Patents by Inventor Manampathy Gangadharan Giridharan
Manampathy Gangadharan Giridharan 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: 11371708Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.Type: GrantFiled: April 6, 2018Date of Patent: June 28, 2022Assignee: General Electric CompanyInventors: Mathew Paul Thariyan, Manampathy Gangadharan Giridharan, Kapil Kumar Singh, Sravan Kumar Dheeraj Kapilavai, Keith Robert McManus, Gregory Allen Boardman, Mark David Durbin
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Patent number: 11156361Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: GrantFiled: July 19, 2019Date of Patent: October 26, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 11067280Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.Type: GrantFiled: April 5, 2019Date of Patent: July 20, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Patent number: 10935245Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.Type: GrantFiled: November 20, 2018Date of Patent: March 2, 2021Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Manampathy Gangadharan Giridharan, Michael Anthony Benjamin, Pradeep Naik, Clayton Stuart Cooper, Vishal Sanjay Kediya
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Publication number: 20210010674Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.Type: ApplicationFiled: April 6, 2018Publication date: January 14, 2021Inventors: Mathew Paul THARIYAN, Manampathy Gangadharan GIRIDHARAN, Kapil Kumar SINGH, Sravan Kumar Dheeraj KAPILAVAI, Keith Robert MCMANUS, Gregory Allen BOARDMAN, Mark David DURBIN
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Publication number: 20200158343Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.Type: ApplicationFiled: November 20, 2018Publication date: May 21, 2020Inventors: Gregory Allen Boardman, Manampathy Gangadharan Giridharan, Michael Anthony Benjamin, Pradeep Naik, Clayton Stuart Cooper, Vishal Sanjay Kediya
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Publication number: 20200025385Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.Type: ApplicationFiled: April 5, 2019Publication date: January 23, 2020Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20190346141Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: ApplicationFiled: July 19, 2019Publication date: November 14, 2019Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 10393382Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: GrantFiled: November 4, 2016Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 10352569Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: GrantFiled: November 4, 2016Date of Patent: July 16, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Patent number: 10295190Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: GrantFiled: November 4, 2016Date of Patent: May 21, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20180313540Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly defines a combustion chamber and a diffuser cavity disposed upstream of the combustion chamber. The combustor assembly includes an acoustic damper that includes an aft wall adjacent to the combustion chamber and a forward wall adjacent to the diffuser cavity. A connecting wall is extended at least along the longitudinal direction and coupled to the aft wall and the forward wall. A damper cavity is defined by the connecting wall, the aft wall, and the forward wall.Type: ApplicationFiled: May 1, 2017Publication date: November 1, 2018Inventors: Sharath Bangalore Nagaraja, Owen Graham, Kwankoo Kim, Manampathy Gangadharan Giridharan, Gregory Allen Boardman
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Publication number: 20180128491Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20180128489Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20180128490Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Publication number: 20180010795Abstract: A deflector for a gas turbine engine combustor. The combustor includes a liner defining a combustion zone and a mixer assembly configured to supply the combustion zone with a predetermined mixture of fuel and air. The deflector includes a deflector body configured to couple to the liner. The deflector body includes a first surface configured to reflect thermal radiation to a predetermined focal area, and an aperture extending through the deflector body and configured to receive the mixer assembly therethrough.Type: ApplicationFiled: July 6, 2016Publication date: January 11, 2018Inventors: Hiranya Kumar Nath, Manampathy Gangadharan Giridharan
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Patent number: 9340277Abstract: An airfoil section of a propeller for a propulsion device includes a pressure surface and a suction surface, the pressure surface and suction surface intersecting at a leading edge and a trailing edge. The airfoil section has a meanline defined midway between the pressure surface and the suction surface and a meanline angle is defined as an angle between a tangent to the meanline and a centerline of the propeller. The blade has a meanline curvature defined as the slope of a meanline angle with respect to chord fraction along the meanline, and at least a portion of the meanline has a meanline curvature that increases from between approximately 0.1 chord fraction progressing toward the leading edge and at least a portion of the meanline has a meanline curvature that decreases from between approximately 0.1 chord fraction progressing toward the leading edge.Type: GrantFiled: April 2, 2012Date of Patent: May 17, 2016Assignee: General Electric CompanyInventors: Andrew Breeze-Stringfellow, Manampathy Gangadharan Giridharan, Syed Arif Khalid, Leroy H. Smith, Jr.
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Publication number: 20130224031Abstract: An airfoil section of a propeller for a propulsion device includes a pressure surface and a suction surface, the pressure surface and suction surface intersecting at a leading edge and a trailing edge. The airfoil section has a meanline defined midway between the pressure surface and the suction surface and a meanline angle is defined as an angle between a tangent to the meanline and a centerline of the propeller. The blade has a meanline curvature defined as the slope of a meanline angle with respect to chord fraction along the meanline, and at least a portion of the meanline has a meanline curvature that increases from between approximately 0.1 chord fraction progressing toward the leading edge and at least a portion of the meanline has a meanline curvature that decreases from between approximately 0.1 chord fraction progressing toward the leading edge.Type: ApplicationFiled: April 2, 2012Publication date: August 29, 2013Inventors: Andrew Breeze-Stringfellow, Manampathy Gangadharan Giridharan, Syed Arif Khalid, Leroy H. Smith, JR.