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公开(公告)号：US10451002B2
公开(公告)日：2019-10-22
申请号：US15004020
申请日：2016-01-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Danis Burton Smith , Mark Knowles , Robert Romano , Shawn Alstad , David Robinson
Abstract: 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.
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公开(公告)号：US20190112984A1
公开(公告)日：2019-04-18
申请号：US15786733
申请日：2017-10-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Tomasz Dobosz , Rocio Chavez Felix
CPC classification number: F02C7/32 , F01D25/162 , F05D2230/644 , F05D2240/50 , F05D2250/312 , F05D2250/313 , F05D2250/314 , F05D2260/4031 , F05D2260/532 , F16H1/222 , F16H55/20
Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The system includes a towershaft coupled to the driveshaft and rotatable about a towershaft axis of rotation. The towershaft includes a towershaft bevel gear. The system includes a primary shaft including a first bevel gear and a second bevel gear that each revolve about a primary shaft axis of rotation. The first bevel gear is coupled to the towershaft bevel gear. The system includes a secondary shaft including a third bevel gear and a fourth bevel gear that each revolve about a secondary shaft axis of rotation. The third bevel gear is coupled to the second bevel gear. The system includes a tertiary shaft including a fifth bevel gear that revolves about a tertiary shaft axis of rotation. The fifth bevel gear is coupled to the fourth bevel gear.
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公开(公告)号：US10221765B2
公开(公告)日：2019-03-05
申请号：US15248150
申请日：2016-08-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Morris Anderson , Danis Burton Smith , Laurence David Noble Liston
Abstract: 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.
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公开(公告)号：US20180058322A1
公开(公告)日：2018-03-01
申请号：US15248150
申请日：2016-08-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Morris Anderson , Danis Burton Smith , Laurence David Noble Liston
IPC: F02C7/047
CPC classification number: F02C7/047 , B64D15/04 , B64D2033/0233 , F02C7/045 , F05D2220/32 , F05D2250/52 , F05D2260/30 , F05D2260/31 , F05D2260/95 , Y02T50/672
Abstract: 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.
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公开(公告)号：US09879637B2
公开(公告)日：2018-01-30
申请号：US14560521
申请日：2014-12-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mark Knowles , Shawn Alstad , Justin C. Mickelsen , Raymond Gage , Bill Russell Watson
CPC classification number: F02K3/06 , F01D25/162 , F01D25/24 , F01D25/28 , F05D2230/60 , F05D2300/121 , F05D2300/603
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20170218848A1
公开(公告)日：2017-08-03
申请号：US15014097
申请日：2016-02-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Tomasz Dobosz , Rocio Chavez
Abstract: 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.
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公开(公告)号：US12024305B2
公开(公告)日：2024-07-02
申请号：US17452690
申请日：2021-10-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Andrew Appleby
CPC classification number: B64D27/40 , B64D27/10 , B64D29/06 , B64D27/404
Abstract: A pylon system for coupling an engine to a vehicle is provided. The pylon system includes a vehicle pylon to be coupled to the vehicle. The vehicle pylon includes a seal along a portion of the vehicle pylon. The pylon system includes an engine pylon including an inboard longeron and an outboard longeron. The inboard longeron is coupled to the outboard longeron at a first end of the engine pylon and is spaced apart from the outboard longeron at a second end of the engine pylon. The engine pylon is to be coupled to the engine, and the engine pylon is slidably coupled to the seal such that the engine pylon is movable relative to the vehicle pylon between at least a first position and a second position.
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公开(公告)号：US11846235B2
公开(公告)日：2023-12-19
申请号：US17443492
申请日：2021-07-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad
CPC classification number: F02C7/24 , F02K1/827 , G10K11/04 , G10K11/16 , F05D2260/96
Abstract: A sound attenuating cell includes a first sound attenuating cavity defined between a first sidewall and a second sidewall. The first sidewall is opposite the second sidewall. The first sidewall includes a first undulating surface and the second sidewall includes a second undulating surface. A deflector is coupled to the first undulating surface. The deflector extends from the first undulating surface toward the second undulating surface. The first undulating surface is axially offset from the second undulating surface to define a tortuous path between the first sidewall and the second sidewall. The first sound attenuating cavity has a first end and a second end. The first end is opposite the second end, and an inlet and an outlet of the first sound attenuating cavity is defined at the first end. The sound attenuating cell includes a second sound attenuating cavity nested within the first sound attenuating cavity.
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公开(公告)号：US11773807B1
公开(公告)日：2023-10-03
申请号：US17662684
申请日：2022-05-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Laurence Liston , Andrew Appleby , Jeffrey Aitchison
CPC classification number: F02K1/763 , F02K1/766 , F16H25/2204 , F16H25/2454 , F05D2220/323 , F05D2260/403 , F05D2270/66
Abstract: An actuator for a thrust reverser includes a ball screw, a ball nut coupled to the ball screw, and a gerotor coupled to the ball screw. The gerotor includes an inner rotor coupled to the ball screw and an outer rotor. The outer rotor includes a plurality of bores. The actuator includes a lock system coupled to the outer rotor. The lock system is to enable the gerotor to rotate the ball screw in an unlocked state and to inhibit a rotation of the ball screw in a lock state. The lock system includes a piston coupled to a piston housing and a grippable member coupled to the piston housing. The piston is received in one of the bores in the lock state, and the grippable member is to move the piston housing relative to the gerotor to move the lock system to the unlocked state.
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公开(公告)号：US11499503B1
公开(公告)日：2022-11-15
申请号：US17409156
申请日：2021-08-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shawn Alstad , Robert L. Hoover
IPC: F02K1/62
Abstract: A translating cowl thrust reverser system with efflux management includes a support structure, a transcowl, a cowl shield, and a single cascade structure. The transcowl and cowl shield are moveable together between a first position, in which the transcowl abuts the support structure, and a second position, in which an aperture is formed between the transcowl and the support structure. The cowl shield has cowl shield turning vanes. The single cascade structure is disposed within the aperture and includes a forward wall, a curved vane, internal turning vanes, and external turning vanes. In the first position, each cowl shield turning vane is disposed between a different pair of external turning vanes. The cowl shield turning vanes, the internal turning vanes, and the external turning vanes turn the airflow so that it is directed substantially perpendicular to, and vertically outboard relative to, a plane of symmetry.
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