Patents by Inventor Jürgen Meisl

Jürgen Meisl 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: 10184351
    Abstract: A gas turbine with a burner, which gas turbine has at least one fuel feed line and at least one fuel outflow line, wherein a flushing water line is connected fluidically to the fuel feed line, and wherein a leakage oil tank is connected fluidically via a drainage line to the fuel outflow line and the connection of the fuel outflow line and the drainage line is provided at a point downstream of at least one closure valve in the fuel outflow line, wherein a bypass line is connected fluidically to the fuel outflow line upstream of the closure valve, which bypass line connects the fuel outflow line fluidically to the leakage oil tank.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: January 22, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Jürgen Meisl, James Smith
  • Publication number: 20170234219
    Abstract: A fuel burner system (10) for a turbine engine (12) configured to operate with syngas fuel, whereby the fuel burner system (10) is configured to reduce nozzle and combustor basket temperatures is disclosed. The fuel burner system (10) may include a plurality of first and second fuel injection ports (16) positioned within a combustor (18), whereby the first fuel injection ports (14) are larger than the second fuel injection ports (16). One or more air injection ports (20) may be aligned with the first fuel injection ports (14). During operation, fuel injected into the combustor (18) from the first fuel injection ports (14) mixes better with the incoming air, causing reduced NOx emissions and lower flame temperatures. Also, the regions between adjacent air injection ports (20), which typically run the hottest, are cooler than conventional combustion system due, in part, to the smaller, second fuel injection ports (16) aligned with regions (22) between adjacent air injection ports (20).
    Type: Application
    Filed: September 11, 2014
    Publication date: August 17, 2017
    Inventors: Vinayak V. Barve, Rafik N. Rofail, Samer P. Wasif, Clifford E. Johnson, Khalil Farid Abou-Jaoude, Stephan Buch, Bernd Prade, Jürgen Meisl
  • Publication number: 20160305276
    Abstract: A gas turbine with a burner, which gas turbine has at least one fuel feed line and at least one fuel outflow line, wherein a flushing water line is connected fluidically to the fuel feed line, and wherein a leakage oil tank is connected fluidically via a drainage line to the fuel outflow line and the connection of the fuel outflow line and the drainage line is provided at a point downstream of at least one closure valve in the fuel outflow line, wherein a bypass line is connected fluidically to the fuel outflow line upstream of the closure valve, which bypass line connects the fuel outflow line fluidically to the leakage oil tank.
    Type: Application
    Filed: December 3, 2014
    Publication date: October 20, 2016
    Applicant: Siemens Aktiengesellschaft
    Inventors: Jürgen Meisl, James Smith
  • Patent number: 9297532
    Abstract: A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: March 29, 2016
    Assignee: Siemens Aktiengesellschaft
    Inventors: Samer P. Wasif, Juergen Meisl, Bertram Janus, Andreas Koch
  • Publication number: 20150316266
    Abstract: A burner (1) with a longitudinal burner axis (2) and a mixing channel (3, 4), formed in an annular manner around the longitudinal burner axis (2), for the mixing of fuel and air. Each mixing channel is bounded radially on the inside by a channel hub (5, 6) and radially on the outside by a channel outer wall (7, 8). A fuel concentration distribution in the mixing channel (3, 4) from the channel hub (5, 6) to the channel outer wall (7, 8) being adjustable by adjusting the introduction of fuel to provide an adjustable fuel concentration distribution at respective radial locations across each mixing claimed. Also a combustion system (20) with a burner (1) and to a method for operating a burner (1).
    Type: Application
    Filed: April 30, 2014
    Publication date: November 5, 2015
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Bernd PRADE, Mariano CANO WOLFF, Boris Ferdinand KOCK, Jürgen MEISL, Andreas DIEBELS, William R. RYAN
  • Patent number: 9074771
    Abstract: A burner insert for a gas turbine combustion chamber is provided. The burner insert includes a burner insert wall including a cold side and a hot side, an edge delimiting the burner insert wall. The edge includes an edge bar extending at least partially circumferentially and projecting beyond the cold side. A burner opening for inserting a burner is formed in the burner insert wall.
    Type: Grant
    Filed: September 14, 2009
    Date of Patent: July 7, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Andreas Böttcher, Andre Kluge, Tobias Krieger, Jürgen Meisl, Kai-Uwe Schildmacher
  • Patent number: 8973367
    Abstract: Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel.
