Patents by Inventor Gert Johannes van der Merwe

Gert Johannes van der Merwe 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).

  • Publication number: 20190085714
    Abstract: A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.
    Type: Application
    Filed: September 20, 2017
    Publication date: March 21, 2019
    Inventors: Darek Tomasz Zatorski, Gert Johannes van der Merwe, Brandon Wayne Miller, Daniel Alan Niergarth
  • Publication number: 20190085710
    Abstract: The present disclosure is directed to a method of operating an active clearance control system for an interdigitated turbine engine. The method includes flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine. The present disclosure is further directed to a gas turbine engine including a low speed turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The engine further includes a turbine frame at least partially surrounding the low speed turbine rotor; a seal assembly disposed between the outer shroud of the low speed turbine rotor and the turbine frame; and a fifth manifold coupled to the turbine frame.
    Type: Application
    Filed: September 20, 2017
    Publication date: March 21, 2019
    Inventors: Gert Johannes van der Merwe, Darek Tomasz Zatorski
  • Publication number: 20180371997
    Abstract: A clearance control system includes one or more clearance control devices that include features for controlling the clearances between rotating and stationary components of an engine. In one exemplary aspect, a clearance control device utilizes a fluid to pressurize an actuation chamber defined by a compliant member of the clearance control device. The pressurization of the actuation chamber causes the actuation chamber to expand in a direction that changes the clearance between the stationary and rotating components of the engine.
    Type: Application
    Filed: June 27, 2017
    Publication date: December 27, 2018
    Inventors: Gert Johannes van der Merwe, Joel Francis Kirk
  • Publication number: 20180298784
    Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, and wherein the gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a turbine frame defined around the axial centerline, the turbine frame comprising a first bearing surface disposed inward along the radial direction. The gas turbine engine further includes a turbine rotor assembly including a bearing assembly coupled to the first bearing surface of the turbine frame and the turbine rotor assembly. The turbine rotor assembly further includes a first turbine rotor disposed upstream of the turbine frame and a second turbine rotor disposed downstream of the turbine frame.
    Type: Application
    Filed: April 12, 2017
    Publication date: October 18, 2018
    Inventors: Thomas Ory Moniz, Alan Roy Stuart, Jeffrey Donald Clements, Brandon Wayne Miller, Darek Tomasz Zatorski, Gert Johannes van der Merwe, Joel Francis Kirk, Richard Wesling
  • Publication number: 20180209274
    Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a first turbine rotor comprising an inner shroud, an outer shroud outward of the inner shroud in the radial direction, at least one connecting airfoil coupling the inner shroud and the outer shroud at least partially along the radial direction, and an outer band outward of the outer shroud in the radial direction and extended at least partially in the circumferential direction, and a plurality of connecting members couples the outer shroud and the outer band.
    Type: Application
    Filed: January 25, 2017
    Publication date: July 26, 2018
    Inventors: Darek Tomasz Zatorski, Brandon Wayne Miller, Richard Wesling, Gert Johannes van der Merwe
  • Publication number: 20180163845
    Abstract: A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.
    Type: Application
    Filed: December 12, 2016
    Publication date: June 14, 2018
    Inventors: Gert Johannes van der Merwe, Raymond Floyd Martell
  • Publication number: 20180087396
    Abstract: A gas turbine engine includes a compressor section and a turbine section. A first spool is rotatable with a first turbine of the turbine section and a first compressor of the compressor section. Additionally, a second spool is rotatable with a second turbine of the turbine section and a second compressor of the compressor section. An electric machine is positioned at least partially inward of the core air flowpath of the gas turbine engine along a radial direction of the gas turbine engine. Additionally, the exemplary gas turbine engine includes a gear assembly mechanically coupled to both the first spool and the second spool, such that the first and second spools may each drive the electric machine.
