Patents by Inventor Daniel Mark Brown
Daniel Mark Brown 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: 9435217Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: GrantFiled: October 6, 2015Date of Patent: September 6, 2016Assignee: General Electric CompanyInventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, Jr.
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Publication number: 20160024954Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: ApplicationFiled: October 6, 2015Publication date: January 28, 2016Inventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, JR.
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Patent number: 9200528Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: GrantFiled: September 11, 2012Date of Patent: December 1, 2015Assignee: General Electric CompanyInventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, Jr.
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Publication number: 20140072415Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: ApplicationFiled: September 11, 2012Publication date: March 13, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, JR.
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Patent number: 6877321Abstract: A method for assembling a turbine engine including an exhaust diffuser extending aftward from exhaust casing, wherein the method includes coupling a relief diaphragm to the exhaust diffuser and coupling a guide system to the exhaust diffuser such that the guide system is radially inward from the relief diaphragm and defines at least a portion of the exhaust flow path through the exhaust diffuser.Type: GrantFiled: March 31, 2003Date of Patent: April 12, 2005Assignee: General Electric CompanyInventors: Klaus M. Retzlaff, Daniel Mark Brown
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Patent number: 6854954Abstract: A method for assembling a power system is provided. The method includes coupling a first turbine and second turbine together with a coupling that extends between a first rotor of a first turbine and a second rotor of the second turbine, and such that the first turbine has fluid flow along a first flow path, and the second turbine has fluid flow along a second flow path. The method further includes fixedly coupling an outer wall to the first turbine that directs fluid flow from the first flow path towards the second flow path.Type: GrantFiled: March 3, 2003Date of Patent: February 15, 2005Assignee: General Electric CompanyInventors: Douglas Carl Hofer, Daniel Mark Brown, Scott William Blackwell, Norman Douglas Lathrop, Edward John Sharrow
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Publication number: 20040187472Abstract: A method for assembling a turbine engine including an exhaust diffuser extending aftward from exhaust casing, wherein the method includes coupling a relief diaphragm to the exhaust diffuser and coupling a guide system to the exhaust diffuser such that the guide system is radially inward from the relief diaphragm and defines at least a portion of the exhaust flow path through the exhaust diffuser.Type: ApplicationFiled: March 31, 2003Publication date: September 30, 2004Applicant: GENERAL ELECTRIC COMPANYInventors: Klaus M. Retzlaff, Daniel Mark Brown
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Publication number: 20040175267Abstract: A method for assembling a power system is provided. The method includes coupling a first turbine and second turbine together with a coupling that extends between a first rotor of a first turbine and a second rotor of the second turbine, and such that the first turbine has fluid flow along a first flow path, and the second turbine has fluid flow along a second flow path. The method further includes fixedly coupling an outer wall to the first turbine that directs fluid flow from the first flow path towards the second flow path.Type: ApplicationFiled: March 3, 2003Publication date: September 9, 2004Inventors: Douglas Carl Hofer, Daniel Mark Brown, Scott William Blackwell, Norman Douglas Lathrop, Edward John Sharrow
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Patent number: 6783321Abstract: The shafts of upstream and downstream turbines are interconnected by a coupling. A diffuser is provided in an intermediate cavity between the upstream and downstream turbines to recover kinetic energy, as well as minimize or eliminate windage and spinning losses resultant from exposure of the coupling to the flowpath along the turbines. A radial entry inlet provides a supplemental fluid admission into the intermediate cavity, the admission being turned axially and circumferentially for joining with the flow exiting the upstream turbine for combined flow to the downstream turbine.Type: GrantFiled: November 6, 2002Date of Patent: August 31, 2004Assignee: General Electric CompanyInventors: Norman Douglas Lathrop, Daniel Mark Brown, Edward John Sharrow, Kristin Segreto, Douglas Carl Hofer
