: July 10, 2018Assignee: PRATT & WHITNEY CANADA INC.Inventors: Remo Marini, Mark Huzzard Cunningham, Francois C. Bisson, Reza Mohammad Kameshki
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Publication number: 20180066604Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.Type: ApplicationFiled: August 9, 2017Publication date: March 8, 2018Inventors: Remo MARINI, Mark Huzzard CUNNINGHAM
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Patent number: 9759159Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.Type: GrantFiled: October 23, 2014Date of Patent: September 12, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Remo Marini, Mark Huzzard Cunningham
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Publication number: 20160326983Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.Type: ApplicationFiled: April 25, 2016Publication date: November 10, 2016Inventors: Remo MARINI, Mark Huzzard CUNNINGHAM, Francois C. BISSON, Reza Mohammad KAMESHKI
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Publication number: 20150337761Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.Type: ApplicationFiled: October 23, 2014Publication date: November 26, 2015Inventors: Remo MARINI, Mark Huzzard CUNNINGHAM
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Publication number: 20150075169Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and an annular shroud with the mixer attached to a downstream end of the shroud, the shroud and the mixer surrounding the hub to form an annular exhaust gas duct positioned radially therebetween, a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located within an axial length of the mixer between an upstream end and a downstream end of the mixer, the deswirling struts each having a cambered profile and extending radially across the annular exhaust gas duct and interconnecting the mixer and the hub.Type: ApplicationFiled: May 26, 2014Publication date: March 19, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Mark Huzzard CUNNINGHAM, Edward Parker VLASIC, Sami GIRGIS
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Publication number: 20140260283Abstract: An exhaust mixer for a gas turbine engine has a plurality of circumferentially distributed alternating inner and outer lobes, and a plurality of aerodynamic struts positioned and oriented between adjacent inner lobes in the core flow passage. The struts are configured for diverting a portion of the core flow radially outwardly in troughs formed by the outer lobes on the core flow side of the mixer.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: RICHARD BOUCHARD, MARK HUZZARD CUNNINGHAM
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Patent number: 8635875Abstract: A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes. The outer lobes protrude into the annular bypass passage of the engine, whereas the inner lobes protrude into the main gas path passage of the engine. The inner and outer lobes respectively define alternating troughs and crest with radial interconnecting walls therebetween. The mixer has a jagged trailing edge including a plurality of tabs extending from each radial wall between the troughs and the crests.Type: GrantFiled: April 29, 2010Date of Patent: January 28, 2014Assignee: Pratt & Whitney Canada Corp.Inventor: Mark Huzzard Cunningham
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Publication number: 20110265447Abstract: A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes. The outer lobes protrude into the annular bypass passage of the engine, whereas the inner lobes protrude into the main gas path passage of the engine. The inner and outer lobes respectively define alternating troughs and crest with radial interconnecting walls therebetween. The mixer has a jagged trailing edge including a plurality of tabs extending from each radial wall between the troughs and the crests.Type: ApplicationFiled: April 29, 2010Publication date: November 3, 2011Inventor: Mark Huzzard CUNNINGHAM