Patents by Inventor John Frederick Lockyer
John Frederick Lockyer 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: 9631512Abstract: A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.Type: GrantFiled: January 31, 2013Date of Patent: April 25, 2017Assignee: Solar Turbines IncorporatedInventor: John Frederick Lockyer
-
Patent number: 9341194Abstract: An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).Type: GrantFiled: November 1, 2012Date of Patent: May 17, 2016Assignee: Solar Turbines IncorporatedInventor: John Frederick Lockyer
-
Patent number: 9296038Abstract: A liquid fuel injection spoke for a gas turbine engine. The liquid fuel injection spoke may include an inlet end and an outlet end. The liquid fuel injection spoke may further include a head located at the inlet end and a stem extending along a longitudinal axis from the head to the outlet end. The stem may define a fluid passageway therein. The head may include a cavity with an inner wall. The inner wall may include an annular protrusion.Type: GrantFiled: July 27, 2012Date of Patent: March 29, 2016Assignee: Solar Turbines IncorporatedInventors: Alexander Ilich Krichever, Mario Eugene Abreu, Norm Turoff, John Frederick Lockyer, Christopher Zdzislaw Twardochleb, David Marc Stansel
-
Patent number: 9151227Abstract: A fuel injector for a gas turbine engine may include an injector housing extending along a longitudinal axis and configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a flow path for a fuel air mixture to the combustor extending longitudinally within the injector housing, and a gallery for liquid fuel encircling the flow path. The gallery may include a plurality of fuel spokes that are configured to deliver liquid fuel from the gallery to the flow path. The gallery may extend from a feed end to a terminal end that overlaps the feed end. The feed end may be a region where liquid fuel enters the gallery and the terminal end may be a region where the gallery terminates.Type: GrantFiled: November 10, 2010Date of Patent: October 6, 2015Assignee: Solar Turbines IncorporatedInventors: John Frederick Lockyer, Christopher Zdzislaw Twardochleb, Mario Eugene Abreu
-
Publication number: 20140209124Abstract: A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.Type: ApplicationFiled: January 31, 2013Publication date: July 31, 2014Applicant: SOLAR TURBINES INCORPORATEDInventor: John Frederick Lockyer
-
Publication number: 20140209123Abstract: A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.Type: ApplicationFiled: January 31, 2013Publication date: July 31, 2014Applicant: Solar Turbines IncorporatedInventor: John Frederick Lockyer
-
Publication number: 20140208762Abstract: A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.Type: ApplicationFiled: January 31, 2013Publication date: July 31, 2014Applicant: Solar Turbines IncorporatedInventor: John Frederick Lockyer
-
Patent number: 8778091Abstract: A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.Type: GrantFiled: January 31, 2013Date of Patent: July 15, 2014Assignee: Solar Turbines Inc.Inventor: John Frederick Lockyer
-
Publication number: 20140119895Abstract: An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).Type: ApplicationFiled: November 1, 2012Publication date: May 1, 2014Applicant: SOLAR TURBINES INCORPORATEDInventor: John Frederick Lockyer
-
Publication number: 20130168472Abstract: A liquid fuel injection spoke for a gas turbine engine. The liquid fuel injection spoke may include an inlet end and an outlet end. The liquid fuel injection spoke may further include a head located at the inlet end and a stem extending along a longitudinal axis from the head to the outlet end. The stem may define a fluid passageway therein. The head may include a cavity with an inner wall. The inner wall may include an annular protrusion.Type: ApplicationFiled: July 27, 2012Publication date: July 4, 2013Inventors: Alexander Ilich Krichever, Mario Eugene Abreu, Norm Turoff, John Frederick Lockyer, Christopher Zdzislaw Twardochleb, David Marc Stansel
-
Publication number: 20120111016Abstract: A fuel injector for a gas turbine engine may include an injector housing extending along a longitudinal axis and configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a flow path for a fuel air mixture to the combustor extending longitudinally within the injector housing, and a gallery for liquid fuel encircling the flow path. The gallery may include a plurality of fuel spokes that are configured to deliver liquid fuel from the gallery to the flow path. The gallery may extend from a feed end to a terminal end that overlaps the feed end. The feed end may be a region where liquid fuel enters the gallery and the terminal end may be a region where the gallery terminates.Type: ApplicationFiled: November 10, 2010Publication date: May 10, 2012Inventors: John Frederick Lockyer, Christopher Zdzislaw Twardochleb, Mario Eugene Abreu
-
Patent number: 8099940Abstract: A pilot assembly for a fuel injector of a gas turbine engine may include a longitudinal passageway having an outlet end. A mass flow in the longitudinal passageway may generally flow towards the outlet end during operation of the engine. The pilot assembly may also include a liquid fuel nozzle that is positioned to direct a mixture of liquid fuel and air near the outlet end, and a compressed air inlet that is configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure. The longitudinal passageway may also include a flow restriction section. The flow restriction section may be a narrowed section of the longitudinal passageway, in which an upstream side of the flow restriction section may have compressed air at substantially the compressor discharge pressure and a downstream side may have air at a lower pressure and a higher velocity.Type: GrantFiled: December 18, 2008Date of Patent: January 24, 2012Assignee: Solar Turbines Inc.Inventors: Christopher Zdzislaw Twardochleb, John Frederick Lockyer, Mario Eugene Abreu
-
Patent number: 7966832Abstract: A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion of the injector grommet is disposed within a groove of the connection assembly.Type: GrantFiled: December 29, 2004Date of Patent: June 28, 2011Assignee: Solar Turbines IncInventors: John Frederick Lockyer, Stuart Alexander Greenwood
-
Publication number: 20110030377Abstract: A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion of the injector grommet is disposed within a groove of the connection assembly.Type: ApplicationFiled: October 19, 2010Publication date: February 10, 2011Applicant: Caterpillar Inc.Inventors: John Frederick LOCKYER, Stuart Alexander GREENWOOD
-
Publication number: 20100154424Abstract: A pilot assembly for a fuel injector of a gas turbine engine may include a longitudinal passageway having an outlet end. A mass flow in the longitudinal passageway may generally flow towards the outlet end during operation of the engine. The pilot assembly may also include a liquid fuel nozzle that is positioned to direct a mixture of liquid fuel and air near the outlet end, and a compressed air inlet that is configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure. The longitudinal passageway may also include a flow restriction section. The flow restriction section may be a narrowed section of the longitudinal passageway, in which an upstream side of the flow restriction section may have compressed air at substantially the compressor discharge pressure and a downstream side may have air at a lower pressure and a higher velocity.Type: ApplicationFiled: December 18, 2008Publication date: June 24, 2010Inventors: Christopher Zdzislaw Twardochleb, John Frederick Lockyer, Mario Eugene Abreu