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Publication number: 20040086375Abstract: The shafts of upstream and downstream turbines are interconnected by a coupling. A diffuser is provided in an intermediate cavity between the upstream and downstream turbines to recover kinetic energy, as well as minimize or eliminate windage and spinning losses resultant from exposure of the coupling to the flowpath along the turbines. A radial entry inlet provides a supplemental fluid admission into the intermediate cavity, the admission being turned axially and circumferentially for joining with the flow exiting the upstream turbine for combined flow to the downstream turbine.Type: ApplicationFiled: November 6, 2002Publication date: May 6, 2004Inventors: Norman Douglas Lathrop, Daniel Mark Brown, Edward John Sharrow, Kristin Segreto, Douglas Carl Hofer
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Publication number: 20040052638Abstract: A cover is provided to conceal the forward-facing step defined by the protrusion of the first stage diaphragm into the LP inlet. The cover presents a smoothly contoured surface to the flowing fluid in both radial and circumferential directions and thus reduces energy loss of the working fluid, thereby to increase performance of the LP turbine.Type: ApplicationFiled: September 12, 2002Publication date: March 18, 2004Inventors: Daniel Mark Brown, Stephen R. Swan, Edward J. Sharrow, Carol A. Sterantino
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Patent number: 6705829Abstract: A cover is provided to conceal the forward-facing step defined by the protrusion of the first stage diaphragm into the LP inlet. The cover presents a smoothly contoured surface to the flowing fluid in both radial and circumferential directions and thus reduces energy loss of the working fluid, thereby to increase performance of the LP turbine.Type: GrantFiled: September 12, 2002Date of Patent: March 16, 2004Assignee: General Electric CompanyInventors: Daniel Mark Brown, Stephen R. Swan, Edward J. Sharrow, Carol A. Sterantino
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Patent number: 6609881Abstract: A pair of steam turbine inlet ports are disposed at opposite sides of a steam turbine housing for flowing steam in opposite circumferential directions in a generally annular steam chamber to first stages of a turbine through axially opposite outlets. Portions of the chamber in the upper and lower housing have decreasing cross-sections in a generally circumferential direction away from the steam inlet portions to provide a substantially uniform flow of steam about the chamber in a generally radially inward direction and about and through the axial outlets.Type: GrantFiled: November 15, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Daniel Mark Brown, George Horner Kirby, Andrew Ivan Christopher Hunter, Richard Lloyd Mattice, Brian E. Thompson
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Publication number: 20030091431Abstract: A pair of steam turbine inlet ports are disposed at opposite sides of a steam turbine housing for flowing steam in opposite circumferential directions in a generally annular steam chamber to first stages of a turbine through axially opposite outlets. Portions of the chamber in the upper and lower housing have decreasing cross-sections in a generally circumferential direction away from the steam inlet portions to provide a substantially uniform flow of steam about the chamber in a generally radially inward direction and about and through the axial outlets.Type: ApplicationFiled: November 15, 2001Publication date: May 15, 2003Inventors: Daniel Mark Brown, George Horner Kirby, Andrew Ivan Christopher Hunter, Richard Lloyd Mattice, Brian E. Thompson
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Patent number: 6484505Abstract: A combustor for a turbine includes a combustor liner; a first flow sleeve surrounding the liner, the flow sleeve having a plurality of rows of cooling holes formed about a circumference of the flow sleeve; and a transition piece connected to the combustor liner and the flow sleeve and adapted to carry hot combustion gases to a stage of the turbines. The transition piece is surrounded by a second flow sleeve which directs cooling air to the transition piece. One of the plurality of rows of cooling holes in the first flow sleeve is located adjacent the transition piece, and cooling conduits are mounted in the cooling holes of at least the first of the plurality of rows of cooling holes to direct impingement cooling air against the surface of the liner while diverting crossflow cooling air around the impingement cooling air.Type: GrantFiled: February 25, 2000Date of Patent: November 26, 2002Assignee: General Electric CompanyInventors: Daniel Mark Brown, David Orus Fitts, Stephen Hugh Black