Patents by Inventor Stephen W. Jorgensen
Stephen W. Jorgensen 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: 10920670Abstract: A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.Type: GrantFiled: October 6, 2017Date of Patent: February 16, 2021Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Marcos Escudero Olano, Stephan Strueken, Thomas Zierer, Frank Graf, Adnan Eroglu, Joshua R. McNally, Stephen W. Jorgensen, Afzal Pasha Mohammed
-
Patent number: 10718525Abstract: Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.Type: GrantFiled: June 27, 2016Date of Patent: July 21, 2020Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam
-
Patent number: 10571128Abstract: Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.Type: GrantFiled: June 27, 2016Date of Patent: February 25, 2020Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam
-
Patent number: 10215418Abstract: The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.Type: GrantFiled: October 13, 2014Date of Patent: February 26, 2019Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Jeremy Metternich, Stephen W. Jorgensen, David Giel, Ramesh Keshava-Bhattu
-
Publication number: 20180100439Abstract: A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.Type: ApplicationFiled: October 6, 2017Publication date: April 12, 2018Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Marcos ESCUDERO OLANO, Stephan STRUEKEN, Thomas ZIERER, Frank GRAF, Adnan EROGLU, Joshua R. McNALLY, Stephen W. JORGENSEN, Afzal Pasha MOHAMMED
-
Publication number: 20170002743Abstract: Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.Type: ApplicationFiled: June 27, 2016Publication date: January 5, 2017Inventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam
-
Publication number: 20170002742Abstract: Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.Type: ApplicationFiled: June 27, 2016Publication date: January 5, 2017Inventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam
-
Publication number: 20170003032Abstract: Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary combustor and/or fuel cartridge assembly may comprise first and second fuel circuits or manifolds. Methods and systems are also provided for staging and controlling a flow of fuel and/or water through different fuel circuits and pilot injectors, to allow purging and ignition using different fuel circuits, pilot injectors, and fuel sources.Type: ApplicationFiled: June 27, 2016Publication date: January 5, 2017Inventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam
-
Patent number: 9429206Abstract: A mountable attachment for positioning a sensor in an environment, like a combustion chamber of a gas turbine is disclosed. The mountable attachment includes a mounting member having a hollow elongated configuration for incorporating the sensor therewithin. The attachment further includes at least one primary resilient member disposed within the mounting member in a coordinating manner with the sensor for applying an axially outward force on the mounting member to prevent thereto from loosening from a counterpart , and providing a mounting torque for mounting the sensor at a target position within the environment . The attachment may also include additional resilient member, such as a secondary resilient member, which may in combination with the primary resilient members attain a resulting mounting force to prevent the mounting member from loosening from the counterpart.Type: GrantFiled: May 9, 2014Date of Patent: August 30, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Mirko Ruben Bothien, Stephen W. Jorgensen
-
Publication number: 20160102864Abstract: The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.Type: ApplicationFiled: October 13, 2014Publication date: April 14, 2016Inventors: JEREMY METTERNICH, Stephen W. Jorgensen, David Giel, Ramesh Keshava-Bhattu
-
Publication number: 20140346313Abstract: A mountable attachment for positioning a sensor in an environment, like a combustion chamber of a gas turbine is disclosed. The mountable attachment includes a mounting member having a hollow elongated configuration for incorporating the sensor therewithin. The attachment further includes at least one primary resilient member disposed within the mounting member in a coordinating manner with the sensor for applying an axially outward force on the mounting member to prevent thereto from loosening from a counterpart , and providing a mounting torque for mounting the sensor at a target position within the environment . The attachment may also include additional resilient member, such as a secondary resilient member, which may in combination with the primary resilient members attain a resulting mounting force to prevent the mounting member from loosening from the counterpart.Type: ApplicationFiled: May 9, 2014Publication date: November 27, 2014Inventors: Mirko Ruben Bothien, Stephen W. Jorgensen
-
Patent number: 8684130Abstract: An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner.Type: GrantFiled: November 30, 2012Date of Patent: April 1, 2014Assignee: Alstom Technology Ltd.Inventors: Mirko Ruben Bothien, Stephen W. Jorgensen, Douglas Pennell
-
Publication number: 20140069738Abstract: An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner.Type: ApplicationFiled: November 30, 2012Publication date: March 13, 2014Applicant: ALSTOM Technology LtdInventors: Mirko Ruben BOTHIEN, Stephen W. Jorgensen, Douglas Pennell
-
Publication number: 20130255276Abstract: The present invention is directed to a mounting system for a gas turbine transition duct. The mounting system includes a generally C-shaped mounting bracket having a generally radially extending first portion, an arc-shaped second portion, and a generally radially extending third portion. Each of the first portion and third portion includes a spherical bearing and the second portion has a plurality of sets of mounting holes. In another embodiment of the present invention, a gas turbine transition duct is provided having a panel assembly, an aft frame secured to the panel assembly and a mounting system for securing the transition duct to a turbine inlet. The panel assembly includes two formed sheets of metal secured together along axial seams. The panel assembly is secured to an aft frame that is capable of expanding in the circumferential direction due to thermal growth.Type: ApplicationFiled: February 27, 2013Publication date: October 3, 2013Applicant: Alstom Technology Ltd.Inventors: Stephen W. Jorgensen, Joshua R. McNally, Hany Rizkalla
-
Patent number: 8418474Abstract: A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.Type: GrantFiled: September 29, 2008Date of Patent: April 16, 2013Assignee: Alstom Technology Ltd.Inventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford
-
Patent number: 8322146Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.Type: GrantFiled: August 22, 2008Date of Patent: December 4, 2012Assignee: Alstom Technology LtdInventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford, Plazi Ricklin, David John Henriquez
-
Patent number: 8196412Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle ? wherein ? is an angle measured from the inlet end and X, Y, and Z are coordinates define the panel assembly profile at each angle ?. An alternate embodiment of the invention defines an envelope for the uncoated internal profile of the panel assembly.Type: GrantFiled: September 11, 2009Date of Patent: June 12, 2012Assignee: Alstom Technology LtdInventor: Stephen W. Jorgensen
-
Patent number: 8151570Abstract: Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.Type: GrantFiled: December 6, 2007Date of Patent: April 10, 2012Assignee: Alstom Technology LtdInventors: Stephen Jennings, Peter Stuttaford, Stephen W. Jorgensen
-
Publication number: 20110061393Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle ? wherein ? is an angle measured from the inlet end and X, Y, and Z are coordinates define the panel assembly profile at each angle ?. An alternate embodiment of the invention defines an envelope for the uncoated internal profile of the panel assembly.Type: ApplicationFiled: September 11, 2009Publication date: March 17, 2011Applicant: ALSTOM TECHNOLOGIES LTD.Inventor: Stephen W. Jorgensen
-
Patent number: 7677045Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle ? wherein ? is an angle measured from the inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle ? from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.Type: GrantFiled: April 14, 2006Date of Patent: March 16, 2010Assignee: Power Systems Mfg., LLCInventors: Stephen W. Jorgensen, Heather Johnston