Patents by Inventor Ross James Gustafson
Ross James Gustafson 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: 10539032Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: GrantFiled: December 8, 2016Date of Patent: January 21, 2020Assignee: General Electric CompanyInventors: Sumeet Soni, Rohit Chouhan, Ross James Gustafson, Matthew Peter Scoffone
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Patent number: 9957804Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: GrantFiled: December 18, 2015Date of Patent: May 1, 2018Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Ross James Gustafson, Nicholas Alvin Hogberg
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Patent number: 9957805Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.Type: GrantFiled: December 18, 2015Date of Patent: May 1, 2018Assignee: General Electric CompanyInventors: Sumeet Soni, Ross James Gustafson, Rohit Chouhan, Jason Adam Neville
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Publication number: 20170175530Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.Type: ApplicationFiled: December 18, 2015Publication date: June 22, 2017Inventors: Sumeet Soni, Ross James Gustafson, Rohit Chouhan, Jason Adam Neville
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Publication number: 20170175529Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: ApplicationFiled: December 18, 2015Publication date: June 22, 2017Inventors: Rohit Chouhan, Sumeet Soni, Ross James Gustafson, Nicholas Alvin Hogberg
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Publication number: 20170175556Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: ApplicationFiled: December 8, 2016Publication date: June 22, 2017Inventors: Sumeet SONI, Rohit CHOUHAN, Ross James GUSTAFSON, Matthew Peter SCOFFONE
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Patent number: 9347320Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.Type: GrantFiled: October 23, 2013Date of Patent: May 24, 2016Assignee: General Electric CompanyInventors: Ross James Gustafson, Srinivasa Govardhan Jayana, Spencer Aaron Kareff, Dipesh Dinesh Nanda
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Publication number: 20160024930Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.Type: ApplicationFiled: July 24, 2014Publication date: January 28, 2016Inventors: Kelvin Rono Aaron, Craig Allen Bielek, Ross James Gustafson, Ariel Caesar Prepena Jacala, Spencer Aaron Kareff, Matthew Robert Piersall, John Franklin Ryman
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Publication number: 20150107266Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Ross James Gustafson, Srinivasa Govardhan Jayana, Spencer Aaron Kareff, Dipesh Dinesh Nanda
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Patent number: 9011101Abstract: 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: April 21, 2015Assignee: General Electric CompanyInventors: Ross James Gustafson, Christopher Michael Penny, Aaron Ezekiel Smith, Luke C Sponsellar, William Scott Zemitis
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Patent number: 8998577Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.Type: GrantFiled: November 3, 2011Date of Patent: April 7, 2015Assignee: General Electric CompanyInventors: Ross James Gustafson, Gunnar Leif Siden
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Patent number: 8894376Abstract: Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.Type: GrantFiled: October 28, 2011Date of Patent: November 25, 2014Assignee: General Electric CompanyInventors: Christopher Michael Penny, Ross James Gustafson
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Patent number: 8876485Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. 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. The X and Y values 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 may be joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2011Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Ross James Gustafson, Aaron Gregory Winn
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Publication number: 20130136611Abstract: 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: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Inventors: Ross James Gustafson, Christopher Michael Penny, Aaron Ezekiel Smith, Luke C. Sponseller
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Publication number: 20130136589Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. 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. The X and Y values 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 may be joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Ross James Gustafson, Aaron Gregory Winn
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Publication number: 20130115075Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.Type: ApplicationFiled: November 3, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Ross James Gustafson, Gunnar Leif Siden
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Publication number: 20130108452Abstract: Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.Type: ApplicationFiled: October 28, 2011Publication date: May 2, 2013Applicant: General Electric CompanyInventors: Christopher Michael Penny, Ross James Gustafson
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Publication number: 20130039758Abstract: According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.Type: ApplicationFiled: August 9, 2011Publication date: February 14, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Aaron Ezekiel Smith, Bradley Taylor Boyer, Anthony Louis Giglio, Ross James Gustafson, Christopher Michael Penny
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Publication number: 20110271689Abstract: In one embodiment, a compressor discharge casing of a gas turbine engine is designed to receive discharge air from a compressor and to direct a first portion of the discharge air into a combustor of the gas turbine engine and a second portion of the discharge air into a nozzle assembly of a gas turbine to cool components of the gas turbine. A heat transfer device is configured to receive a cooling fluid and to cool the second portion of the discharge air with the cooling fluid.Type: ApplicationFiled: May 6, 2010Publication date: November 10, 2011Applicant: General Electric CompanyInventors: Benjamin Paul Lacy, Ashok Kumar Anand, Raymond Edward Chupp, Andres Jose Garcia-Crespo, Ross James Gustafson