Patents by Inventor Paul Kendall Smith
Paul Kendall Smith 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: 10253638Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: August 12, 2015Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Patent number: 10221710Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.Type: GrantFiled: February 9, 2016Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: Aaron Gregory Winn, George Andrew Gergely, Mary Virginia Holloway, Paul Kendall Smith
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Patent number: 10138736Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: November 23, 2015Date of Patent: November 27, 2018Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
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Patent number: 10001014Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.Type: GrantFiled: February 9, 2016Date of Patent: June 19, 2018Assignee: General Electric CompanyInventors: Mark Steven Honkomp, Xiaoyong Fu, Paul Kendall Smith, Jalindar Appa Walunj
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Patent number: 9988916Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.Type: GrantFiled: July 16, 2015Date of Patent: June 5, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Aaron Gregory Winn, George Andrew Gergely, Mary Virginia Holloway, Paul Kendall Smith
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Publication number: 20170226880Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Aaron Gregory Winn, George Andrew Gergely, Mary Virginia Holloway, Paul Kendall Smith
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Publication number: 20170226864Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Mark Steven Honkomp, Xiaoyong Fu, Paul Kendall Smith, Jalindar Appa Walunj
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Patent number: 9551226Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.Type: GrantFiled: October 23, 2013Date of Patent: January 24, 2017Assignee: General Electric CompanyInventors: Paul Kendall Smith, Harish Bommanakatte, Anthony Louis Giglio, Jason Douglas Herzlinger, Jacob Charles Perry, II, Alexander Stein
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Publication number: 20170016339Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.Type: ApplicationFiled: July 16, 2015Publication date: January 19, 2017Inventors: Aaron Gregory Winn, George Andrew Gergely, Mary Virginia Holloway, Paul Kendall Smith
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Patent number: 9500085Abstract: A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.Type: GrantFiled: July 23, 2012Date of Patent: November 22, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Paul Kendall Smith, Sylvain Pierre, Dennis Scott Holloway
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Patent number: 9435221Abstract: Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.Type: GrantFiled: August 9, 2013Date of Patent: September 6, 2016Assignee: General Electric CompanyInventor: Paul Kendall Smith
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Publication number: 20160076385Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: ApplicationFiled: November 23, 2015Publication date: March 17, 2016Inventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
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Patent number: 9255480Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.Type: GrantFiled: October 28, 2011Date of Patent: February 9, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Paul Kendall Smith, Gunnar Leif Siden, Craig Allen Bielek, Thomas William Vandeputte
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Publication number: 20150345306Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: ApplicationFiled: August 12, 2015Publication date: December 3, 2015Applicant: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Patent number: 9109455Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: January 20, 2012Date of Patent: August 18, 2015Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Publication number: 20150107265Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Paul Kendall Smith, Harish Bommanakatte, Anthony Louis Giglio, Jason Douglas Herzlinger, Jacob Charles Perry, Alexander Stein
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Publication number: 20150044017Abstract: Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.Type: ApplicationFiled: August 9, 2013Publication date: February 12, 2015Applicant: General Electric CompanyInventor: Paul Kendall Smith
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Patent number: 8845296Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: September 19, 2011Date of Patent: September 30, 2014Assignee: General Electric CompanyInventors: Matthew Durham Collier, Gayathri Puram, Paul Kendall Smith, Jacob Charles Perry, II
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Patent number: 8827641Abstract: A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2011Date of Patent: September 9, 2014Assignee: General Electric CompanyInventors: Paul Kendall Smith, Mary Virginia Holloway, San Jason Nguyen, Daniel Jackson Dillard
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Patent number: 8734116Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2011Date of Patent: May 27, 2014Assignee: General Electric CompanyInventors: Paul Kendall Smith, Spencer Aaron Kareff, Srinivasa Govardhan Jayana