    Type: Application
    Filed: September 28, 2016
    Publication date: March 29, 2018
    Inventors: Gert Johannes van der Merwe, Daniel Alan Niergarth, Peter David Toot
  • Publication number: 20170191548
    Abstract: A planet gear includes an annular planet gear ring including an annular planet gear rim. The annular planet gear rim has an inner radius and an outer radius. The inner radius and the outer radius define a rim thickness therebetween. The annular planet gear rim further has a bending stress neutral axis. The bending stress neutral axis radius and the rim thickness define a ratio including values in a range from and including about 3 to and including about 10.
    Type: Application
    Filed: December 30, 2015
    Publication date: July 6, 2017
    Inventors: Kenneth Lee Fisher, Darren Lee Hallman, Bugra Han Ertas, Donald Albert Bradley, Haris Ligata, William Howard Hasting, Ning Fang, Gert Johannes van der Merwe, Mark Alan Rhoads
  • Publication number: 20170114887
    Abstract: A static lubricant supply system within a gearbox that delivers lubricant to rotating gears. The lubricant supply system includes a stationary sleeve assembly for delivering the lubricant to a rotating receiver member, shaft, or flange. The sleeve assembly includes bearings, seals, jets, and plenums. The jets are skewed to deliver lubricant in the tangential direction of rotational motion of the receiver member, shaft, or flange. In the radial gap transfer configuration, the sleeve assembly circumscribes the receiver member or shaft. A race in the receiver member or shaft receives the lubricant. Channels within the receiver member, shaft, and gears deliver lubricant to the gears. In the axial gap transfer configuration, the sleeve assembly transfers lubricant to a flange attached to a receiver member. The flange has a race that receives the lubricant from the jets. Channels within the flange, receiver member, and gears deliver lubricant to the gears.
    Type: Application
    Filed: October 23, 2015
    Publication date: April 27, 2017
    Inventors: Brandon Wayne Miller, Gert Johannes van der Merwe, Donald Albert Bradley, Michael Anthony Barnell, Christopher James Kroger
  • Publication number: 20160186657
    Abstract: A turbine engine assembly is provided. The assembly includes a low-pressure turbine configured to rotate at a first rotational speed, and a fan assembly coupled to the low-pressure turbine and configured to rotate at a second rotational speed lower than the first rotational speed. The fan assembly includes a fan blade fabricated from a composite material and having a configuration selected based on the second rotational speed of the fan assembly.
    Type: Application
    Filed: October 2, 2015
    Publication date: June 30, 2016
    Inventors: Gert Johannes VAN DER MERWE, Ian Francis PRENTICE
  • Publication number: 20160144970
    Abstract: A turbine engine assembly is provided. The assembly includes a stationary component, a drive shaft, and a gearbox coupled along the drive shaft, and coupled to the stationary component. The assembly also includes a vibration-reducing mechanism coupled between the stationary component and the gearbox. The vibration-reducing mechanism is configured to isolate a vibratory response of the gearbox from the stationary component.
    Type: Application
    Filed: November 17, 2015
    Publication date: May 26, 2016
    Inventors: Gert Johannes VAN DER MERWE, Charles Stanley ORKISZEWSKI
  • Patent number: 8818683
    Abstract: A method for operating a gas turbine engine includes coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a vibration level of a rotor assembly within the gas turbine engine, detecting the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor, comparing the detected vibration level to a predetermined vibration threshold, and generating an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.
    Type: Grant
    Filed: April 21, 2006
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: Gert Johannes van der Merwe, David Allen Bradford
  • Publication number: 20080127734
    Abstract: A vibration measurement system for a gas turbine engine. The vibration measurement system includes a first accelerometer coupled to the gas turbine engine, the first accelerometer configured to transmit a first identifier, a second accelerometer coupled to the gas turbine engine, the second accelerometer configured to transmit a second identifier that is different than the first identifier, and a signal conditioning computer coupled to the first and second accelerometers for receiving the first and second identifiers, the signal conditioning computer configured to determine which of the first and second accelerometers is connected to the signal conditioning computer based on the first and second identifiers.
    Type: Application
    Filed: November 30, 2006
    Publication date: June 5, 2008
    Inventors: Gert Johannes van der Merwe, Daniel Edward Mollmann