Patents by Inventor David W. Foutch
David W. Foutch 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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Publication number: 20190257599Abstract: Thermal management systems incorporating shape memory alloy (SMA) actuators and related methods. A thermal management system includes a heat transfer region, a process fluid conduit, a thermal management fluid conduit, and an SMA actuator assembly. The SMA actuator assembly includes an SMA element coupled to an actuation element, which is configured to assume a position among a plurality of positions defined between a restrictive position and an open position. The position of the actuation element is based, at least in part, on a conformation of the SMA element. A method of passively regulating a temperature of a process fluid includes conveying a process fluid stream in heat exchange relation with an SMA element, transitioning the SMA element to assume a conformation, flowing each of the process fluid stream and a thermal management fluid stream through a heat transfer region, and modulating a flow rate of the thermal management fluid stream.Type: ApplicationFiled: February 21, 2018Publication date: August 22, 2019Inventors: David W. Foutch, Frederick Theodore Calkins
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Publication number: 20190093557Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.Type: ApplicationFiled: January 25, 2018Publication date: March 28, 2019Applicant: The Boeing CompanyInventors: Holly J. Thomas, Brian L. Riedel, Alexandre D. Curaudeau, David W. Foutch, Steve G. Mackin
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Patent number: 10100744Abstract: Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.Type: GrantFiled: June 19, 2015Date of Patent: October 16, 2018Assignee: The Boeing CompanyInventors: Steve G. Mackin, David W. Foutch, Eric G. Landre
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Patent number: 10054051Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet and a compressor outlet. The compressor is to be driven by a drive shaft extending from an engine of an aircraft. The example apparatus also includes a first passageway to fluidly couple a first low-pressure bleed air port from the engine to the compressor inlet and a second passageway to fluidly couple the compressor outlet to a system of the aircraft.Type: GrantFiled: April 1, 2014Date of Patent: August 21, 2018Assignee: The Boeing CompanyInventors: David W. Foutch, Steve G. Mackin, Michael D. Bowman
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Patent number: 10041443Abstract: A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.Type: GrantFiled: June 9, 2015Date of Patent: August 7, 2018Assignee: The Boeing CompanyInventor: David W. Foutch
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Publication number: 20180056554Abstract: A compression molding assembly for molding a honeycomb core, including a plurality of cells defined by a plurality of walls, of a blocker door is provided. The compression molding assembly includes a ram plate comprising a plurality of openings defined therethrough and a plurality of core inserts coupled to the ram plate such that the plurality of core inserts are configured to form the honeycomb core of the blocker door. Each core insert is removably coupled with a respective opening of the plurality of openings such that each core insert is configured to form a respective cell of the plurality of cells.Type: ApplicationFiled: August 29, 2016Publication date: March 1, 2018Inventors: Kevin O'Brien Gaw, Michael A. Nill, Gary Anthony Booker, Stephen Dark, Laura Fournier, Randy J. Grove, David John Barene, Jeston Lingelbach, Kory Shaffer, David W. Foutch, Michael H. Larson
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Publication number: 20180058333Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.Type: ApplicationFiled: October 18, 2017Publication date: March 1, 2018Inventors: David W. Foutch, Steve G. Mackin
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Publication number: 20180058373Abstract: A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.Type: ApplicationFiled: August 29, 2016Publication date: March 1, 2018Inventors: Kevin O'Brien Gaw, Dylan E. Jones, Michael H. Larson, Belur N. Shivashankara, Randy J. Grove, David John Barene, Jeston Lingelbach, Kory Shaffer, David W. Foutch
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Patent number: 9810158Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.Type: GrantFiled: April 1, 2014Date of Patent: November 7, 2017Assignee: THE BOEING COMPANYInventors: David W. Foutch, Steve G. Mackin
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Patent number: 9803586Abstract: A control system for a variable area fan nozzle (VAFN) is disclosed. The VAFN may have a plurality of petals and may be for use with a gas turbine engine. The control system may include a primary system configured to acquire primary data indicative of an operating condition of the VAFN, a secondary system configured to acquire secondary data indicative of a current operating condition of the gas turbine engine, and a control module in operative communication with the primary system and the secondary system. The control module may be configured to: determine a nozzle area of the VAFN based at least in part on the primary data, adjust the determined nozzle area based on the secondary data, and position the plurality of petals according to the adjusted nozzle area.Type: GrantFiled: May 31, 2016Date of Patent: October 31, 2017Assignee: The Boeing CompanyInventors: Jason J. Jackowski, Kent E. Karnofski, David W. Foutch
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Publication number: 20160369705Abstract: Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.Type: ApplicationFiled: June 19, 2015Publication date: December 22, 2016Inventors: Steve G. Mackin, David W. Foutch, Eric G. Landre
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Publication number: 20160363097Abstract: A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.Type: ApplicationFiled: June 9, 2015Publication date: December 15, 2016Applicant: THE BOEING COMPANYInventor: David W. Foutch
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Patent number: 9206912Abstract: A fan air modulating valve (FAMV) employs a pair of doors rotatably attached at the fan bypass air exit of a precooler. An actuator engages the doors for simultaneous rotation through a range of motion from a first closed position to a second open position, wherein trailing edges of said doors sealingly engage an exit plenum extending from the precooler in the first closed position and fan bypass air flow is modulated by positioning the doors within the range of motion between the first and second positions.Type: GrantFiled: January 23, 2013Date of Patent: December 8, 2015Assignee: The Boeing CompanyInventors: Eric G. Landre, David W. Foutch
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Publication number: 20150275758Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet and a compressor outlet. The compressor is to be driven by a drive shaft extending from an engine of an aircraft. The example apparatus also includes a first passageway to fluidly couple a first low-pressure bleed air port from the engine to the compressor inlet and a second passageway to fluidly couple the compressor outlet to a system of the aircraft.Type: ApplicationFiled: April 1, 2014Publication date: October 1, 2015Applicant: The Boeing CompanyInventors: David W. Foutch, Steve G. Mackin, Michael D. Bowman
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Publication number: 20150275769Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.Type: ApplicationFiled: April 1, 2014Publication date: October 1, 2015Inventors: David W. Foutch, Steve G. Mackin
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Patent number: 8955794Abstract: Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high-pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.Type: GrantFiled: July 25, 2013Date of Patent: February 17, 2015Assignee: The Boeing CompanyInventors: Steve G. Mackin, David W. Foutch
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Publication number: 20140250898Abstract: Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high-pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.Type: ApplicationFiled: July 25, 2013Publication date: September 11, 2014Inventors: Steve G. Mackin, David W. Foutch
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Patent number: 8329312Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: GrantFiled: June 27, 2011Date of Patent: December 11, 2012Assignee: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Publication number: 20110256343Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: ApplicationFiled: June 27, 2011Publication date: October 20, 2011Applicant: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Patent number: 7967240Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: GrantFiled: March 16, 2007Date of Patent: June 28, 2011Assignee: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker