Patents by Inventor Jonathan D. Little
Jonathan D. Little 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).
-
Patent number: 11428234Abstract: A bleed system of a gas turbine engine includes a bleed duct having a duct inlet located at a flowpath of a gas turbine engine, and a bleed outlet located outside of the flowpath, and extending circumferentially around a central longitudinal axis. A plurality of bleed doors are located at the bleed outlet and are arrayed along a circumferential length on the bleed duct. Each bleed door includes a first circumferential end, and a second circumferential end. The bleed doors are arrayed such that when the bleed doors are in a closed position the first circumferential end is located at the second circumferential end of an adjacent bleed door of the bleed doors. Each bleed door includes a pivot, such that each bleed door rotates about the pivot from the closed position covering the duct outlet to an opened position allowing a bleed airflow to pass through the duct outlet.Type: GrantFiled: May 8, 2020Date of Patent: August 30, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Jonathan D. Little
-
Patent number: 11421540Abstract: A vane arm connection system for a gas turbine engine, includes a vane stem having a flatted head; a vane arm having a claw engaging the flatted head; and a load spreader having a spreader body defining structure engaging the flatted head, and at least one extension extending laterally from the spreader body.Type: GrantFiled: November 11, 2019Date of Patent: August 23, 2022Assignee: Raytheon Technologies CorporationInventor: Jonathan D. Little
-
Patent number: 11391174Abstract: A variable vane actuation system for a gas turbine engine includes a stem section, along an axis, the stem section includes a groove; a vane arm comprising a claw section received at least partially into the groove; a clip mounted to the claw section; and a fastener fastened to the stem section along the axis to retain the clip and the vane arm to the stem section.Type: GrantFiled: September 17, 2019Date of Patent: July 19, 2022Assignee: Raytheon Technologies CorporationInventor: Jonathan D. Little
-
Patent number: 11346240Abstract: A damping link assembly for a bleed valve of a gas turbine engine. The damping link assembly having: a bleed valve ring having a link aperture; a mechanical fastener disposed in the link aperture; and a damping guide link operatively coupled to the mechanical fastener at one end for rotation about a first axis of the mechanical fastener and the damping guide link being operatively coupled to an idler bracket at an opposite end for rotation about a second axis, the damping guide link being capable of twisting about a third axis different from the first axis and the second axis when the bleed valve ring is rotated from a first position to a second position.Type: GrantFiled: June 7, 2019Date of Patent: May 31, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Jonathan D. Little
-
Publication number: 20210348618Abstract: A bleed system of a gas turbine engine includes a bleed duct having a duct inlet located at a flowpath of a gas turbine engine, and a bleed outlet located outside of the flowpath, and extending circumferentially around a central longitudinal axis. A plurality of bleed doors are located at the bleed outlet and are arrayed along a circumferential length on the bleed duct. Each bleed door includes a first circumferential end, and a second circumferential end. The bleed doors are arrayed such that when the bleed doors are in a closed position the first circumferential end is located at the second circumferential end of an adjacent bleed door of the bleed doors. Each bleed door includes a pivot, such that each bleed door rotates about the pivot from the closed position covering the duct outlet to an opened position allowing a bleed airflow to pass through the duct outlet.Type: ApplicationFiled: May 8, 2020Publication date: November 11, 2021Inventor: Jonathan D. Little
-
Patent number: 11008886Abstract: A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.Type: GrantFiled: June 3, 2019Date of Patent: May 18, 2021Assignee: Raytheon Technologies CorporationInventors: Herbert L. Walker, Jonathan D. Little, Manjunath Subramanya, Mark Boyer, Bernard W. Pudvah
-
Publication number: 20210140331Abstract: A vane arm connection system for a gas turbine engine, includes a vane stem having a flatted head; a vane arm having a claw engaging the flatted head; and a load spreader having a spreader body defining structure engaging the flatted head, and at least one extension extending laterally from the spreader body.Type: ApplicationFiled: November 11, 2019Publication date: May 13, 2021Applicant: United Technologies CorporationInventor: Jonathan D. Little
-
Publication number: 20210079806Abstract: A variable vane actuation system for a gas turbine engine includes a stem section, along an axis, the stem section includes a groove; a vane arm comprising a claw section received at least partially into the groove; a clip mounted to the claw section; and a fastener fastened to the stem section along the axis to retain the clip and the vane arm to the stem section.Type: ApplicationFiled: September 17, 2019Publication date: March 18, 2021Applicant: United Technologies CorporationInventor: Jonathan D. Little
-
Publication number: 20200386115Abstract: A damping link assembly for a bleed valve of a gas turbine engine. The damping link assembly having: a bleed valve ring having a link aperture; a mechanical fastener disposed in the link aperture; and a damping guide link operatively coupled to the mechanical fastener at one end for rotation about a first axis of the mechanical fastener and the damping guide link being operatively coupled to an idler bracket at an opposite end for rotation about a second axis, the damping guide link being capable of twisting about a third axis different from the first axis and the second axis when the bleed valve ring is rotated from a first position to a second position.Type: ApplicationFiled: June 7, 2019Publication date: December 10, 2020Inventor: Jonathan D. Little
