Patents by Inventor Randall R. West
Randall R. West 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: 11905913Abstract: An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.Type: GrantFiled: October 22, 2021Date of Patent: February 20, 2024Assignee: Spirit AeroSystems, Inc.Inventor: Randall R. West
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Patent number: 11679888Abstract: A composite aircraft engine pylon comprising a frame, an aircraft attachment component, and an engine support. The frame includes an outer structural section and an inner structural section configured to at least partially nest with the outer structural section. The outer structural section and the inner structural section sandwich the airframe attachment component and the engine support to form double shear connections between the frame and the aircraft attachment component and between the frame and the engine support.Type: GrantFiled: October 19, 2020Date of Patent: June 20, 2023Assignee: Spirit AeroSystems, Inc.Inventor: Randall R. West
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Publication number: 20230127457Abstract: An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.Type: ApplicationFiled: October 22, 2021Publication date: April 27, 2023Applicant: Spirit AeroSystems, Inc.Inventor: Randall R. West
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Publication number: 20220119122Abstract: A composite aircraft engine pylon comprising a frame, an aircraft attachment component, and an engine support. The frame includes an outer structural section and an inner structural section configured to at least partially nest with the outer structural section. The outer structural section and the inner structural section sandwich the airframe attachment component and the engine support to form double shear connections between the frame and the aircraft attachment component and between the frame and the engine support.Type: ApplicationFiled: October 19, 2020Publication date: April 21, 2022Applicant: SPIRIT AEROSYSTEMS, INC.Inventor: Randall R. West
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Patent number: 8561943Abstract: An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall.Type: GrantFiled: November 29, 2012Date of Patent: October 22, 2013Assignee: Spirit AeroSystems, Inc.Inventors: Gordon R. Crook, Randall R. West, George Larimore Huggins
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Patent number: 8353476Abstract: An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall.Type: GrantFiled: November 23, 2009Date of Patent: January 15, 2013Assignee: Spirit AeroSystems, Inc.Inventors: Gordon R. Crook, Randall R. West, George Larimore Huggins
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Patent number: 8316632Abstract: A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.Type: GrantFiled: February 25, 2009Date of Patent: November 27, 2012Assignee: Spirit AeroSystems, Inc.Inventors: Randall R. West, Henry A. Schaefer
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Publication number: 20110121132Abstract: An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall.Type: ApplicationFiled: November 23, 2009Publication date: May 26, 2011Applicant: Spirit AeroSystems, Inc.Inventors: Gordon R. Crook, Randall R. West, George Larimore Huggins
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Publication number: 20100212286Abstract: A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.Type: ApplicationFiled: February 25, 2009Publication date: August 26, 2010Applicant: Spirit AeroSystems, Inc.Inventors: Randall R. West, Henry A. Schaefer