Patents by Inventor Craig Douglas Young

Craig Douglas Young 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: 7094450
    Abstract: A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.
    Type: Grant
    Filed: April 30, 2003
    Date of Patent: August 22, 2006
    Assignee: General Electric Company
    Inventors: Bangalore Aswatha Nagaraj, Eva Zielonka Lanman, Deborah Anne Schorr, Thomas John Tomlinson, Raymond William Heidorn, David Allen Kastrup, Craig Douglas Young
  • Patent number: 6986253
    Abstract: A method facilitates the operation of a gas turbine engine that includes a combustor including a combustion chamber. The method comprises supplying fuel to the combustion chamber, and directing compressed airflow through a combustor dome assembly that includes a splashplate and a unitarily formed flare cone, such that at least a portion of the compressed airflow is channeled axially downstream through at least one cooling passage defined between the flare cone and the splashplate for cooling of the dome assembly.
    Type: Grant
    Filed: July 16, 2003
    Date of Patent: January 17, 2006
    Assignee: General Electric Company
    Inventors: Thomas A. Leen, Steve Steffens, Craig Douglas Young
  • Patent number: 6983599
    Abstract: A turbine engine combustor member, for example a deflector including an inner surface at a combustor interior and an outer surface away from such interior includes a body of a high temperature alloy having properties combining resistance to hot corrosion in March=1 flows and oxidation to avoid coating the outer surface. In one embodiment, the inner surface includes an environmental resistant coating comprising a ceramic-base thermal barrier coating. In some forms such coating includes an inner coating including Al under the ceramic-base coating. In another embodiment, the member includes air cooling passages and is substantially uncoated. Provision of such a member enables complete combustor assembly including a plurality of members and then coating all inner surfaces concurrently rather than individually before assembly.
    Type: Grant
    Filed: February 12, 2004
    Date of Patent: January 10, 2006
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Bangalore Aswatha Nagaraj, Dane Anthony Elliott-Lewis, Joshua Leigh Miller, Kevin Swayne O'Hara
  • Patent number: 6932093
    Abstract: A method facilitates washing a gas turbine engine combustor. The method comprises coupling a nozzle assembly against the combustor, wherein the nozzle assembly includes an inlet end, a discharge end, a hollow nozzle body extending therebetween, and a centerbody positioned within the nozzle body, coupling the nozzle assembly to a fluid source, and discharging an annulus of fluid from the nozzle assembly into the combustor to facilitate removing particulate matter from the combustor.
    Type: Grant
    Filed: February 24, 2003
    Date of Patent: August 23, 2005
    Assignee: General Electric Company
    Inventors: Paul James Ogden, Craig Douglas Young, Steven Clayton Vise
  • Publication number: 20040219290
    Abstract: A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.
    Type: Application
    Filed: April 30, 2003
    Publication date: November 4, 2004
    Inventors: Bangalore Aswatha Nagaraj, Eva Zielonka Lanman, Deborah Anne Schorr, Thomas John Tomlinson, Raymond William Heidorn, David Allen Kastrup, Craig Douglas Young
  • Publication number: 20040163678
    Abstract: A method facilitates washing a gas turbine engine combustor. The method comprises coupling a nozzle assembly against the combustor, wherein the nozzle assembly includes an inlet end, a discharge end, a hollow nozzle body extending therebetween, and a centerbody positioned within the nozzle body, coupling the nozzle assembly to a fluid source, and discharging an annulus of fluid from the nozzle assembly into the combustor to facilitate removing particulate matter from the combustor.
    Type: Application
    Filed: February 24, 2003
    Publication date: August 26, 2004
    Inventors: Paul James Ogden, Craig Douglas Young, Steven Clayton Vise
  • Publication number: 20040045301
    Abstract: A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein.
    Type: Application
    Filed: September 10, 2002
    Publication date: March 11, 2004
    Inventors: Gilbert Farmer, Steven Clayton Vise, Walter Byron Houchens, Craig Douglas Young
  • Patent number: 6655146
    Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.
