Patents by Inventor Jeffrey Richard Verhiel

Jeffrey Richard Verhiel 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: 20210025333
    Abstract: A fuel delivery system for an aircraft engine includes a first fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a first set of fuel nozzles, a first fuel conduit fluidly connected to the first fuel manifold at a first point, the first fuel conduit being fluidly connectable to a fuel source, a second fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a second set of fuel nozzles, a second fuel conduit fluidly connected to the second fuel manifold at a second point, the second fuel conduit being fluidly connectable to the fuel source, and a cross-flow fuel conduit fluidly connecting the first fuel manifold to the second fuel manifold. A method of operating an aircraft engine is also described.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Publication number: 20210025332
    Abstract: A fuel delivery system for an aircraft engine includes a first fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a first set of fuel nozzles, a second fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a second set of fuel nozzles, and a valve in a fuel nozzle of the second set of fuel nozzles, the valve operable to block fuel flow from the second fuel manifold to the fuel nozzle when the aircraft engine is operated in a standby mode. An aircraft gas turbine engine and a method of operating an aircraft engine are also disclosed.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Kian MCCALDON, Jeffrey Richard VERHIEL
  • Publication number: 20210025337
    Abstract: A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Publication number: 20200362760
    Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and discharging pressurized air from an accumulator into the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
    Type: Application
    Filed: May 11, 2020
    Publication date: November 19, 2020
    Inventors: Oleg MORENKO, Stephen TARLING, Ian BROCCOLINI, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Patent number: 9134028
    Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.
    Type: Grant
    Filed: January 18, 2012
    Date of Patent: September 15, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Jeffrey Richard Verhiel, Parthasarathy Sampath
  • Publication number: 20130180257
    Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.
    Type: Application
    Filed: January 18, 2012
    Publication date: July 18, 2013
    Inventors: Honza Stastny, Jeffrey Richard Verhiel, Parthasarathy Sampath
  • Patent number: 7726131
    Abstract: A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At least one dilution hole is in the floatwall panel near the trailing edge and in communication with the outer surface of the outer shell, and at least one local air impingement hole is in the outer shell downstream of each at least one dilution hole, that directs the cooling air towards the trailing edge of the floatwall panel.
    Type: Grant
    Filed: December 19, 2006
    Date of Patent: June 1, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Robert Sze, Jeffrey Richard Verhiel
  • Patent number: 7631503
    Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.
    Type: Grant
    Filed: September 12, 2006
    Date of Patent: December 15, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Honza Stastny, Jeffrey Richard Verhiel
  • Patent number: 7559203
    Abstract: The support boss is used in a combustor of a gas turbine engine. It comprises a side wall defining an internal space. The side wall has at least one air inlet orifice. It also comprises a bottom wall closing one end of the internal space. The bottom wall has at least one air outlet orifice.
    Type: Grant
    Filed: September 16, 2005
    Date of Patent: July 14, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Honza Stastny, Jeffrey Richard Verhiel
  • Publication number: 20080264064
    Abstract: A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At least one dilution hole is in the floatwall panel near the trailing edge and in communication with the outer surface of the outer shell, and at least one local air impingement hole is in the outer shell downstream of each at least one dilution hole, that directs the cooling air towards the trailing edge of the floatwall panel.
    Type: Application
    Filed: December 19, 2006
    Publication date: October 30, 2008
    Inventors: Robert Sze, Jeffrey Richard Verhiel
  • Publication number: 20080060360
    Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.
    Type: Application
    Filed: September 12, 2006
    Publication date: March 13, 2008
    Inventors: Honza Stastny, Jeffrey Richard Verhiel