Patents by Inventor Madhavan Poyyapakkam
Madhavan Poyyapakkam 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).
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Patent number: 9157637Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.Type: GrantFiled: August 26, 2011Date of Patent: October 13, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Madhavan Poyyapakkam, Adnan Eroglu, Andrea Ciani, Diane Lauffer, Uwe Ruedel
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Patent number: 8713943Abstract: The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body.Type: GrantFiled: May 7, 2012Date of Patent: May 6, 2014Assignee: Alstom Technology LtdInventors: Madhavan Poyyapakkam, Urs Benz, Andre Theuer, Anton Winkler, Andrea Ciani
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Patent number: 8677756Abstract: A burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, includes an injection device for introducing at least one gaseous fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body. The body has two lateral surfaces substantially parallel to the main flow direction. At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle.Type: GrantFiled: May 7, 2012Date of Patent: March 25, 2014Assignee: Alstom Technology Ltd.Inventors: Madhavan Poyyapakkam, Anton Winkler, Khawar Syed, Adnan Eroglu, Andrea Ciani
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Patent number: 8572980Abstract: A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.Type: GrantFiled: May 7, 2012Date of Patent: November 5, 2013Assignee: Alstom Technology LtdInventors: Anton Winkler, Urs Benz, Andre Theuer, Diane Lauffer, Madhavan Poyyapakkam
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Patent number: 8490398Abstract: The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.Type: GrantFiled: May 7, 2012Date of Patent: July 23, 2013Assignee: Alstom Technology Ltd.Inventors: Madhavan Poyyapakkam, Anton Winkler, Khawar Syed, Andrea Ciani
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Patent number: 8413445Abstract: A fuel nozzle assembly for a combustor in a gas turbine including: a gaseous fuel passage and a fuel nozzle at a distal end of the passage; an air tube concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle, wherein the air tube includes a distal section extending axially beyond the fuel injection nozzle; a first fuel-air mixing zone inside the distal section of the air tube, wherein the first fuel-air mixing zone is downstream of the fuel injection nozzle; a flame holder including a porous structure with thermal barrier coating and micro swirlers and defining a downstream end of the first fuel-air mixing zone, wherein fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor.Type: GrantFiled: May 11, 2007Date of Patent: April 9, 2013Assignee: General Electric CompanyInventor: Madhavan Poyyapakkam
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Patent number: 8402768Abstract: The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.Type: GrantFiled: May 7, 2012Date of Patent: March 26, 2013Assignee: Alstom Technology Ltd.Inventors: Khawar Syed, Madhavan Poyyapakkam, Anton Winkler, Andre Theuer
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Publication number: 20120324863Abstract: A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.Type: ApplicationFiled: May 7, 2012Publication date: December 27, 2012Applicant: ALSTOM Technology LtdInventors: Anton WINKLER, Urs BENZ, Andre THEUER, Diane LAUFFER, Madhavan POYYAPAKKAM
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Publication number: 20120297777Abstract: The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body.Type: ApplicationFiled: May 7, 2012Publication date: November 29, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan Poyyapakkam, Urs Benz, Andre Theuer, Anton Winkler, Andrea Ciani
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Publication number: 20120285172Abstract: The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.Type: ApplicationFiled: May 7, 2012Publication date: November 15, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan Poyyapakkam, Anton Winkler, Khawar Syed, Andrea Ciani
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Publication number: 20120272659Abstract: The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.Type: ApplicationFiled: May 7, 2012Publication date: November 1, 2012Applicant: ALSTOM Technology LtdInventors: Khawar Syed, Madhavan Poyyapakkam, Anton Winkler, Andre Theuer
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Publication number: 20120260622Abstract: A burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, includes an injection device for introducing at least one gaseous fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body. The body has two lateral surfaces substantially parallel to the main flow direction. At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle.Type: ApplicationFiled: May 7, 2012Publication date: October 18, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan POYYAPAKKAM, Anton Winkler, Khawar Syed, Adnan Eroglu, Andrea Ciani
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Publication number: 20120047908Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.Type: ApplicationFiled: August 26, 2011Publication date: March 1, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan Poyyapakkam, Adnan Eroglu, Andrea Ciani, Diane Lauffer, Uwe Ruedel
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Patent number: 7757492Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.Type: GrantFiled: May 18, 2007Date of Patent: July 20, 2010Assignee: General Electric CompanyInventors: John Charles Intile, Madhavan Poyyapakkam, Ganesh Pejawar Rao, Karthick Kaleeswaran
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Publication number: 20080282667Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.Type: ApplicationFiled: May 18, 2007Publication date: November 20, 2008Inventors: John Charles Intile, Madhavan Poyyapakkam, Ganesh Pejawar Rao, Karthick Kaleeswaran
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Publication number: 20080276618Abstract: A mixing region of a fuel nozzle assembly for a combustor in a gas turbine, the assembly including: a gaseous fuel nozzle having a center axis and extending along the center axis, the fuel nozzle including a gaseous fuel passage and a fuel nozzle at a distal end of the passage; an air tube concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle, wherein the air tube includes a distal section extending axially beyond the fuel injection nozzle; a first fuel-air mixing zone defined by and inside the distal section of the air tube, wherein said first fuel-air mixing zone is downstream of the fuel injection nozzle; a flame holder comprising a porous structure with thermal barrier coating and micro swirlers and defining a downstream end of the first fuel-air mixing zone, wherein fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor.Type: ApplicationFiled: May 11, 2007Publication date: November 13, 2008Applicant: GENERAL ELECTRIC COMPANYInventor: Madhavan Poyyapakkam
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Patent number: 7082770Abstract: A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured to incorporate a conical aft portion having a plurality of air feed holes that reduce pressure loss to the incoming air and flow separation effects from the surrounding combustor hardware, thereby resulting in improved combustor performance.Type: GrantFiled: December 24, 2003Date of Patent: August 1, 2006Inventors: Vincent C. Martling, Martin John Spalding, Madhavan Poyyapakkam
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Publication number: 20050144953Abstract: A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured to incorporate a conical aft portion having a plurality of air feed holes that reduce pressure loss to the incoming air and flow separation effects from the surrounding combustor hardware, thereby resulting in improved combustor performance.Type: ApplicationFiled: December 24, 2003Publication date: July 7, 2005Inventors: Vincent Martling, Martin Spalding, Madhavan Poyyapakkam