    Type: Grant
    Filed: November 5, 2009
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Tobias Krieger, Jürgen Meisl
  • Publication number: 20130247578
    Abstract: A method of operating a gas turbine, a device for regulating the starting and/or the operation of a gas turbine and a power plant are provided. The method includes continuously extracting fuel from a fuel network, and combusting, in at least one combustion chamber of a gas turbine, the fuel by adding combustion air. For an increase of a fuel stream supplied to the at least one combustion chamber, a fuel volume is extracted from a fuel store and supplied to the fuel still to be supplied to the at least one combustion chamber.
    Type: Application
    Filed: November 29, 2011
    Publication date: September 26, 2013
    Inventors: Eberhard Deuker, Jan Eickelkamp, Boris Ferdinand Kock, Berthold Köstlin, Jürgen Meisl, Dennis Nehlsen
  • Publication number: 20130180251
    Abstract: A burner arrangement includes a carrier and at least two burners which are mounted on the carrier in a flow direction Each burner includes a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades. An attachment is arranged on the side leading to a combustion chamber At least one fuel nozzle is disposed in the attachment and is connected to the fuel duct. The at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form, and the at least two fuel nozzles of the at least two burners with a different functional characteristic and/or spray form include at least one full jet nozzle and at least one pressure swirl nozzle.
    Type: Application
    Filed: August 16, 2011
    Publication date: July 18, 2013
    Inventors: Matthias Hase, Jürgen Meisl
  • Publication number: 20130160423
    Abstract: A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
    Type: Application
    Filed: December 3, 2012
    Publication date: June 27, 2013
    Inventors: Samer P. Wasif, Juergen Meisl, Bertram Janus, Andreas Koch
  • Publication number: 20130104554
    Abstract: A burner assembly for a gas turbine is provided. The burner assembly has a combustor, a centrally arranged pilot burner and plurality of main burners surrounding the pilot burner. Each main burner has a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel. The lance is supported on the housing by swirl blades and an attachment is arranged on the lance in the direction of the combustor. The liquid fuel nozzle is arranged in the attachment downstream of the swirl blades and connected to the fuel channel. For the improved mixing of the fuel with the air, the liquid fuel nozzle is designed as a full jet nozzle and the full jet nozzle has a length and a diameter, the ratio of the length to the diameter is at least 1.5.
    Type: Application
    Filed: July 1, 2011
    Publication date: May 2, 2013
    Inventors: Siegfried Bode, Timothy A. Fox, Thomas Grieb, Matthias Hase, Jürgen Meisl, Sebastian Pfadler
  • Publication number: 20120174591
    Abstract: A fuel line system for a gas turbine and a method for purging the same is provided. Parts of the line system may be purged using a comparatively low quantity of purging medium.
    Type: Application
    Filed: September 23, 2010
    Publication date: July 12, 2012
    Inventors: Matthias Hase, Axel Mayr, Jürgen Meisl
  • Publication number: 20110247338
    Abstract: Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel.
    Type: Application
    Filed: November 5, 2009
    Publication date: October 13, 2011
    Inventors: Andreas Böttcher, Tobias Krieger, Jürgen Meisl
  • Publication number: 20110197590
    Abstract: A burner insert for a gas turbine combustion chamber is provided. The burner insert includes a burner insert wall including a cold side and a hot side, an edge delimiting the burner insert wall. The edge includes an edge bar extending at least partially circumferentially and projecting beyond the cold side. A burner opening for inserting a burner is formed in the burner insert wall.
    Type: Application
    Filed: September 14, 2009
    Publication date: August 18, 2011
    Inventors: Andreas Böttcher, Andre Kluge, Tobias Krieger, Jürgen Meisl, Kai-Uwe Schildmacher
  • Publication number: 20100192583
    Abstract: A method for stabilizing the flame of a premixing burner, comprising a reaction chamber containing a fluid is provided. The method includes injecting an air-fuel mixture into the reaction chamber at a speed that is different from that of the fluid present in the reaction chamber, adjusting the speed such that vortices form at the boundary between the air-fuel mixture and the surrounding fluid. A premixing burner including a reaction chamber and at least one premixing spray nozzle opening into the reaction chamber is also provided. The premixing burner injects an air-fuel mixture into the reaction chamber at a speed that is different from that of the surrounding fluid, the speed being adjusted such that vortices from at the boundary between the air-fuel mixture and the surrounding fluid.
    Type: Application
    Filed: June 19, 2008
    Publication date: August 5, 2010
    Inventors: Mariano Cano Wolff, Patrick Ronald Flohr, Matthias Hase, Martin Lenze, Jürgen Meisl, Paul Pixner, Uwe Remlinger, Kai-Uwe Schildmache, Thomas Alexis Schneider, Jaap van Kampen