Patents by Inventor Shawn Alstad
Shawn Alstad 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: 20190080679Abstract: An improved cell structure that enables design improvements to acoustic panels is provided. The provided cell structure for an acoustic panel is (i) capable of damping a wider range of audible frequencies, (ii) able to be easily combined and integrated into a variety of panel dimensions, and (iii) manufacturable using additive manufacturing techniques such as direct metal laser sintering (DMLS).Type: ApplicationFiled: September 12, 2017Publication date: March 14, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventor: Shawn Alstad
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Patent number: 10221765Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.Type: GrantFiled: August 26, 2016Date of Patent: March 5, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Morris Anderson, Danis Burton Smith, Laurence David Noble Liston
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Publication number: 20180372004Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft. A first accessory axis of rotation and a second accessory axis of rotation are substantially transverse to the shaft axis of rotation.Type: ApplicationFiled: August 7, 2018Publication date: December 27, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Tomasz Dobosz, Rocio Chavez
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Patent number: 9951695Abstract: Gas turbine engines including multi-axis accessory gearboxes of mechanical drive systems are provided. The gearbox comprises a housing, a drive shaft, bevel pinion and drive shaft bevel gears, and a side bevel gear set operable to directly at least one side accessory device. Housing is disposed about a towershaft operatively coupled to main engine shaft and operable to rotate about a first axis. Drive shaft is skewed to main shaft and operable to rotate about a second axis that intersects the first axis at a first angle. Bevel pinion gear is mounted on the towershaft. Drive shaft bevel gear is mounted on the drive shaft. Side bevel gear set comprises an input gear meshing with one or more side bevel gears each having a side bevel gear axis at a second angle to the first axis and independently positionable relative to input gear. Second angle is independent of other angles.Type: GrantFiled: April 29, 2014Date of Patent: April 24, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Tomasz Dobosz, Shawn Alstad
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Patent number: 9950799Abstract: An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.Type: GrantFiled: March 9, 2016Date of Patent: April 24, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Morris Anderson, Shawn Alstad
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Publication number: 20180058322Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.Type: ApplicationFiled: August 26, 2016Publication date: March 1, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Morris Anderson, Danis Burton Smith, Laurence David Noble Liston
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Publication number: 20180051653Abstract: An improved translating cowl (transcowl) assembly for a thrust reverser system for a turbine engine is provided. The transcowl assembly comprises an outer skin comprised of a first composite material and an inner skin comprised of a second composite material. The inner skin is configured to couple circumferentially within the outer skin, and creates a flow path for engine exhaust flow. The inner skin comprises a contoured depression configured to provide clearance for movement of a blocker door. A metallic bracket is disposed between the inner skin and outer skin.Type: ApplicationFiled: August 17, 2016Publication date: February 22, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Patrick S. Mulloy, Shawn Alstad
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Patent number: 9879637Abstract: A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.Type: GrantFiled: December 4, 2014Date of Patent: January 30, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Mark Knowles, Shawn Alstad, Justin C. Mickelsen, Raymond Gage, Bill Russell Watson
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Patent number: 9816396Abstract: A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load.Type: GrantFiled: October 16, 2014Date of Patent: November 14, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Justin C. Mickelsen, Laurence David Noble Liston, Mark Knowles, Shawn Alstad
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Publication number: 20170259926Abstract: An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.Type: ApplicationFiled: March 9, 2016Publication date: September 14, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Morris Anderson, Shawn Alstad
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Patent number: 9756915Abstract: Embodiments described herein provide cases for mobile electronic devices. The cases may include a body configured to be selectively secured to a mobile electronic device having at least one sensor proximate to an outer surface thereof and a cover slidably coupled to the body. The cover is slidable between a first position and a second position relative to the body such that when the cover is in the first position, the at least one sensor is blocked by the cover and when the cover is in the second position, the at least one sensor is not blocked by the cover.Type: GrantFiled: March 17, 2015Date of Patent: September 12, 2017Inventors: Quang Nguyen, Shawn Alstad
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Publication number: 20170218848Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft. A first accessory axis of rotation and a second accessory axis of rotation are substantially transverse to the shaft axis of rotation.Type: ApplicationFiled: February 3, 2016Publication date: August 3, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Tomasz Dobosz, Rocio Chavez
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Publication number: 20170211510Abstract: A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, and an anti-rotation structure. The transcowl is mounted on the support structure and has an inner surface. The transcowl is axially translatable, relative to the support structure, between first and second positions. The door is pivotally coupled to the turbine engine, and has a forward edge and an aft edge. The door is rotatable between stowed and deployed positions when the transcowl translates between the first and second positions, respectively. The anti-rotation structure extends from the transcowl and is disposed adjacent to the aft edge of the door when the transcowl is in the first position and the door is in the stowed position. The anti-rotation structure is configured such that door rotation out of the stowed position only occurs subsequent to or concurrently with translation of the transcowl out of the first position.Type: ApplicationFiled: January 22, 2016Publication date: July 27, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Mark Knowles, Robert Romano, Shawn Alstad, David Robinson
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Publication number: 20170211511Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.Type: ApplicationFiled: January 25, 2016Publication date: July 27, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Shawn Alstad, John Taylor Pearson, Morris Anderson
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Publication number: 20170204809Abstract: A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.Type: ApplicationFiled: January 14, 2016Publication date: July 20, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Mark Knowles, Shawn Alstad, Robert Romano, John Taylor Pearson, Morris Anderson, David Robinson
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Publication number: 20170074211Abstract: A system and method for reducing idle thrust in a translating cowl reverser system is provided. The provided system and method provide a partial deployment, or thrust reverser system intermediate position for a translating cowl thrust reverser system.Type: ApplicationFiled: September 10, 2015Publication date: March 16, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Shawn Alstad, Robert Romano, Mark Knowles, David Robinson
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Publication number: 20170074167Abstract: A precooler system having a symmetrical precooler core that is optimized to be integrally mounted to the turbofan engine, regardless of the turbofan engine size, is provided. The provided precooler system optimizes available space between a turbofan engine and the nacelle, and does not substantially increase weight and cost. The provided precooler system may be flexibly implemented as either a right handed precooler system or a left handed precooler system.Type: ApplicationFiled: September 10, 2015Publication date: March 16, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Robert Romano, Morris Anderson, Robert Hoover
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Publication number: 20160305370Abstract: A thrust reverser system capable of providing high efficiency within a tightly constrained nacelle is provided. The thrust reverser system provides a displaceable internal door pivotally mounted within a transcowl. The displaceable internal door is rotatable about a pivot axis that is positioned aft of a front edge of the transcowl when the transcowl is in a deployed position.Type: ApplicationFiled: April 16, 2015Publication date: October 20, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Mark Knowles, Robert Romano, Shawn Alstad, David Robinson, Israel Picazo
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Publication number: 20160160800Abstract: A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.Type: ApplicationFiled: December 4, 2014Publication date: June 9, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark Knowles, Shawn Alstad, Justin C. Mickelsen, Raymond Gage, Bill Russell Watson
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Publication number: 20160108757Abstract: A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load.Type: ApplicationFiled: October 16, 2014Publication date: April 21, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Justin C. Mickelsen, Laurence David Noble Liston, Mark Knowles, Shawn Alstad