    Type: Grant
    Filed: July 31, 2001
    Date of Patent: December 2, 2003
    Assignee: General Electric Company
    Inventors: Ella Christine Kutter, Marwan Al-Roub, Thomas Anthony Leen, Daniel Dale Brown, Craig Douglas Young, Gilbert Farmer, Mohammad Ehteshami
  • Patent number: 6581386
    Abstract: A combustor baffle includes an outer tube with external threads and a heat shield at opposite ends thereof. An inner tube is disposed inside the outer tube in a unitary assembly therewith. The outer tube is retained in a combustor dome by a retention nut, and the inner tube supports an air swirler with a brazed joint therewith. The brazed joint permits sacrifice of the baffle during disassembly for access to the threaded joint for final disassembly without damage to the dome or air swirler.
    Type: Grant
    Filed: September 29, 2001
    Date of Patent: June 24, 2003
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Paul James Ogden
  • Patent number: 6546732
    Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: April 15, 2003
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Paul Edward Sabla, Steven Clayton Vise
  • Patent number: 6543233
    Abstract: A combustor liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second annular panel section having a forward end, an aft end and a second cooling nugget located at the forward end thereof. The second panel section is joined at its forward end to the aft end of the first panel section. A first row of cooling holes is located in the first cooling nugget, and a second row of cooling holes is located in the second cooling nugget. A group of dilution holes is located in the first panel section. The dilution holes are located at the aft end of the first panel section, immediately upstream of the second cooling nugget. Furthermore, each one of the dilution holes defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes have different hole diameters.
    Type: Grant
    Filed: February 9, 2001
    Date of Patent: April 8, 2003
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Ella Christine Kutter
  • Publication number: 20030061815
    Abstract: A combustor baffle includes an outer tube with external threads and a heat shield at opposite ends thereof. An inner tube is disposed inside the outer tube in a unitary assembly therewith. The outer tube is retained in a combustor dome by a retention nut, and the inner tube supports an air swirler with a brazed joint therewith. The brazed joint permits sacrifice of the baffle during disassembly for access to the threaded joint for final disassembly without damage to the dome or air swirler.
    Type: Application
    Filed: September 29, 2001
    Publication date: April 3, 2003
    Inventors: Craig Douglas Young, Paul James Ogden
  • Patent number: 6530227
    Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: March 11, 2003
    Assignee: General Electric Co.
    Inventors: Craig Douglas Young, Paul Edward Sabla, Steven Clayton Vise
  • Publication number: 20030027093
    Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.
    Type: Application
    Filed: July 31, 2001
    Publication date: February 6, 2003
    Inventors: Ella Christine Kutter, Marwan Al-Roub, Thomas Anthony Leen, Daniel Dale Brown, Craig Douglas Young, Gilbert Farmer, Mohammad Ehteshami
  • Patent number: 6442940
    Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The combustor includes an air swirler, and the one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends circumferentially through the deflector portion for receiving cooling fluid therein. Because the deflector-flare cone assembly receives pre-loaded braze tape and braze rope, a single braze operation secures the deflector-flare cone assembly within the combustor and to a combustor air swirler.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: September 3, 2002
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Kenneth Edward Seitzer, Paul James Ogden
  • Publication number: 20020108374
    Abstract: A combustor liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second annular panel section having a forward end, an aft end and a second cooling nugget located at the forward end thereof. The second panel section is joined at its forward end to the aft end of the first panel section. A first row of cooling holes is located in the first cooling nugget, and a second row of cooling holes is located in the second cooling nugget. A group of dilution holes is located in the first panel section. The dilution holes are located at the aft end of the first panel section, immediately upstream of the second cooling nugget. Furthermore, each one of the dilution holes defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes have different hole diameters.
    Type: Application
    Filed: February 9, 2001
    Publication date: August 15, 2002
    Inventors: Craig Douglas Young, Ella Christine Kutter