Patents by Inventor Sara Christine Crawford
Sara Christine Crawford 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: 20200141355Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.Type: ApplicationFiled: February 9, 2018Publication date: May 7, 2020Applicant: Rohr, Inc.Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
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Patent number: 10619597Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.Type: GrantFiled: February 9, 2018Date of Patent: April 14, 2020Assignee: ROHR, INC.Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
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Patent number: 10605198Abstract: A thrust reverser of a nacelle is orientated at least in-part about a fan case of a turbofan engine. The thrust reverser includes an outer fixed structure assembly and a radial spacer. The outer fixed structure assembly circumferentially extends about a centerline and is spaced, at least in part, radially outward from the fan case. The radial spacer is engaged to the outer fixed structure assembly and is in sliding contact with the fan case.Type: GrantFiled: April 15, 2016Date of Patent: March 31, 2020Assignee: ROHR, INC.Inventor: Sara Christine Crawford
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Patent number: 10514004Abstract: A cascade assembly of a nacelle for a turbofan engine includes a one-piece cascade fixed to a translating sleeve constructed and arranged to move between forward and aft positions along a centerline. A hook device of the cascade assembly includes a first catch fixed to a stationary structure and a second catch fixed to the one-piece cascade. The first catch is adapted to mate with the second catch for translating load when the cascade assembly is in a deployed state and the translating sleeve is in the aft position.Type: GrantFiled: December 14, 2015Date of Patent: December 24, 2019Assignee: ROHR, INC.Inventor: Sara Christine Crawford
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Patent number: 10428764Abstract: A cascade assembly of a nacelle for a turbofan engine includes a cascade concentrically disposed about an centerline, and a translating sleeve constructed and arranged to move between a forward position and an aft position along the centerline. A deflection limiter of the cascade assembly includes a first surface facing at least in-part in a radial direction and a second surface facing at least in-part in an opposite radial direction. The first surface is carried by one of the cascade and the translating sleeve and the second surface is carried by the other of the cascade and the translating sleeve. The first and second surfaces oppose one-another for limiting deflection when the translating sleeve is in the aft position and are spaced axially apart when the translating sleeve is in the forward position.Type: GrantFiled: February 10, 2016Date of Patent: October 1, 2019Assignee: ROHR, INC.Inventor: Sara Christine Crawford
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Patent number: 10160552Abstract: A nacelle for a turbofan engine includes a fan case, an inner barrel and a nose lip generally concentrically disposed about an axis. The inner barrel projects forward from and is engaged to the fan case at a first split line. The nose lip is engaged to the inner barrel at a second split line, and extends substantially radially outward directly from the second split line, then substantially axially rearward to the fan cowl as one unitary piece.Type: GrantFiled: February 12, 2016Date of Patent: December 25, 2018Assignee: ROHR, INC.Inventor: Sara Christine Crawford
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Patent number: 9926884Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.Type: GrantFiled: February 19, 2015Date of Patent: March 27, 2018Assignee: Rohr, Inc.Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
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Publication number: 20170298869Abstract: A thrust reverser of a nacelle is orientated at least in-part about a fan case of a turbofan engine. The thrust reverser includes an outer fixed structure assembly and a radial spacer. The outer fixed structure assembly circumferentially extends about a centerline and is spaced, at least in part, radially outward from the fan case. The radial spacer is engaged to the outer fixed structure assembly and is in sliding contact with the fan case.Type: ApplicationFiled: April 15, 2016Publication date: October 19, 2017Inventor: Sara Christine Crawford
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Publication number: 20170233090Abstract: A nacelle for a turbofan engine includes a fan case, an inner barrel and a nose lip generally concentrically disposed about an axis. The inner barrel projects forward from and is engaged to the fan case at a first split line. The nose lip is engaged to the inner barrel at a second split line, and extends substantially radially outward directly from the second split line, then substantially axially rearward to the fan cowl as one unitary piece.Type: ApplicationFiled: February 12, 2016Publication date: August 17, 2017Inventor: Sara Christine Crawford
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Publication number: 20170226962Abstract: A cascade assembly of a nacelle for a turbofan engine includes a cascade concentrically disposed about an centerline, and a translating sleeve constructed and arranged to move between a forward position and an aft position along the centerline. A deflection limiter of the cascade assembly includes a first surface facing at least in-part in a radial direction and a second surface facing at least in-part in an opposite radial direction. The first surface is carried by one of the cascade and the translating sleeve and the second surface is carried by the other of the cascade and the translating sleeve. The first and second surfaces oppose one-another for limiting deflection when the translating sleeve is in the aft position and are spaced axially apart when the translating sleeve is in the forward position.Type: ApplicationFiled: February 10, 2016Publication date: August 10, 2017Inventor: Sara Christine Crawford
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Publication number: 20170167439Abstract: A cascade assembly of a nacelle for a turbofan engine includes a one-piece cascade fixed to a translating sleeve constructed and arranged to move between forward and aft positions along a centerline. A hook device of the cascade assembly includes a first catch fixed to a stationary structure and a second catch fixed to the one-piece cascade. The first catch is adapted to mate with the second catch for translating load when the cascade assembly is in a deployed state and the translating sleeve is in the aft position.Type: ApplicationFiled: December 14, 2015Publication date: June 15, 2017Inventor: Sara Christine Crawford
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Publication number: 20160245227Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.Type: ApplicationFiled: February 19, 2015Publication date: August 25, 2016Applicant: ROHR, INC.Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
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Patent number: 9086034Abstract: An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes, including an aft-most vane, and rails defining a series of cells or air passages therebetween. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. A flow deflection shelf is mounted to each of the cascade segments and includes a deflector portion that at least partially extends forward of a group of cells of the cascade segments along which the flow deflection shelf is mounted. The deflector portion is configured to at least partially redirect at least a portion of a volume of air forwardly as the air outwardly passes through the group of cells of the cascade segments.Type: GrantFiled: December 1, 2011Date of Patent: July 21, 2015Assignee: Rohr, Inc.Inventors: Michael Ray Aten, Sara Christine Crawford
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Publication number: 20130092755Abstract: An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes, including an aft-most vane, and rails defining a series of cells or air passages therebetween. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. A flow deflection shelf is mounted to each of the cascade segments and includes a deflector portion that at least partially extends forward of a group of cells of the cascade segments along which the flow deflection shelf is mounted. The deflector portion is configured to at least partially redirect at least a portion of a volume of air forwardly as the air outwardly passes through the group of cells of the cascade segments.Type: ApplicationFiled: December 1, 2011Publication date: April 18, 2013Inventors: Michael Ray Aten, Sara Christine Crawford
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Patent number: 8109466Abstract: An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments.Type: GrantFiled: June 23, 2008Date of Patent: February 7, 2012Assignee: Rohr, Inc.Inventors: Michael Ray Aten, Sara Christine Crawford
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Publication number: 20090314887Abstract: An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments.Type: ApplicationFiled: June 23, 2008Publication date: December 24, 2009Applicant: Rohr, Inc.Inventors: Michael Ray Aten, Sara Christine Crawford