Patents by Inventor Thomas Malkus
Thomas Malkus 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: 20240117768Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.Type: ApplicationFiled: October 3, 2022Publication date: April 11, 2024Inventors: Trevor Howard Wood, Ramakrishna Venkata Mallina, Giridhar Jothiprasad, Kishore Ramakrishnan, Thomas Malkus
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Publication number: 20240060510Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).Type: ApplicationFiled: August 15, 2023Publication date: February 22, 2024Inventors: Stephan Priebe, Giridhar Jothiprasad, Joseph Capozzi, Thomas Malkus, Michael Macrorie, Trevor H. Wood
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Publication number: 20240060429Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).Type: ApplicationFiled: August 17, 2022Publication date: February 22, 2024Inventors: Stephan Priebe, Giridhar Jothiprasad, Joseph Capozzi, Thomas Malkus, Michael Macrorie, Trevor H. Wood
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Publication number: 20230417155Abstract: Compact bleed valve assemblies are disclosed. An example turbine engine comprises a rotor blade having an axial chord (C) measured at a tip of the rotor blade, and a variable bleed valve (VBV) including a VBV port defining a bleed flowpath and an exit angle (?exit) for bleed air exiting the VBV port, the VBV port including a forward entrance edge and an aft exit edge and a first length (LA) therebetween, and a VBV door corresponding to the VBV port, the VBV door to generate a bleed cavity having a bleed cavity area (BA) in the VBV port when the VBV is in a closed position, the VBV door to move between an open position and the closed position at a rotation angle (??), the VBV door to extend a distance (LAact) beyond the first length (LA), wherein L ? A + L ? A a ? c ? t C - 2 * ( B ? V ? I ? P + 0 . 1 ? 5 ) - 1 . 3 ? 5 ? - 0.8 , and wherein B ? V ? I ? P = 0 . 1 ? 5 * B ? A C 2 + 0 . 8 ? 5 * ? ? ? + ? e ? x ? i ? t 2 ? ? .Type: ApplicationFiled: June 27, 2022Publication date: December 28, 2023Inventors: Thomas Malkus, Giridhar Jothiprasad, Christopher E. LaMaster, Jeffrey D. Carnes
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Patent number: 11840987Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.Type: GrantFiled: April 5, 2022Date of Patent: December 12, 2023Assignee: General Electric CompanyInventors: Trevor Howard Wood, Kishore Ramakrishnan, Justin John Gambone, Jr., Darren Lee Hallman, Thomas Malkus, Jixian Yao, Keith Edward James Blodgett
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Publication number: 20230358181Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: ApplicationFiled: July 17, 2023Publication date: November 9, 2023Inventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Publication number: 20230340927Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.Type: ApplicationFiled: April 12, 2023Publication date: October 26, 2023Inventors: Trevor Howard Wood, Thomas Malkus, Kishore Ramakrishnan
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Publication number: 20230323815Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.Type: ApplicationFiled: April 11, 2022Publication date: October 12, 2023Inventors: Gregory Alexander Natsui, Giridhar Jothiprasad, Lana Maria Osusky, Thomas Malkus
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Publication number: 20230313754Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.Type: ApplicationFiled: April 5, 2022Publication date: October 5, 2023Inventors: Trevor Howard Wood, Kishore Ramakrishnan, Justin John Gambone, JR., Darren Lee Hallman, Thomas Malkus, Jixian Yao, Keith Edward James Blodgett
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Patent number: 11739698Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: GrantFiled: March 1, 2022Date of Patent: August 29, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Publication number: 20230228219Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.Type: ApplicationFiled: January 18, 2022Publication date: July 20, 2023Inventors: Li Zheng, Nicholas J. Kray, Changjie Sun, Thomas Malkus, Giridhar Jothiprasad, Mitchell J. Headley
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Publication number: 20230228220Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: ApplicationFiled: March 1, 2022Publication date: July 20, 2023Inventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Publication number: 20230212989Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly includes a variable bleed valve (VBV) door corresponding to a bleed port, an intermediary device operatively coupled to the VBV door, and a first actuator operatively coupled to the intermediary device, the first actuator to move between a first position and a second position, the first actuator to cause the intermediary device to move between the first position and the second position to cause the VBV door to move between the first position and the second position.Type: ApplicationFiled: January 5, 2022Publication date: July 6, 2023Inventors: Thomas Malkus, Jeffrey D. Carnes, Giridhar Jothiprasad, Christopher E. LaMaster, Michael Macrorie, Trevor H. Wood, Steven M. Taylor, Mitchell J. Headley, Paul J. Trimby