Patents by Inventor Bhanu Mahasamudram Reddy
Bhanu Mahasamudram Reddy 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: 10808547Abstract: An apparatus and method of cooling an airfoil for a gas turbine engine includes a tip for the radially outer end of the airfoil with internal ribs defining cooling circuits within an interior of the airfoil. The ribs can be full-length, extending between a root and tip of the airfoil. A gap can be formed in the full-length ribs near the tip to form a thermal stress reduction structure for the full-length rib.Type: GrantFiled: February 8, 2016Date of Patent: October 20, 2020Assignee: General Electric CompanyInventors: Bridget Lucy Lessard, Bhanu Mahasamudram Reddy, Gaoqiu Zhu, Michael Jong Lee
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Patent number: 10577943Abstract: An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.Type: GrantFiled: May 11, 2017Date of Patent: March 3, 2020Assignee: General Electric CompanyInventors: Andrea Terese Marinelli, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Publication number: 20180328188Abstract: An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.Type: ApplicationFiled: May 11, 2017Publication date: November 15, 2018Inventors: Andrea Terese Marinelli, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Patent number: 9976424Abstract: A turbine blade includes an airfoil having an internal cooling circuit. The cooling circuit includes a body cooling passage with at least one turn, and a tip cooling channel that forms a cooling barrier to thermally isolate the turn from at least a portion of the exterior surface of the airfoil.Type: GrantFiled: July 2, 2015Date of Patent: May 22, 2018Assignee: General Electric CompanyInventors: Christopher Lloyd McKenzie, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Publication number: 20170226869Abstract: An apparatus and method of cooling an airfoil for a gas turbine engine includes a tip for the radially outer end of the airfoil with internal ribs defining cooling circuits within an interior of the airfoil. The ribs can be full-length, extending between a root and tip of the airfoil. A gap can be formed in the full-length ribs near the tip to form a thermal stress reduction structure for the full-length rib.Type: ApplicationFiled: February 8, 2016Publication date: August 10, 2017Inventors: Bridget Lucy Lessard, Bhanu Mahasamudram Reddy, Gaoqiu Zhu, Michael Jong Lee
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Publication number: 20170002664Abstract: A turbine blade includes an airfoil having an internal cooling circuit. The cooling circuit includes a body cooling passage with at least one turn, and a tip cooling channel that forms a cooling barrier to thermally isolate the turn from at least a portion of the exterior surface of the airfoil.Type: ApplicationFiled: July 2, 2015Publication date: January 5, 2017Inventors: Christopher Lloyd McKenzie, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Patent number: 8591189Abstract: A turbine blade includes forward and aft serpentine cooling circuits terminating in corresponding forward and aft impingement channels. Each serpentine circuit has two metered inlets for distributing primary inlet flow to the first passes thereof and supplemental inlet flow to the last passes thereof.Type: GrantFiled: November 20, 2006Date of Patent: November 26, 2013Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Patent number: 8281604Abstract: A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.Type: GrantFiled: December 17, 2007Date of Patent: October 9, 2012Assignee: General Electric CompanyInventors: Mark Broomer, Victor Hugo Silva Correia, Robert Francis Manning, Stephen Kin-Keung Tung, Bhanu Mahasamudram Reddy
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Patent number: 7857587Abstract: A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip.Type: GrantFiled: November 30, 2006Date of Patent: December 28, 2010Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Publication number: 20090155050Abstract: A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.Type: ApplicationFiled: December 17, 2007Publication date: June 18, 2009Inventors: Mark Broomer, Victor Hugo Silva Correia, Robert Francis Manning, Stephen Kin-Keung Tung, Bhanu Mahasamudram Reddy
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Publication number: 20080131278Abstract: A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Victor Hugo Silva Correia, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Publication number: 20080118366Abstract: A turbine blade includes forward and aft serpentine cooling circuits terminating in corresponding forward and aft impingement channels. Each serpentine circuit has two metered inlets for distributing primary inlet flow to the first passes thereof and supplemental inlet flow to the last passes thereof.Type: ApplicationFiled: November 20, 2006Publication date: May 22, 2008Inventors: Victor Hugo Silva Correia, Robert Francis Manning, Bhanu Mahasamudram Reddy
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Patent number: 6595748Abstract: A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in front of a pair of side channels. The leading edge channel receives coolant from the pressure side channel in isolation from the suction side channel.Type: GrantFiled: August 2, 2001Date of Patent: July 22, 2003Assignee: General Electric CompanyInventors: David Allen Flodman, Bhanu Mahasamudram Reddy, Mark Douglas Gledhill
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Publication number: 20030026698Abstract: A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in front of a pair of side channels. The leading edge channel receives coolant from the pressure side channel in isolation from the suction side channel.Type: ApplicationFiled: August 2, 2001Publication date: February 6, 2003Inventors: David Allen Flodman, Bhanu Mahasamudram Reddy, Mark Douglas Gledhill