-
Patent number: 10830155Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system comprising: a vane arm having a radially inward facing surface, a radially outward surface opposite the radially inward facing surface, a wedge projecting away from the radially inward facing surface, an aperture extending from the radially outward surface to the radially inward surface, and an interlocking feature located in the aperture and circumferentially opposite the wedge relative to the aperture; and a vane stem having a first end, a second end opposite the first end, a seat surface interposed between the first end and the second end, a primary portion extending from the first end to the seat surface, a secondary portion extending from the seat surface to the second end, and a stem notch configured to interlock with the interlocking feature of the vane arm.Type: GrantFiled: February 8, 2018Date of Patent: November 10, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Jonathan D. Little
-
Publication number: 20200158025Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system comprising: a vane arm having a radially inward facing surface, a radially outward surface opposite the radially inward facing surface, a wedge projecting away from the radially inward facing surface, an aperture extending from the radially outward surface to the radially inward surface, and an interlocking feature located in the aperture and circumferentially opposite the wedge relative to the aperture; and a vane stem having a first end, a second end opposite the first end, a seat surface interposed between the first end and the second end, a primary portion extending from the first end to the seat surface, a secondary portion extending from the seat surface to the second end, and a stem notch configured to interlock with the interlocking feature of the vane arm.Type: ApplicationFiled: February 8, 2018Publication date: May 21, 2020Inventor: Jonathan D. Little
-
Publication number: 20190316483Abstract: A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.Type: ApplicationFiled: June 3, 2019Publication date: October 17, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Herbert L. Walker, Jonathan D. Little, Manjunath Subramanya, Mark Boyer, Bernard W. Pudvah
-
Patent number: 10352186Abstract: A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.Type: GrantFiled: January 22, 2016Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Herbert L. Walker, Jonathan D. Little, Manjunath Subramanya, Mark Boyer, Bernard W. Pudvah
-
Patent number: 10260643Abstract: A bleed valve includes a valve body which includes an aperture. A resonator is in fluid communication with the aperture in the valve body. A drain valve is in fluid communication with the resonator.Type: GrantFiled: November 18, 2015Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Jonathan D. Little
-
Patent number: 9879611Abstract: Bleed valve assemblies in a gas turbine engine are disclosed herein. A bleed valve assembly in a low pressure compressor may include a bleed valve and a resonator chamber. A manifold may allow passage of air from a bleed duct into the resonator chamber. The resonator chamber may alter resonation properties of the bleed duct in order to prevent damage to components in the low pressure compressor.Type: GrantFiled: June 29, 2015Date of Patent: January 30, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, David A. Topol, Mark Boyer, Brian Desfosses, W. Marshall Quin, John Holchin, Jonathan D. Little, Bryan Roseberry
-
Publication number: 20170211410Abstract: A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.Type: ApplicationFiled: January 22, 2016Publication date: July 27, 2017Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Herbert L. Walker, Jonathan D. Little, Manjunath Subramanya, Mark Boyer, Bernard W. Pudvah
-
Patent number: 9677421Abstract: An assembly for a gas turbine engine includes a rotor formed by a drum and a hub. The drum has a generally conically shaped inner surface that defines a flow path along a first cavity. The hub is connected to the drum and has a conically shaped inner surface that defines a flow path along a second cavity.Type: GrantFiled: October 24, 2012Date of Patent: June 13, 2017Assignee: United Technologies CorporationInventors: Jonathan D. Little, Herbert L. Walker, Arun Jayasingh
-
Patent number: 9540939Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.Type: GrantFiled: December 26, 2013Date of Patent: January 10, 2017Assignee: United Technologies CorporationInventors: David Maliniak, Daniel J. Monahan, Jonathan D. Little, Veerachari J. Mayachari, Rakesh Sharma N. Dumavath, Arun Kumar Jayasingh, Herbert L. Walker
-
Publication number: 20160195015Abstract: A single piece nosecone with support ring and fastening method providing smooth aerodynamic flow into a gas turbine engine is disclosed. The support ring may include a rim having a curved upper surface, the curvature following a curve of the nosecone and having a hole extending radially therethrough to connect to the nosecone. The support ring may also include a flange having a first portion with a wall resting on top of a platform of the nosecone, the first portion having a hole aligned with the hole in the rim to connect to the nosecone and a second portion extending substantially radially from the first portion and having a hole extending therethrough, the second portion being employed to connect to the gas turbine engine.Type: ApplicationFiled: December 20, 2013Publication date: July 7, 2016Applicant: United Technologies CorporationInventor: Jonathan D. Little
-
Publication number: 20160153311Abstract: A bleed valve includes a valve body which includes an aperture. A resonator is in fluid communication with the aperture in the valve body. A drain valve is in fluid communication with the resonator.Type: ApplicationFiled: November 18, 2015Publication date: June 2, 2016Inventor: Jonathan D. Little