Patents by Inventor Christopher Zollars

Christopher Zollars 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: 20200309036
    Abstract: A gas turbine engine includes a plural spool assembly including a first spool and a second spool. The engine also includes an accessory configured to change between a motor mode and a generator mode and a transmission configured to transmit mechanical power between the accessory and at least one of the first spool and the second spool. The transmission, when the accessory is in the generator mode, is configured to transmit mechanical power from the first spool to the accessory for generating electric power at the accessory. The transmission, when the accessory is in the motor mode, is configured to transmit mechanical power from the accessory to the second spool.
    Type: Application
    Filed: March 28, 2019
    Publication date: October 1, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: David K Jan, Christopher Zollars
  • Publication number: 20200248624
    Abstract: An engine system includes a gas generator section and a load compressor. The gas generator section includes a core compressor, a combustion assembly, and a turbine. The core compressor receives and compresses a first flow of air as first compressed air. The combustion assembly receives the first compressed air from the compressor, mixes the first compressed air with fuel, and combusts the first compressed air and fuel mixture to result in combustion gases. The turbine receives the combustion gases from the combustion assembly and extracts energy from the combustion gases. The load compressor is driven by the turbine, and it is further configured to receive and compress a second flow of air as second compressed air. At least a portion of the second compressed air is directed to the gas generator section as cooling air.
    Type: Application
    Filed: February 1, 2019
    Publication date: August 6, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Nicholas Hemans, Vanessa Dwinell, Christopher Zollars
  • Publication number: 20200166211
    Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
    Type: Application
    Filed: November 27, 2018
    Publication date: May 28, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Nagaraja S. Rudrapatna, Atul Verma, David Chou, Christopher Zollars
  • Patent number: 9382910
    Abstract: Auxiliary power units and methods and systems for activation and deactivation of a load compressor therein are provided. Auxiliary power unit includes the load compressor having an impeller, APU engine, coupling member, pre-spinning means, and APU controller. APU engine is adapted to be mechanically engaged to load compressor to drive load compressor to provide pneumatic power and to be disengaged when the need for pneumatic power ceases. Coupling member couples load compressor and APU engine and is configured to be controllably moved between an engaged position in which the APU engine is mechanically engaged with the load compressor, and a disengaged position, in which the APU engine is disengaged from the load compressor. APU controller is operably coupled to load compressor, APU engine, coupling member, and pre-spinning means and adapted to receive and be responsive to rotational speed signals for controlling movement of coupling member between engaged and disengaged positions.
    Type: Grant
    Filed: February 28, 2013
    Date of Patent: July 5, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David K. Jan, Christopher Zollars
  • Patent number: 9115586
    Abstract: An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.
    Type: Grant
    Filed: April 19, 2012
    Date of Patent: August 25, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David K. Jan, Christopher Zollars, Rajiv Rana, Tom Polakis, Ardeshir Riahi
  • Publication number: 20140241906
    Abstract: Auxiliary power units and methods and systems for activation and deactivation of a load compressor therein are provided. Auxiliary power unit includes the load compressor having an impeller, APU engine, coupling member, pre-spinning means, and APU controller. APU engine is adapted to be mechanically engaged to load compressor to drive load compressor to provide pneumatic power and to be disengaged when the need for pneumatic power ceases. Coupling member couples load compressor and APU engine and is configured to be controllably moved between an engaged position in which the APU engine is mechanically engaged with the load compressor, and a disengaged position, in which the APU engine is disengaged from the load compressor. APU controller is operably coupled to load compressor, APU engine, coupling member, and pre-spinning means and adapted to receive and be responsive to rotational speed signals for controlling movement of coupling member between engaged and disengaged positions.
    Type: Application
    Filed: February 28, 2013
    Publication date: August 28, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: David K. Jan, Christopher Zollars
  • Publication number: 20130280036
    Abstract: An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.
    Type: Application
    Filed: April 19, 2012
    Publication date: October 24, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: David K. Jan, Christopher Zollars, Rajiv Rana, Tom Polakis, Ardeshir Riahi
  • Patent number: 7832986
    Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.
    Type: Grant
    Filed: March 7, 2007
    Date of Patent: November 16, 2010
    Assignee: Honeywell International Inc.
    Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars
  • Publication number: 20080219853
    Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.
    Type: Application
    Filed: March 7, 2007
    Publication date: September 11, 2008
    Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars