Patents by Inventor Matthew Durham Collier
Matthew Durham Collier 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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Publication number: 20170356344Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency. Specifically, the compressor discharge temperature may be modified by adjusting the inlet guide vanes of the compressor or by adjusting a temperature of air entering the compressor.Type: ApplicationFiled: August 28, 2017Publication date: December 14, 2017Applicant: General Electric CompanyInventors: Sarah Lori Crothers, Matthew Durham Collier, Scott Edward Sherman, Joseph Vincent Citeno
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Patent number: 9745896Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency.Type: GrantFiled: February 26, 2013Date of Patent: August 29, 2017Assignee: GENERAL ELECTRIC COMPANYInventors: Sarah Lori Crothers, Matthew Durham Collier, Scott Edward Sherman, Joseph Vincent Citeno
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Patent number: 9638041Abstract: 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: October 23, 2013Date of Patent: May 2, 2017Assignee: General Electric CompanyInventors: Lee Larned Brozyna, Matthew Durham Collier, Christopher William Kester, Alexander Stein
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Patent number: 9127560Abstract: A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.Type: GrantFiled: December 1, 2011Date of Patent: September 8, 2015Assignee: General Electric CompanyInventors: Matthew Durham Collier, Anthony Louis Giglio, Gayathri Puram
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Publication number: 20150110629Abstract: 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: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Lee Larned Brozyna, Matthew Durham Collier, Christopher William Kester, Alexander Stein
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Patent number: 8876478Abstract: A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.Type: GrantFiled: November 17, 2010Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Stephen Paul Wassynger, Daniel Howard Tragesser, Matthew Durham Collier
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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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Publication number: 20140238033Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency.Type: ApplicationFiled: February 26, 2013Publication date: August 28, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Sarah Lori Crothers, Matthew Durham Collier, Scott Edward Sherman, Joseph Vincent Citeno
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Patent number: 8790086Abstract: A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.Type: GrantFiled: November 11, 2010Date of Patent: July 29, 2014Assignee: General Electric CompanyInventors: Mark Steven Honkomp, Matthew Durham Collier, Jason Douglas Herzlinger
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Publication number: 20130142649Abstract: A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.Type: ApplicationFiled: December 1, 2011Publication date: June 6, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Matthew Durham Collier, Anthony Louis Giglio, Gayathri Puram
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Publication number: 20130071249Abstract: 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: ApplicationFiled: September 19, 2011Publication date: March 21, 2013Inventors: Matthew Durham Collier, Gayathri Puram, Paul Kendall Smith, Jacob Charles Perry, II
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Publication number: 20120195742Abstract: A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance.Type: ApplicationFiled: January 28, 2011Publication date: August 2, 2012Inventors: Sanjeev Kumar Jain, Rajnikumar Nandalal Suthar, Matthew Durham Collier
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Publication number: 20120121423Abstract: A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.Type: ApplicationFiled: November 11, 2010Publication date: May 17, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Steven Honkomp, Matthew Durham Collier, Jason Douglas Herzlinger
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Publication number: 20120121424Abstract: A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.Type: ApplicationFiled: November 17, 2010Publication date: May 17, 2012Applicant: General Electric CompanyInventors: Stephen Paul WASSYNGER, Daniel Howard TRAGESSER, Matthew Durham COLLIER
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Patent number: 7731482Abstract: A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.Type: GrantFiled: June 13, 2006Date of Patent: June 8, 2010Assignee: General Electric CompanyInventors: Benjamin Arnette Lagrange, Randall Richard Good, Gary Charles Liotta, Jon Robert DeLong, Matthew Durham Collier, James William Vehr, Anthony Aaron Chiurato
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Publication number: 20070286734Abstract: A damping system for a turbin bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.Type: ApplicationFiled: June 13, 2006Publication date: December 13, 2007Applicant: GENERAL ELECTRIC COMPANYInventors: Benjamin Arnette Lagrange, Randall Richard Good, Gary Charles Liotta, Jon Robert DeLong, Matthew Durham Collier, James William Vehr